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AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
June-July 1968
INDEX
111
...........................
ADVANCED STUDIES OFFICE ..................................
PROJECTS OFFICE ..........................................
IV
AEROSPACE ENVIRONMENT DIVISION
TECHNICAL AND SCIENTIFIC STAFF
.
.
.
I1
v
.
.
.
..
.
.........................
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A
S c i e n t i f i c Advisory O f f i c e
B
Guidance Theory ranch
C
O p t i m i z a t i o n Theory Branch
D
Astrodynamics Branch
.
.
.
.
V I I.
VIII
.....................................
.............................
............................
......................
...........................
AEROPHYSICS DIVISION
A
Mechanical Design O f f i c e
B
Aerodynamic Design Branch
C
Experimental Aerophysics Branch
D
Thermal Environment Branch
E
Unsteady Gas Dynamics Branch
.
VI
...........................
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...............................
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.................................
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DYNAMICS AND nIGHT MECHANICS DIVISION
A
Damping of Liquid O s c i l l a t i o n s by Wall Roughness
B
Saturn V
.............................
C
S a t u r n IB
D
S a t u r n Apollo A p p l i c a t i o n Program
E
G e n e r a t i o n of Real E a r t h Model C i r c u l a r and
E l l i p t i c a l O r b i t V e l o c i t y Requirements
S a t u r n V Launch Vehicle and S p a c e c r a f t Launch
F
Probability
.....
.........
.......
............................................
....................
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.
..........................................
FLIGIFT TEST ANALYSIS DIVISION ............................
A . F l i g h t Mechanics Branch ..............................
B. Tracking and O r b i t a l A n a l y s i s Branch .................
C . F l i g h t E v a l u a t i o n Branch .............................
.
.
.
..
.
�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
I.
TECHNICAL & SCIENTIFIC STAFF
A TM X e n t i t l e d "Wind Vector C a l c u l a t i o n Using Crossed-Beam Data
and D e t e c t o r Arrangement f o r H o r i z o n t a l Winds," was w r i t t e n and i s i n
It s e t s f o r t h t h e c o n d i t i o n s i n which
t h e process of being published.
a continuous, though bounded, a r r a y of unknown winds w i t h i n a l i m i t e d
space volume can be monitored w i t h s u f f i c i e n t accuracy and confidence.
The g e n e r a l method has been a p p l i e d and f u r t h e r developed i n t h e p r a c t i c a l
important c a s e of h o r i z o n t a l wind motion. As a n example, l o c a t i o n s and
a t t i t u d e s of t h r e e ground-based d e t e c t o r s have been computed f o r measuring h o r i z o n t a l winds t h a t could be p r e s e n t a t t h e 100 m-level blowinr
from two o p p o s i t e q u a r t e r s of t h e r o s e .
(Heybey)
11.
ADVANCED STUDIES OFFICE
A.
F l i g h t Mechanics and Performance Analysis Group
1.
Launch Vehicles
The RFQ on t h e "Launch Vehicle T r a j e c t o r y O p t i m i z a t i o n Comp u t e r Program (Phase IV)" was r e l e a s e d on June 13, 1968.
The computer .program i s t o be developed f o r u s e on t h e 1108
system f u l l y u s i n g t h e remote s t a t i o n s f o r q u i c k response time.
F i f t e e n p r o p o s a l s , which have been r e c e i v e d i n response t o
t h e RFQ, a r e now being e v a l u a t e d . DAP i s a s s i s t i n g i n t h i s e v a l u a t i o n
and s e l e c t i o n of t h e c o n t r a c t o r , and i t i s a n t i c i p a t e d t h a t they w i l l
a s s i s t i n c o n t r a c t o r monitoring and o r i e n t a t i o n i n o r d e r t h a t t h e i r
previous e f f o r t s may be e f f i c i e n t l y used and expanded.
Requests f o r performance i n f o r m a t i o n have been r e c e i v e d
from b o t h Col. Burke and M r . N o b l i t t of NASA Headquarters. These d a t a
included performance c a p a b i l i t i e s of t h e I n t - 2 0 and I n t - 2 1 v e h i c l e s
w i t h s t a n d a r d 5 - 2 engines and w i t h t h e J-2s e n g i n e s . This i n f o r m a t i o n
i s t o be used f o r planning a c t i v i t i e s a t NASA Headquarters.
�Performance d a t a on t h e S a t u r n and T i t a n v e h i c l e s a r e
being run i n s u p p o r t of t h e u t i l i z a t i o n s t u d y . Data f o r t h e S a t u r n 660K
v e h i c l e has been obtained and a r e p o r t published on June 20, 1968. The
d a t a f o r t h e T i t a n IIIM have been completed, and a r e p o r t w i l l be
published soon. Performance runs a r e a l s o being made on t h e SA-IB,
SA-IB c o r e v e h i c l e , and SA-IB MLV 11.7B.
2.
Nuclear S t u d i e s
R-AS-VP'requested and was provided w i t h d a t a on t h e high
energy mission performance c a p a b i l i t y of t h e t h r e e - s t a g e S a t u r n MLV-255
w i t h and w i t h o u t a Centaur f o u r t h s t a g e f o r a c o s t e f f e c t i v e n e s s comp a r i s o n s t u d y of t h e S a t u r n nuclear System w i t h a n a l l - c h e m i c a l
system f o r h i g h energy missions i n t h e 1977-1980 time frame.
Performance d a t a on a spectrum of v e h i c l e s have been g i v e n
t o M r . Whit B r a n t l e y f o r OWS/NPS ( o r b i t a l workshop/nuclear e l e c t r i c
power s y s tem) i n t e g r a t i o n s t u d y .
3.
S a t u r n V Workshop
On Monday, June 17, 1968, a p r e s e n t a t i o n was g i v e n t o
D r . von Braun on t h e S a t u r n V Workshop a c t i v i t y . The d i s c u s s i o n was
d i r e c t e d p r i m a r i l y a t answering a r e q u e s t from M r . Chuck Mathews' o f f i c e
t o d e f i n e a n i n t e r m e d i a t e workshop t o be flown i n 1973-74. The c l a s s e s
of s t a t i o n s developed were t h e f o l l o w i n g :
I n t e g r a l : a l l systems, i . e . , crew q u a r t e r s , subsystems,
experiments a r e a l l developed and launched i n t e g r a l l y .
Hybrid:
i n t e g r a l except t h a t t h e experimental module can
b e interchanged a n d / o r flown s e p a r a t e l y .
Modular: a l l major systems developed and flown s e p a r a t e l y
and s m a l l s h o r t - d u r a t i o n s t a t i o n s , e . g . , MOLY SLA-lab type
s t a t i o n s w i t h l i f e t i m e l i m i t e d t o 90 days.
A s e r i e s of meetings was h e l d a t NASA Headquarters on t h e I n t e r m e d i a t e
Space S t a t i o n (launched 1973-1974) l e a d i n g up t o a p r e s e n t a t i o n t o
M r . Mathews on June 28, 1968, by MSC, Langley and MSFC. The MSFC p r e s e n t a t i o n was g e n e r a l l y considered t o be o u t s t a n d i n g i n terms of t h e
amount of d a t a g e n e r a t e d i n t h e s h o r t p e r i o d of time allowed. The
Langley group recommended a concept v e r y s i m i l a r t o t h e MORL launched
on t h e I n t e r m e d i a t e 20 (S-IC/S-IVB) and r e s u p p l i e d by S a t u r n I B . MSC
presented t h e i r MOM (Manned O r b i t i n g Module) concept using o n l y
S a t u r n I B f o r launch of t h e s t a t i o n and n e c e s s a r y r e s u p p l y f l i g h t s .
The Marshall s t u d y was much broader i n that f o u r concepts ( i n t e g r a l ,
�h y b r i d , modular, s m a l l / s h o r t d u r a t i o n ) were 'developed, w i t h primary
emphasis being placed on t h e hybrid and modular o p t i o n s . The recomrnendat i o n s from Mathews and Mueller were t o s t r e s s , i n t h e f u t u r e , t h e modular
approach and t o emphasize u s e of t h e I B .
4.
P r e s s u r e Fed Launch Vehicle
A p r e s e n t a t i o n was g i v e n t o M r . Frank Williams on J u l y 9,
1968, on t h e p r e s s u r e - f e d launch v e h i c l e performance t r a d e o f f s ( i . e . ,
r e l a t i v e p r o p e l l a n t l o a d i n g s ) on t h e two- and t h r e e - s t a g e v e h i c l e s .
For t h e t h r e e - s t a g e v e h i c l e , b o t h two and f o u r engines were considered
f o r t h e second s t a g e , and i t s performance a p p e a r s t o be 70 p e r c e n t
t o 90 p e r c e n t h i g h e r t h a n a two-stage v e h i c l e of comparable l i f t o f f
weight.
B
.
As trodynamics and Miss i o n Analys i s Group
1.
Optimum Mu1 t i - I m p u l s e Rendezvous Program
An optimum multi-impulse rendezvous (OMIR) computer program has been o b t a i n e d from t h e Manned Space F l i g h t Center i n Houston.
This program u s e s ~ a w d e n ' s primer v e c t o r concept t o determine t h e
optimum number and t h e l o c a t i o n of t h e impulses. The OMIR program i s
capable of determining optimal three-dimensional rendezvous t r a ject o r i e s r e q u i r i n g a s many a s s i x impulses, under t h e r e s t r i c t i o n of twobody motion.
The OMIR program i s being made compatible w i t h t h e UNIVAC
1108 computer a t t h e MSFC Computation Laboratory.
2.
unmanned P l a n e t a r y S t u d i e s
Langley Research Center l e t f o u r c o n t r a c t s i n March and
A p r i l of t h i s year t o s t u d y powered s p a c e c r a f t , d i r e c t v e r s u s i n d i r e c t
m i s s i o n modes f o r t h e Mars l a n d e r c a p s u l e , and hard and s o f t l a n d e r s
f o r t h e 1973 Mars mission. The c o n t r a c t s were
(a)
Mars S o f t Lander Capsule Study, McDonnell-Douglas
C o r p o r a t i o n , $91K, 3 months, f i n a l p r e s e n t a t i o n
June 25, 1968, COR, M r . Chuck I n g l e s , LRC.
(b)
Study of Powered S p a c e c r a f t f o r Mars Missions, The
Boeing Company, $93K, 3 months, f i n a l p r e s e n t a t i o n
June 26, 1968, COR M r . Canady, LRC.
(c)
Study of D i r e c t v e r s u s O r b i t a l E n t r y f o r Mars Miss i o n s ,
M a r t i n M a r i e t t a Corporation, $loOK, 3 months, f i n a l
p r e s e n t a t i o n J u l y 1, 1968, COR, M r . Dan Snow, LRC.
�(d)
Mars Hard Lander Capsule Study, General E l e c t r i c
Company, @4K, 3 months, f i n a l p r e s e n t a t i o n J u l y 30-31,
COR, M r . Bob Smith, LRC.
M r . Bobby E l l i s o n , from t h i s o f f i c e , a t t e n d e d t h e f i n a l p r e s e n t a t i o n on
(a) and (d) above. These a r e r e p o r t e d i n t r i p r e p o r t s , R-AERO-X-28-68
and i n t h e P l a n e t a r y Working Group.
3.
P l a n e t a r y Nuclear Mission Parameter Study
TRW gave a p r e s e n t a t i o n J u l y 24 on t h e i r p l a n e t a r y n u c l e a r
m i s s i o n parameter s t u d y , NAS8-5371. Mars o r b i t a l c a p t u r e - l a n d e r m i s s i o n s
and a Venus o r b i t a l c a p t u r e m i s s i o n were s t u d i e d d u r i n g t h e 1980-93 time
period.
I n i t i a l v e h i c l e weight was optimized w i t h r e s p e c t t o v a r i o u s
parameters. These included t r a j e c t o r y types and launch o p p o r t u n i t i e s ,
v e h i c l e con£ i g u r a t i o n s , p l a n e t a r y s t o p o v e r t i m e s , engine t h r u s t l e v e l s ,
n u c l e a r engine a f t e r c o o l i n g , e l l i p t i c a l parking o r b i t s a t t a r g e t p l a n e t ,
and e a r t h launch window d u r a t i o n . The use of e l l i p t i c a l parking o r b i t s
a t t h e t a r g e t p l a n e t was found t o produce v e h i c l e weight s a v i n g of up
t o 30 p e r c e n t over t h a t r e q u i r e d f o r c i r c u l a r parking o r b i t s . Also,
by t h r u s t i n g d u r i n g a f t e r c o o l i n g , a 6 p e r c e n t weight s a v i n g was o b t a i n e d .
Published r e s u l t s of t h i s s t u d y w i l l be a v a i l a b l e i n one month.
F u r t h e r a n a l y s e s were recommended i n t h e a r e a s of e l l i p t i c a l
parking o r b i t s a t e a r t h :
t h e employment of m u l t i p l e burns f o r e j e c t i o n
from parking o r b i t s and t h e a s s o c i a t e d r a d i a t i o n s h i e l d i n g p e n a l t i e s
f o r r e p e t i t i v e passes through t h e Van A l l e n b e l t , launch window d u r a t i o n
f o r d e p a r t u r e from t h e t a r g e t p l a n e t , and o p e r a t i o n a l d i f f i c u l t i e s
involved i n t h e r e s t a r t and a f t e r c o o l ing of t h e n u c l e a r e n g i n e s .
C.
System Analysis Group
The a n a l y s i s i s s t i l l i n p r o g r e s s t o determine t h e i m p l i c a t i o n s
of c o n v e r t i n g t h e AS-210 S-IVB t o a S a t u r n V launched m i s s i o n w h i l e
r e t a i n i n g i t s S a t u r n I Workshop backup s t a t u s . The p r e l i m i n a r y r e s u l t s
of t h e MDC/MSFC s t u d y i n d i c a t e t h a t t h e conversion t o a S a t u r n V Workshop i s f e a s i b l e , r e l a t i v e l y s i m p l e , inexpensive, and a c h i e v a b l e s o a s
t o c l o s e l y f o l l o w t h e S a t u r n I Workshop. Out of s e v e r a l approach o p t i o n s ,
t h e " s e l e c t e d " conversion p l a n (based on t h e r e l e a s e of AS-210 a t KSC)
can be c a r r i e d o u t a t KSC i n 9 months from workshop r e l e a s e t o launch.
�PROJECTS OFFICE
111,
1.
AS-205 DCR Meeting
On June 5 and 6, 1968, t h e AS-205 DCR Board met a t KSC.
Launch Complex 34 and 39 were d i s c u s s e d d u r i n g t h e f i r s t day and h a l f .
On t h e a f t e r n o o n of June 6, 1968, t h e AS-205 l a n d , l a n d i n g problem was
d i s c u s s e d by MSFC. These items a r e b r i e f l y summarized below:
M r . Huss, MSC, p r e s e n t e d t h e GO/NO-GO launch procedure t o
avoid land l a n d i n g . There a r e t h r e e d e c i s i o n s involved, which a r e
(1) pickup count, (2) crew i n g r e s s , and (3) launch. A l l t h r e e d e c i s i o n s w i l l be based on wind monitoring s i m u l a t i o n s a t MSC. The f i r s t
two w i l l s i m u l a t e pad a b o r t which can w i t h s t a n d a wind from t h e e a s t
25 f t / s e c . The d e c i s i o n whether o r n o t t o launch w i l l be based
of
on s i m u l a t i o n covering t h e f i r s t 15 seconds of f l i g h t . As a r u l e of
thumb, a n a v e r a g e wind component f o r a l t i t u d e s of 0 t o 7,000 f e e t of
1 f t / s e c o r g r e a t e r from 72" e a s t of n o r t h w i l l y i e l d p r e d i c t i o n of
land impact. D e c i s i o n (1) w i l l be based on e s t i m a t e d winds 12-24 hours
b e f o r e launch, whereas d e c i s i o n s (2) and (3) w i l l b e based on measured
winds. For September, t h e r e i s x 90 p e r c e n t p r o b a b i l i t y o f crew i n g r e s s
w i t h a launch p r o b a b i l i t y of 25 t o 35 p e r c e n t i f t h e winds a r e indeed
r e s t r i c t e d t o avoid land landing. The MSFC and MSC p r o b a b i l i t y c a l c u l a t i o n s a r e i n agreement.
-
MSC a l s o p r e s e n t e d t h e AS-205 launch escape v e h i c l e , LEV a b o r t
performance. P r e v i o u s l y t h e manual a b o r t l i m i t s of 3 d e g / s e c a t t i t u d e
r a t e and 5 degrees a t t i t u d e e r r o r i n p i t c h and yaw have been employed
due t o LEV c a p a b i l i t y . However, a s t r o n g push w i t h i n MSC has r e s u l t e d
i n t h e e l i m i n a t i o n of t h e manual l i m i t s . The a u t o m a t i c a b o r t l i m i t
of 5 d e g / s e c i s s t i l l v a l i d and w i l l c a t c h t h e i d e n t i f i e d f a i l u r e s
r e q u i r i n g near-pad a b o r t . An e a r l y l o s s of p l a t f o r m w i l l r e s u l t i n t h
v e h i c l e ' s f a i l i n g t o p i t c h , t h u s , f l y i n g v e r t i c a l l y . For t h i s f a i l u r e
5
and i f
t h e range s a f e t y o f f i c e r w i l l a b o r t t h e f l i g h t a t ~ 5 seconds,
t h e wind r e s t r i c t i o n s t o a v o i d land l a n d i n g d u r i n g t h e f i r s t 15 seconl
i s a p p l i e d , t h e c a s e w i l l n o t r e s u l t i n l a n d i n g on l a n d . Of c o u r s e ,
tower c o l l i s i o n should occur and r e q u i r e a b o r t , l a n d impact i s q u e s t i
a b l e . MSC summarized t h e land- and w a t e r - l a n d i n g c a p a b i l i t y , which .
b e i n g updated f o r t h e h e a v i e r SIC. The land-landing t e s t s have show
t h a t t h e AS-205 primary s t r u c t u r e w i l l s u r v i v e ; however, t h e i n t e r n a
s p a c e c r a f t damage t o t h e RCS t a n k s , couch f o o t r e s t r a i n t , honeycomb
s t r u t s , and secondary s t r u c t u r e i s unknown. M r . Hagood i n t r o d u c e d .
AS-205 f l i g h t mechanics EDS summary, g i v i n g t h e purpose, t h e gound
and c o n s t r a i n t s , and t h e method used i n determining t h e l i m i t s .
M r . Swider, CCSD, p r e s e n t e d t h e r e s u l t s of t h e f a i l u r e mode simular
and summarized t h e AS-205 a u t o m a t i c and manual l i m i t s . The r e q u i r
f o r t h e Q-ball s e n s o r w a s questioned s i n c e t h e AS-205 a n a l y s i s sho
�t h a t one a c t u a t o r hardover i s t h e o n l y f a i l u r e where t h e Q-ball (qa)
i n d i c a t i o n i s a cue, and i t i s followed c l o s e l y by t h e o v e r r a t e s e n s o r .
An a c t i o n item w a s a s s i g n e d t o determine t h e requirement f o r t h e Q-ball
on S a t u r n I B .
2.
Twelfth FLSP Meeting
The 1 2 t h F l i g h t Limits Sub-panel Meeting was h e l d a t MSFC
on June 5 , 1968. The AS-205 LEV l i m i t s and procedure f o r GO/NO-GO
launch d e c i s i o n t o a v o i d land impact were d i s c u s s e d . Other items
covered a r e a s f o l l o w s :
-
Analyses a r e i n p r o g r e s s t o d e t e r S a t u r n V LEV Limits
mine i f manual a b o r t l i m i t s a r e a p p l i c a b l e f o r n e a r pad. MSC i s
determining whether o r n o t the max a l i m i t f o r max q can be i n c r e a s e d .
It a p p e a r s t h a t t h e b o l t s which a t t a c h t h e tower t o t h e CM w i l l be t h e
r e s t r i c t i n g item.
-
The AS-503 launch v e h i c l e f l i g h t
S a t u r n V, AS-503
mechanics EDS a n a l y s i s has been published. MSFC p o i n t e d o u t t h a t t h e
S-IC outboard engines c a n t of = 2 degrees t o h e l p a l l e v i a t e t h e S / C
l o a d s f o r one engine o u t w i l l be on AS-503.
The backup t o t h e p l a t f o r m
f a i l u r e w i l l n o t be implemented on S a t u r n I B o r V. On S a t u r n V, t h e
d i s p l a y f o r p l a t f o r m f a i l u r e i s being modified such t h a t b o t h t h e
guidance f a i l l i g h t ( p l a t f o r m f a i l u r e ) and t h e o v e r r a t e 1i g h t w i l l
i n d i c a t e a p l a t f o r m f a i l u r e . This provides redundance and t h e two
cues a r e a v a i l a b l e f o r crew t o abort: i f t h e f a i l u r e o c c u r s i n max q.
review.
-
The FLSP EDS r e p o r t f o r AS-205 i n f i n a l
Documentation
Plans a r e t o b e g i n t h e AS-503 r e p o r t i n mid-August.
-
During t h e AS-205 Launch Vehicle DCR,
APS F a i l u r e
D r . Mueller asked i f t h e S-IVB could f l y w i t h one APS i n o p e r a t i v e .
Analyses show t h a t , f o r t h e b o o s t phase, r o l l c o n t r o l i s maintained
f o r one APS i n o p e r a t i v e . Analyses a l s o show t h a t , f o r t h e b o o s t phase,
r o l l c o n t r o l i s maintained f o r one APS module f a i l u r e ; however, f o r t h e
o r b i t a l phase,one module f a i l u r e r e s u l t s i n l o s s of c o n t r o l of t h e
vehicle.
-
MSC i s proposing a m i s s i o n r u l e t o r e t a i n
LET J e t t i s o n
t h e launch escape tower (LET) p a s t nominal j e t t i s o n time i f Mode I1
a b o r t (SM a b o r t ) i s n o t achieved. This was d i s c u s s e d d u r i n g t h e meeti n g and R-AERO/R-ASTR a n a l y s e s show t h a t t h e v e h i c l e goes u n s t a b l e i f
22 seconds
t h e LET is h e l d p a s t t h e S-IVB g a i n change, which o c c u r s
a f t e r nominal j e t t i s o n .
The m i s s i o n r u l e w i l l be modified t o r e f l e c t
our r e s u l t s . The minutes of t h e meeting a r e being documented.
-
�3.
J-2S Study
Study p l a n s , ground r u l e s , and s e l e c t i o n of m i s s i o n prof i l e s have been accomplished. The s e l e c t e d s t u d y m i s s i o n p r o f i l e s
i n c l u d e a b a s i c LOR miss i o n , synchronous, two-s t a g e low e a r t h o r b i t ,
and a 100 n.mi. p o l a r o r b i t . Nominal t r a j e c t o r i e s have been g e n e r a t e d
f o r t h e s e s t u d y m i s s i o n p r o f i l e s . The f o l l o w i n g p r e l i m i n a r y d e s i g n
c r i t e r i a have been t r a n s m i t t e d t o t h e s e v e r a l c o n t r a c t o r s : J-2s engine
exhaust plume c h a r a c t e r i s t i c s , S - I 1 b a s e h e a t i n g environment, aerodynamic
h e a t i n g environment, on-pad and i n - f l i g h t a c o u s t i c environment, and
s t a t i c aerodynamic and l o a d d i s t r i b u t i o n c h a r a c t e r i s t i c s .
4.
Plume Contamination T e s t i n g
A plume contamination t e s t i n g program f o r t h e AAP C l u s t e r
has been planned d u r i n g t h i s p e r i o d i n response t o a r e q u e s t from
R-P&VE. R-AERO-AT c o n t a c t e d t h e A i r Force and MSC t o determine t h e
e x t e n t of contamination t e s t i n g done i n t h e p a s t and planned f o r t h e
f u t u r e . The A i r Force i s p r e s e n t l y t e s t i n g a t AEDC t o determine t h e
contamination of t h e MDL by plume c o n s t i t u e n t s , and R-AERO-AT has cons i d e r e d t h i s t e s t i n g i n t h e t e s t p l a n . The p r e l i m i n a r y t e s t p l a n i s
b e i n g e v a l u a t e d by R-P&VE and on August 2, 1968, a meeting has been
scheduled t o determine t h e a v a i l a b i l i t y of funds.
5.
AAP C l u s t e r
Work continued d u r i n g June and July on t h e C l u s t e r Mission
w i t h primary emphasis on t h e unmanned rendezvous a n a l y s e s f o r AAP-4, t h e
e a r t h r e s o u r c e s experiments c o m p a t i b i l i t y f o r AAP-1/2, and performance
improvement f o r AAP-2 t o overcome a growing payload weight/performance
problem. E f f o r t t o d a t e i n d i c a t e s t h a t t h e h y b r i d s t a b l e o r b i t technique
i s b e s t f o r t h e unmanned rendezvous of AAP-4.
Studies indicate t h a t the
use of a second burn i n t h e AAP-4 rendezvous scheme i s n o t a t t r a c t i v e .
R e s u l t s of t h e e a r t h r e s o u r c e s experiments c o m p a t i b i l i t y a n a l y s e s t o
d a t e i n d i c a t e t h a t t h e experiments can b e packaged and t i m e l i n e d on t h e
AAP-1/2 m i s s i o n . However, t h e a d d i t i o n a l weight involved (about a 1,000
pounds) p l a c e s t h e AAP-2 i n a n e x c e s s i v e l y overweight c o n d i t i o n .
Some of t h e performance impzovements b e i n g i n v e s t i g a t e d
f o r AAP-2 i n c l u d e t h e u s e of t h e CSM RCS system t o b o o s t t h e AAP-2 t o
h i g h e r a l t i t u d e , t h e r e b y reducing t h e r e q u i r e d i n s e r t i o n a l t i t u d e f o r
AAP-2, use of a h i g h e r performance 3-2 e n g i n e i n t h e OWS S-IVB s t a g e and
i n s e r t i o n of t h e AAP-2 a t p e r i g e e w i t h a c o a s t t o apogee f o r t h e p a s s i v a t i o n impulse t o c i r c u l a r i z e t h e o r b i t r a t h e r t h a n t h e p r e s e n t l y b a s e l i n e d
apogee i n s e r t i o n w i t h immediate pass i v a t i o n . Another performance improvement that w i l l be i n v e s t i g a t e d , a s mentioned a t t h e B a s e l i n e Review Meeting a t MSFC on J u l y 23 and 24, 1968, i s t h e concept of p l a c i n g t h e AAP-2
i n t o a n e l l i p t i c a l o r b i t . R e s u l t s of t h i s i n v e s t i g a t i o n w i l l be r e p o r t e d
a t a l a t e r date.
�IV.
AEROSPACE ENVIRONMENT DIVISION
A.
Environment Research Off i c e
1. During t h i s r e p o r t i n g p e r i o d , 45 rawin f l i g h t s were made
by t h e MSFC Atmospheric Research F a c i l i t y i n s u p p o r t of s t a t i c t e s t s
a t t h e T e s t Laboratory. S t a t i c t e s t s of t h e F-1 engine r e q u i r e d
34 f l i g h t s . Eleven f l i g h t s were r e q u i r e d f o r t h e two s t a t i c t e s t s of
t h e S-IC b o o s t e r .
2. The CPS-9 weather r a d a r was placed back i n o p e r a t i o n , and
d a t a f o r t h e R-AERO-YE thunders torm s t u d y a r e being a c q u i r e d . S e v e r a l
of t h e Aerovane Anemometers have been s e r v i c e d i n s u p p o r t of t h i s s t u d y
and d a t a have been recorded f o r t h e s t u d y .
3. A s e r i e s of t e s t s w i t h f o u r Climet cup-type anemometers
was conducted i n t h e Dynamic Wind F a c i l i t y . Other t e s t s were conducted
l s i n g t h e Reed-ball anemometer, b u t because of t h e h i g h t h r e s h o l d of
t h e i n s t r u m e n t , no u s a b l e d a t a were o b t a i n e d . The Reed-ball anemometer
i s a s t r a i n - g a g e type of i n s t r u m e n t , and t h e b r i d g e c i r c u i t i n t h e u n i t
t e s t e d has a s t a r t i n g t h r e s h o l d of a b o u t 20 m i l e s p e r hour wind speed.
This range of t h r e s h o l d makes t h i s instrument u n d e s i r a b l e f o r r e c o r d i n g
s u r f a c e wind d a t a on a r o u t i n e b a s i s .
4.
NASA's 150-meter M e t e o r o l o g i c a l Tower
a . A l l r e c o r d i n g systems f u n c t i o n e d p r o p e r l y , p r o v i d i n g
continuous wind, temperature, dew p o i n t , p r e s s u r e , and r e l a t i v e humidity
data
.
b.
being recorded.
The s o l a r r a d i a t i o n gage was i n s t a l l e d and d a t a a r e now
c . Two a u t o m a t i c r a i n gages which have been shipped t o
t h e tower w i l l be i n s t a l l e d some time i n August.
d. The wind d i r e c t i o n s e l e c t o r i s being r e d e s i g n e d . The
d e s i g n has been completed and r e q u i r e d p a r t s f o r f a b r i c a t i o n ordered.
The new s e l e c t o r should be ready by t h e f i r s t of November.
e . A complete updated s e t of schematics f o r a l l systems
on t h e tower was compiled and w i l l be added t o t h e Tower Operations
Manua 1
.
f . A 35 mm camera mounted a t t h e 30-meter l e v e l w i l l r e c o r d
d a t a of thunderstorm a c t i v i t y i n t h e Cape a r e a .
�B.
Atmospheric Dynamics Branch
1.
Jimsphere Temperature Sensor (NAS8-20588)
The Jimsphere temperature s e n s o r peogram i s on schedule.
P r e p a r a t i o n s a r e being made t o f i e l d t e s t the s e n s o r a t Wallops I s l a n d ,
V i r g i n i a , d u r i n g t h e f i r s t p a r t of September 1968. Some m o d i f i c a t i o n s
have been made t o t h e e l e c t r o n i c package of t h e s e n s o r t o o b t a i n a
more s t a b l e o u t p u t s i g n a l and t o reduce t h e weight of t h e balloon-borne
s y s tem. An a r t i c l e on t h e temperature s e n s o r and t h e l a s t f i e l d t e s t s
made a t Cape Kennedy has been a c c e p t e d by t h e J o u r n a l of Applied
Meteorology, s u b j e c t t o some c o r r e c t i o n s being made i n t h e a r t i c l e .
The a r t i c l e should be published i n t h e near f u t u r e .
2.
Toxic Fuel D i f f u s i o n F o r e c a s t Handbook
N e g o t i a t i o n s a r e i n p r o g r e s s on t h e proposed c o n t r a c t under
DCN1-8-75-00103 e n t i t l e d , "Development of Toxic Fuel D i f f u s i o n F o r e c a s t
Handbook."
This s t u d y w i l l use s e v e r a l s o u r c e s of m e t e o r o l o g i c a l d a t a
from t h e Cape Kennedy a r e a t o develop a n atmospheric d i f f u s i o n model
which can e f f e c t i v e l y p r e d i c t down-wind c o n c e n t r a t i o n s of gaseous
exhaust m a t e r i a l s r e l e a s e d d u r i n g a normal launch o r due t o a c o n f l a g r a tion.
3.
Jimsphere Turbulence Program
The Jimsphere program being performed a t Wallops I s l a n d ,
V i r g i n i a , is c o n t i n u i n g t o be used t o s u p p o r t t h e l a s e r r a d a r l a t m o s p h e r i c t u r b u l e n c e d e t e c t i o n program being conducted by D r . J . D.
Lawrence, Jr., and M r . Steward O c h e l t r e e , of LRC. The LRC p e r s o n n e l
have i n d i c a t e d t h a t t h e Jimsphere wind d a t a a r e of g r e a t v a l u e t o them
i n t h e i r i n v e s t i g a t i o n of atmospheric t u r b u l e n c e . The Jimsphere d a t a
w i l l be used t o provide a n i n d i c a t i o n of p o s s i b l e t u r b u l e n t r e g i o n s of
t h e atmosphere. The d a t a from t h e s e r e g i o n s w i l l t h e n be c o r r e l a t e d
w i t h survey a i r c r a f t response d a t a and l a s e r r a d a r r e t u r n s . D r . Lawrence
and M r . O r c h e l t r e e p l a n t o v i s i t MSFC/R-AERO-Y p o s s i b l y i n August 1968
t o d i s c u s s t h e program.
4.
Automatic Data Process f o r NASA's M e t e o r o l o g i c a l Tower
Plans a r e being made t o a c q u i r e a n a u t o m a t i c d a t a p r o c e s s o r
f o r NASA'S 150 meter m e t e o r o l o g i c a l tower. The p r o c e s s o r w i l l e l i m i n a t e
t h e need t o reduce t h e m e t e o r o l o g i c a l d a t a by manual means. The manual
r e d u c t i o n is now being done under a c r o s s s e r v i c e c o n t r a c t w i t h t h e
N a t i o n a l Weather Records Center of A s h v i l l e , North C a r o l i n a .
�C.
T e r r e s t r i a l Environment Branch
1. A r e p o r t , "Frequency D i s t r i b u t i o n of S o l a r R a d i a t i o n a t
A p a l a c h i c o l a , F l o r i d a , and Santa Maria, C a l i f o r n i a , " by Glenn E.
Daniels has been prepared f o r p u b l i c a t i o n i n t h e n e x t Research Review.
2. A r e p o r t , " T e r r e s t r i a l Environment ( C l i m a t i c ) C r i t e r i a
Guidelines f o r Use i n Space Vehicle Development, 1968 Revision," by
Glenn E. D a n i e l s , e t a l . , i s being published.
3.
Chrysler
-
Heating
-
In-House
The problem of c o n s t r u c t i n g r e a l i s t i c thermodynamic atmosp h e r i c models s u i t a b l e f o r e s t a b l i s h i n g maximum and minimum d e s i g n and
o p e r a t i o n a l c o n d i t i o n s f o r S a t u r n Launch Vehicles was d i s c u s s e d w i t h
Chrysler C o r p o r a t i o n Space D i v i s i o n r e p r e s e n t a t i v e s d u r i n g a meeting
a t MSFC on June 25, 1968. The p r e s e n t r e f e r e n c e atmospheres a r e s u i t a b l e f o r nominal c o n d i t i o n s , b u t t h e r e i s no "standard" atmosphere f o r
maximum and minimum c o n d i t i o n s . For example, t h e r e i s no s t a n d a r d
r e a l i s t i c atmosphere a v a i l a b l e f o r maximum aerodynamic h e a t i n g a n a l y s e s .
A 1 though t h e C h r y s l e r r e p r e s e n t a t i v e s a t t h e meeting i n d i c a t e d t h a t t h i s
work could be done w i t h i n t h e p r e s e n t c o n t r a c t , i t now a p p e a r s t h a t a
s p e c i a l s t u d y may be r e q u i r e d .
4.
World-Wide Cloud Cover (In-House)
O r i g i n a l l y , p r o b a b i l i t y d i s t r i b u t i o n s of world-wide cloud
cover were prepared f o r a r e a s approximately 60 NM i n diameter w i t h cond i t i o n a l d i s t r i b u t i o n s r e p r e s e n t i n g s p a t i a l and temporal cloud condit i o n a l i t y 200 NM away and 24 hours l a t e r . By means of computer programs
completed d u r i n g June and J u l y , i t i s now p o s s i b l e t o
(a)
s c a l e t h e cloud c o n d i t i o n a l i t y f o r times and d i s t a n c e s o t h e r than 24 hours and 200 NM,
(b)
ad j us t t h e s t a t is t i c s f o r d i u r n a l changes, and
(c)
s c a l e t h e p r o b a b i l i t y and c o n d i t i o n a l p r o b a b i l i t y
d i s t r i b u t i o n s f o r enlarged a r e a s i z e s
.
Memos R-AERO-YT-44-68 and R - A E R O - Y T - ~ ~ - concerned
~~,
with
earth-viewing a n a l y s i s over t h e U. S. f o r n a t u r a l r e s o u r c e s experiments,
were d i s t r i b u t e d
.
�5.
A c o u s t i c Wind P r o f i l e Mapping F a c i l i t y
No d a t a were recorded t h i s p e r i o d by t h e A c o u s t i c a l Wind
P r o f i l e Mapping F a c i l i t y a t Cape Kennedy because t h e f a c i l i t y ' s c a b l e
system w a s b e i n g r e f u r b i s h e d . New c a b l e s , b o t h messenger and i n s t r u m e n t a t i o n , were shipped t o t h e Cape f o r i n s t a l l a t i o n by Pan American
personnel.
This r e f u r b i s h m e n t is scheduled t o be completed and operat i o n a l f o r t h e SA-205 launch.
Wind s c r e e n s were purchased and w i l l be used f o r t h e SA-205
launch. These s c r e e n s a r e designed t o reduce wind n o i s e , and p e r m i t
e a s i e r d e f i n i n g of r o c k e t exhaust n o i s e i n d a t a r e d u c t i o n .
6.
NWRC
An i n v e s t i g a t i o n of t h e azimuth v a r i a b i l i t y of t h e Cape
Kennedy h o u r l y peak winds was begun. This s t u d y i s i n s u p p o r t of t h e
r i s k l e v e l s a s s i g n e d t o t h e launch v e h i c l e c r i t i c a l wind l i m i t s .
7.
U n i v e r s i t y of Georgia
-
C o n t r a c t NAS8-11175
The f o u r t e c h n i c a l r e p o r t s l i s t e d below were produced by
t h e U n i v e r s i t y of Georgia d u r i n g June and July:
a.
b
8.
.
"Areas Under t h e Pearson Type I11 Curve."
" P r o b a b i l i t i e s of Sequences of Favorable and Unfavora b l e Launching I n t e r v a l s a t Cape Kennedy."
."
c.
" C u r t a i l e d A t t r i b u t e Sampling
d.
"The Use of Second-Order Markov Chains i n E s t i m a t i n g
P r o b a b i l i t i e s of Sequences of Favorable and Unfavora b l e Days f o r Launching Space Vehicles."
Lockheed Support C o n t r a c t
The launch p r o b a b i l i t y program which p r e v i o u s l y had cons i d e r e d ground winds, max q r e g i o n winds, and a d v e r s e w e a t h e r has been
modified t o t a k e i n t o a c c o u n t t h e near-pad a b o r t c o n s t r a i n t f o r AS-205.
A r e p o r t f o r AS-205 launch p r o b a b i l i t i e s should be ready f o r p u b l i c a t i o n
i n August.
Work i s c o n t i n u i n g on t h e a n a l y t i c a l s t u d y of t h e Cape
Kennedy low l e v e l winds (0-2 km). The f i r s t s t e p w i l l be t o compare
t h e l i n e a r two-dimensional t h e o r y w i t h r e c e n t s t a t i s t i c a l r e s u l t s . As
work p r o g r e s s e s , i t i s a n t i c i p a t e d that more g e n e r a l a n a l y t i c a l models
and a n o n l i n e a r numerical model w i l l be developed and t e s t e d .
�A r e p o r t e n t i t l e d , "The Theory of Exceedances," was cornpleted during t h i s period.
I n t h i s study, the p r o b a b i l i t y t h a t the
mth l a r g e s t of t h e p a s t L o b s e r v a t i o n s w i l l be exceeded k times i n N
f u t u r e t r i a l s i s d e r i v e d . The expected number of exceedances and t h e
v a r i a n c e a r e a l s o found. An i n t e r p o l a t i v e scheme i s p r e s e n t e d f o r
d e f i n i n g p r o b a b i l i t i e s a s s o c i a t e d w i t h v a l u e s n o t a c t u a l l y observed.
This document w i l l be published a s a NASA c o n t r a c t o r r e p o r t .
D.
Space Environment Branch
1.
A c o u s t i c G r a v i t y Wave Study
The 1,000 hours, p l u s , of n i n e frequency d o p p l e r d a t a has
been reduced and i s c u r r e n t l y undergoing p r e l i m i n a r y a n a l y s i s t o i d e n t i f y
i o n o s p h e r i c d i s t u r b a n c e s caused by s t a t i c t e s t f i r i n g s of r o c k e t b o o s t e r s
and thunderstorms. Thus f a r , t h e p i c t u r e remains u n c l e a r as t o t h e propag a t i o n of a c o u s t i c waves t o i o n o s p h e r i c h e i g h t s . There i s some i n d i c a t i o n
that t h e a c o u s t i c waves may, on some days, be r e f l e c t e d by c r i t i c a l l a y e r
b a r o c l i n i c i n s t a b i l i t y caused by mesospheric winds.
It i s becoming
a p p a r e n t t h a t f u r t h e r a n a l y s i s must i n c l u d e t h e e f f e c t s of i n t e r v e n i n g
winds.
2.
Thermal Conduction i n t h e Ionosphere
A s e r i e s of e q u a t i o n s i s being programmed through which
t h e thermal h e a t i n g of t h e upper atmosphere may b e d e r i v e d . The h e a t ing mechanisms b e i n g considered a r e thermal conduction by temperature
g r a d i e n t s , e l a s t i c c o l l i s i o n s , r o t a t i o n a l and v i b r a t i o n a l h e a t i n g , and
f i n e s t r u c t u r e e x c i t a t i o n through i n e l a s t i c c o l l i s i o n s . The d a t a
o b t a i n e d from t h e r e c e n t thermospheric probe s h o t s w i l l be used t o c a l c u l a t e t h e a c t u a l h e a t i n g curve which i n t u r n w i l l b e compared w i t h t h e
t h e o r e t i c a l models.
3.
AFTAC/ITT Phase P a t h Sound Unit
The AFTAC/ITT phase p a t h sounder u n i t w i l l be shipped t o
Marshall Space F l i g h t Center on GBL. The instrument w i l l be l o c a t e d a t
a s i t e c u r r e n t l y b e i n g used by t h e NASAIMSFC C-4 ionosonde. Arrangements
w i l l then be made t o have two e n g i n e e r s from ITT come t o H u n t s v i l l e f o r
two weeks t o b r i n g t h e i n s t r u m e n t t o o p e r a t i o n a l s t a t u s and t o t r a i n a
l o c a l crew of e n g i n e e r s i n t h e o p e r a t i o n and maintenance of t h e s t e p p e d
frequency phase p a t h sounder. This procedure should provide t h e maximum
i n e f f e c t i v e o p e r a t i o n a t a minimum of c o s t . The l o c a l NASA e n g i n e e r t o
have charge of t h e maintenance and o p e r a t i o n of t h e sounder u n i t is
M r . Robert Turner, R-AERO-YT.
�4.
S t u d i e s Related t o t h e S t r u c t u r e and V a r i a b i l i t y of
t h e Upper Atmosphere
S t u d i e s r e l a t e d t o t h e s t r u c t u r e and v a r i a b i l i t y of t h e
upper atmosphere have been d i r e c t e d t o (1) a d e t a i l e d comparison of
atmospheric d e n s i t y that i s o b t a i n e d from s a t e l l i t e drag d a t a t o d e n s i t y
of e x i s t i n g model atmospheres, (2) t h e c o n t i n u a t i o n of t h e a n a l y s i s of
s i x MSFC thermosphere probe d a t a , and ( 3 ) t h e e s t a b l i s h m e n t of environment c r i t e r i a f o r s e v e r a l ATM e n g i n e e r i n g s t u d i e s
.
5.
S a t e l l i t e Drag Determined Density Study
A d e t a i l e d a n a l y s i s of d e n s i t i e s o b t a i n e d from s a t e l l i t e
drag d a t a has been i n i t i a t e d t o provide i n f o r m a t i o n needed f o r t h e
r e f i n e m e n t of t h e MSFC Modified J a c c h i a Model Atmosphere (1967). Prel i m i n a r y r e s u l t s of t h i s a n a l y s i s have provided a technique f o r d i r e c t l y
r e l a t i n g e x o s p h e r i c temperature t o atmospheric d e n s i t y . This t e c h n i q u e ,
which i s n o t l i m i t e d by t h e c o n s t a n t boundary c o n d i t i o n s i n h e r e n t i n t h e
c u r r e n t MSFC model, w i l l be used i n developing a model atmosphere that
i s i n agreement w i t h drag determined d e n s i t i e s a t a l l a l t i t u d e s . Low
a l t i t u d e A i r Force s a t e l l i t e d a t a w i l l provide r e f i n e m e n t s t o t h e lower
p o r t i o n of t h e MSFC model (150 t o 200 km) which w i l l p r o v i d e more a c c u r a t e
i n p u t s t o MSFC s a t e l l i t e l i f e t i m e s t u d i e s
.
6.
Thermosphere Probe Study
Diurnal v a r i a t i o n s of t h e thermosphere have been provided
b y s t u d y of s i x MSFC thermosphere probe d a t a . Numerical techniques
a p p l i e d t o t h e d a t a have r e f i n e d t h e d a t a and enabled a g r e a t e r amount
t o be used. Numerical i n t e g r a t i o n of t h e s e d a t a , coupled w i t h known
s a t e l l i t e d a t a , v i a a d i f f u s i o n technique has g i v e n i n s i g h t i n t o t h e
lower thermosphere v a r i a b i l i t y . I n a d d i t i o n , a second i n t e g r a t i o n
technique i n v o l v i n g a more complex d i f f u s i o n e q u a t i o n i s b e i n g t e s t e d .
Comparison of t h e r e s u l t s of t h e two techniques should y i e l d f u r t h e r
knowledge i n t h i s low thermospheric r e g i o n . A f i r s t r u n look a t t h e
u t i l i z a t i o n of t h e h e a t e q u a t i o n ( a n o t h e r t h e o r e t i c a l approach) coupled
w i t h t h e d a t a , has been made, and the groundwork has been f o r m u l a t e d f o r
i t s a p p l i c a t i o n t o t h i s r e g i o n of t h e atmosphere.
7.
ATM Environment C r i t e r i a
S p e c i f i c environment c r i t e r i a i n p u t s f o r s e v e r a l ATM
e n g i n e e r i n g s t u d i e s have been developed u s i n g t h e MSFC Modified Jacchia
Model Atmosphere (1967).
These i n p u t s c o n s i s t of (1) p r e d i c t i o n s of
t h e time-dens i t y p r o f i l e s t o which t h e ATM w i l l be exposed, ( 2 ) l a t i tude v e r s u s l o n g i t u d e c r o s s s e c t i o n s of d e n s i t y f o r t h e approximate
U P - 2 / U P - 1 launch d a t e , and (3) a n e s t i m a t e of t h e range of d e n s i t y
t o which t h e A'IM w i l l be exposed.
�I n e s t a b 1 i s h i n g ATM environment c r i t e r i a , p r e d i c t e d 81-day
mean s o l a r f l u x v a l u e s a r e o b t a i n e d from t h e MSFC S o l a r Cycle P r e d i c t i o n
Program. A s t a t i s t i c a l s t u d y has been i n i t i a t e d f o r t h e b e s t e s t i m a t e
of t h e d a i l y s o l a r f l u x v a l u e t h a t should be a s s o c i a t e d w i t h t h e p r e d i c t e d 81-day mean v a l u e .
A f i n a l d r a f t of t h e 1968 r e v i s i o n of NASA TM X-53521, "Space
Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development 1967
Revision," has been completed and reviewed by t h e Space Sciences Laboratory.
�V
.
AEROPHYS ICS DIVISION
A.
Mechanical Design Off i c e
1. Request has been made by -AE f o r t h e d e s i g n of models,probe
s u p p o r t and t r a v e r s i n g equipment f o r j e t plume impingement t e s t s i n t h e
IBFF. I n i t i a l t e s t s w i l l involve p r e s s u r e measurements. Following t e s t s
w i l l i n c l u d e b o t h f o r c e and p r e s s u r e measurements.
2 . The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and
their current status.
M o d i f i c a t i o n of Model 327, 14 WT (AU)
Design
P r e s s u r e Model, Water Tower Study , UAH (AU)
Design
M o d i f i c a t i o n of Pneumatic Work Bench (-A)
Design
X-Y-Z P o s i t i o n i n g Device, LDC (-LIE)
Design
Redesign of F l a t P l a t e Protuberance
Design
Heat T r a n s f e r Model L. R. C. 4' WT (AT)
Design
Heated Plenum Chamber LDWT (-AE)
Design
S a t u r n V Force Models, Bent C e n t e r i n g , 14" WT (-AD)
Design
C a l i b r a t i o n Equipment, H. R. E .
Des ign/
Fabrication
(-AE)
5 Component Micro Force Balance L. D . C.
(-AE)
Drafting
4" L. D. P r e s s u r e Model, L. T. V. WT (AD)
Drafting
Sapphire Windows, S. T. S . , 14" WT X-Beam (AE)
Fabrication
Nozzle and Plenum, Laser Beam (-A)
Fabrication
Redesign Survey Probe, 14" WT (AE)
Fabrication
Low Volume Diaphragm C u t t e r , IBFF (-AE)
Fabrication
V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n , 18.75%
P i l o t Model, H. R. E. (-AE)
Fabrication
�V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n , H. R . E .
(-AE)
Fabrication
Tracer M a t e r i a l I n j e c t o r , X-Beam, S. T. S. 14" WT (-A)
Fabrication
Strap-on Force Model, 14" WT (-AD)
Delivered
S a t u r n V P r e s s Model (No. 424), 14" WT (-AD)
De 1i v e r ed
B.
Aerodynamic Des i g n Branch
1.
Saturn I B
a.
AAP-I1 Aerodynamics
S t a t i c aerodynamic c h a r a c t e r i s t i c s were d e f i n e d f o r
t h e AAP-I1 v e h i c l e w i t h t h e proposed payload shroud, which has a 12'30'
frustum r e p l a c i n g t h e 8O58' frustum. S t a t i c s t a b i l i t y and a x i a l f o r c e
d a t a f o r c o n t r o l and t r a j e c t o r y s t u d i e s a r e d e f i n e d f o r a Mach number
range from 0 t o 5 . 0 f o r a n g l e s of a t t a c k from 0' t o 10'.
Distributed
aerodynamic l o a d s , b o t h a x i a l and normal, were d e f i n e d f o r s t r u c t u r a l
a n a l y s i s a t a n g l e s of a t t a c k of 0" t o 10' f o r t h e Mach number range
from 0.8 t o 2.0.
These d a t a were estimated and w i l l be updated when
experimental d a t a become a v a i l a b l e .
b.
f o r the Saturn I B
d u i t s ) . External
tunnel t e s t d a t a ,
i n - f l i g h t venting
pressures f o r the
68-42.
c.
S a t u r n IB/OWS S o l a r Panel Conduit P r e s s u r e s
I n t e r n a l and e x t e r n a l p r e s s u r e bands have been d e f i n e d
O r b i t a l Workshop v e h i c l e s o l a r panels f a i r i n g s (conp r e s s u r e bands, which were determined from MSFC 14-inch
encompass a n a n g l e - o f - a t t a c k range up t o 8 d e g r e e s . An
a n a l y s i s determined t h e maximum and mimimum i n t e r n a l
f a i r i n g . These d a t a a r e being published i n R-AERO-AD-
OWS A l t i t u d e Control System
Aerodynamic loads on t h e workshop a l t i t u d e c o n t r o l system
modules were determined f o r i n p u t i n t o t h e s t r u c t u r a l a n a l y s i s . The
modules a r e mounted on t h e a f t s k i r t of t h e S-IVB s t a g e w i t h a 17'30'
f a i r i n g extending forward on t h e tank s e c t i o n of t h e s t a g e . The e x t e r n a l
p r e s s u r e s over t h e forward f a i r i n g and t h e main body of t h e module were
d e f i n e d over t h e Mach range of 0.8 t o 1.95 f o r a n g l e s of a t t a c k of 0 t o
10". I n t e r n a l p r e s s u r e s f o r t h e nose f a i r i n g were a l s o d e f i n e d a s a
f u n c t i o n of Mach number. Maximum s i d e load was p r e d i c t e d a s a d i s t r i b u t e d
load over t h e module. These d a t a a r e being published i n a n o f f i c e
memorandum, R-AERO-AD-68-42.
�d.
AAP-IT. S t a b i l i t y and Loads T e s t
T e s t s have been scheduled i n t h e MSFC 14-inch TWT t o
d e f i n e t h e s t a t i c s t a b i l i t y , a x i a l f o r c e c h a r a c t e r i s t i c s , and load d i s t r i b u t i o n s f o r t h e AAP-I1 launch v e h i c l e . The nose c o n f i g u r a t i o n of
t h e v e h i c l e i s a m o d i f i c a t i o n of t h e g e n e r a l payload shape used on t h e
AS-203.
Two models, a .75 p e r c e n t s c a l e p r e s s u r e model of t h e upper
s t a g e s e c t i o n of t h e v e h i c l e and a .55 p e r c e n t s c a l e f o r c e model of t h e
t o t a l v e h i c l e c o n f i g u r a t i o n , a r e being f a b r i c a t e d f o r use i n t h e s e t e s t s .
The p r e s s u r e model w i l l be t e s t e d f o r a Mach range of 0.80 t o 2.99 a t
a n g l e s of a t t a c k of from -4" t o +12"; t h e f o r c e model i s t o b e i n v e s t i g a t e d a t Mach numbers ranging from 0.50 t o 4.96 i n a n a n g l e - o f - a t t a c k
range of -4" t o +lo0. These t e s t s a r e t o be completed by mid-August.
e.
AAP D e f i n i t i o n of Plume Flow F i e l d f o r Nose Cone
Ejection
O f f i c e Memorandum R-AERO-AD-68-42 p r e s e n t s t h e r e s u l t s
of a r e v i s e d a n a l y t i c a l a n a l y s i s d e f i n i n g t h e plume flow f i e l d e x p e r i enced by t h e payloads of t h e AAP-2 o r AAP-4 v e h i c l e s d u r i n g nose cone/
SLA e j e c t i o n . This updated a n a l y s i s , which s u p e r s e d e s R-AERO-AD-68-13,
was p r e d i c a t e d by a p o s s i b l e c r i t i c a l aerodynamic load s i t u a t i o n imposed
on t h e LEM of t h e AAP-4 v e h i c l e . The aerodynamic flow f i e l d i s t o be
used i n con j u n c t i o n w i t h nose cone/ SLA e j e c t i o n t r a j e c t o r i e s (R-AERODCC-5-68) f o r d e f i n i t i o n of maximum aerodynamic l o a d s imposed on t h e
exposed v e h i c l e payloads.
2.
Saturn V
a.
A x i a l Force C h a r a c t e r i s t i c s
The aerodynamic a x i a l f o r c e c h a r a c t e r i s t i c s have been
determined f o r AS-503 and subs based on l a r g e model wind t u n n e l t e s t s and
AS-502 f l i g h t b a s e p r e s s u r e measurements. These d a t a a r e p u b l i s h e d i n
A comparison of t h e e f f e c t of scoop
o f f i c e memorandum R-AERO-AD-68-37.
removal on v e h i c l e s t a b i l i t y i s a l s o i n c l u d e d . The e f f e c t s shown a r e
small.
b.
E f f e c t s of F71 Plume Induced Flow S e p a r a t i o n on
Saturn V S t a t i c S t a b i l i t y
The e f f e c t s of flow s e p a r a t i o n on t h e Apollo S a t u r n V
analysis
f i r s t s t a g e aerodynamics a r e p r e s e n t e d i n R - A E R O - A D - ~ ~ - ~ ~ The
.
r e v e a l e d a d e c r e a s e i n normal f o r c e and a forward s h i f t i n c e n t e r of
These d a t a supersede t h o s e p r e s e n t e d i n NASA
p r e s s u r e above Mach 3.0.
TM X-53517 e n t i t l e d " S t a t i c Aerodynamics C h a r a c t e r i s t i c s of t h e ApolloS a t u r n V Vehicle" f o r power-on f l i g h t above Mach 3.0.
�c.
Aerodynamics of Saturn V
+ 5-25
Vehicle
The s t a t i c aerodynamic c h a r a c t e r i s t i c s of t h e Saturn V
J - 2 s v e h i c l e have been published i n o f f i c e memorandum R-Al3RO-A~-68-44.
The l i n e a r aerodynamics, t o t a l and d i s t r i b u t e d , a r e presented f o r Mach
The n o n l i n e a r aeronumbers of 0.9, 1.0, 1.1, 1.2, 1.46, 1.70 and 2.0.
dynamics, t o t a l s and d i s t r i b u t i o n s , a r e presented f o r Mach numbers of
1.2, 1.46, 1.70 and 2.0 a t angles of a t t a c k t o 15". Axial f o r c e t o t a l s
and d i s t r i b u t i o n s a r e a l s o presented. These d a t a a r e t o be used f o r
preliminary s t u d i e s by t h e Boeing Company.
d.
-
Hydrogen Venting Study
Overboard venting of hydrogen i s being considered f o r
t h e S-IVB s t a g e during f i r s t s t a g e f l i g h t f o r both Saturn IB and Saturn V
launch v e h i c l e s . Because experimental d a t a on gas v e n t i n g i s 1imited ,
a n i n v e s t i g a t i o n i s being made t o a s s e s s t h e e f f e c t of v a r i o u s v e n t r a t e s
Concentration l e v e l s w i l l be measured
on downstream c o n c e n t r a t i o n of Hz.
a t d i s t a n c e of 100 h (h = v e n t plume p e n e t r a t i o n h e i g h t ) downstream of a
f l u s h c i r c u l a r v e n t p o r t a t s u p e r s o n i c Mach numbers and s c a l e d flow
It is hoped t h a t t h i s i n v e s t i g a t i o n w i l l proratios (2 preset rate).
v i d e a s e t of d a t a whose range i s broad enough t o cover f u t u r e H2 v e n t ing r a t e s . T e n t a t i v e plans c a l l f o r t e s t i n g i n MSFC f a c i l i t i e s during
t h e next s i x months.
e.
Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n
P r e s s u r e t e s t i n g i n t h e MSFC 14-inch TWT f a c i l i t y of
t h e ogive-cylinder and o g i v e - c y l i n d e r - f r u s t u m - c y l i n d e r c o n f i g u r a t i o n
has been completed. Time delays a s s o c i a t e d w i t h model i n s t a l l a t i o n and
d a t a accuracy r e s u l t e d i n rescheduling t h e flow v i s u a l i z a t i o n p o r t i o n of
t h i s t e s t u n t i l September. The flow v i s u a l i z a t i o n models have been
flash-coated w i t h copper and then oxidized t o provide a b l a c k background
f o r optimum c o n t r a s t i n r e l a t i o n t o t h e white china-clay t h a t i s used t o
i d e n t i f y t h e l o c a l flow c o n d i t i o n . Longitudinal and r a d i a l l i n e s w i l l
be s c r i b e d through t h i s coating i n t o t h e s t e e l model and then they w i l l
be f i l l e d w i t h epoxy t o provide a white g r i d on a b l a c k background t o
a s s i s t i n a c c u r a t e l y measuring changes i n s u r f a c e flow c h a r a c t e r i s t i c s .
Design of t h e 4.0-inch diameter ogive-cylinder p r e s s u r e model t o be
t e s t e d i n t h e LTV 4' HSWT has been completed. Delivery of t h e model
plans t o f a b r i c a t i o n has been delayed, however, because of higher
p r i o r i t y requirements of t h e d r a f t i n g s e c t i o n .
September 1968.
February 1969.
A p r e - t e s t conference is scheduled w i t h LTV f o r
The t e s t d a t e i s t e n t a t i v e l y scheduled f o r January-
�3.
General
S i x t h I n t e r n a t i o n a l Symposium on R a r e f i e d Gas Dynamics
M r . J o s h D. Johnson, R-AERO-ADE, a t t e n d e d t h e S i x t h I n t e r n a t i o n a l Symposium on R a r e f i e d Gas Dynamics which was h e l d a t Massachusetts
I n s t i t u t e of Technology J u l y 22-26, 1968. A t t h i s symposium, approxim a t e l y 180 papers were p r e s e n t e d that d e s c r i b e d t h e o r e t i c a l and e x p e r i mental s t u d i e s t h a t have been performed r e c e n t l y i n r a r e f i e d gas dynamics
A d e t a i l e d t r i p r e p o r t w i l l be d i s t r i b u t e d t o a p p r o p r i a t e people w i t h i n
t h e Aero-Astrodynamics Laboratory.
Experimental Aerophysics Branch
C.
1.
Low D e n s i t y Chamber
The model n o z z l e has been f a b r i c a t e d and d e l i v e r e d f o r t h e
experimental i n v e s t i g a t i o n of j e t plume impingement i n t h e Low D e n s i t y
Chamber. I n i t i a l t e s t s i n measuring t h e impact p r e s s u r e of t h e C02
plume r e v e a l e d d i f f i c u l t i e s i n a l i g n i n g t h e probe and n o z z l e . Hardware
r e f i n e m e n t s a r e now underway.
2.
Impulse Base Flow F a c i l i t y
Blockage t e s t s of t h e 18.75 p e r c e n t p i l o t High Reynolds
Number equipment have been completed, and model s t a t i c p r e s s u r e measuring techniques a r e being s t u d i e d . The primary phases of t h e program
( s t a r t i n g l o a d s , blockage, and pressure-measuring t e c h n i q u e s ) have been
e s s e n t i a l l y completed. Transonic t e s t i n g w i l l b e i n t e r r u p t e d f o r a n
experimental program i n s u p p o r t of AAP/S-IVB Workshop plume impingement
studies
.
The workshop plume impingement program, scheduled t o b e g i n
August 12, 1968, w i l l b e d i v i d e d i n t o 6 p a r t s .
1.
Plume s t u d y (Phase I).
2.
Plume impingement p r e s s u r e on a f l a t p l a t e .
3.
Plume impingement p r e s s u r e on a ' c y l i n d e r .
4.
Plume impingement f o r c e s on a f l a t p l a t e .
5.
Plume s t u d y (Phase 11).
6.
AAPIWorkshop plume impingement f o r c e s .
�(b) An i n v e s t i g a t i o n f o r R-AERO-AU t o determine flow
s e p a r a t i o n c h a r a c t e r i s t i c s on s e v e r a l cone c y l i n d e r - f l a r e models. This
t e s t i s t h e f i r s t phase of a shock-induced s e p a r a t i o n s t u d y t o be p e r formed i n t h e TWT on S a t u r n c o n f i g u r a t i o n s . Visual d a t a were recorded
using o i l - f l o w , c h i n a - c l a y , and shadowgraph flow v i s u a l i z a t i o n t e c h n i q u e s .
T o t a l runs:
64.
( c ) A p r e l i m i n a r y check was made on p o s s i b l e problems
a s s o c i a t e d w i t h a n N2-cooled cone model. The model r e p r e s e n t s a p o r t i o n
of t h e i n v e s t i g a t i o n t o be conducted by C h r y s l e r Space D i v i s i o n f o r
R-AERO-AU, "The E v a l u a t i o n of t h e Acoustic Sources of Background Noise
T o t a l runs:
9.
i n Wind Tunnels
."
(d) An i n v e s t i g a t i o n f o r R-AERO-AD of t h e e f f e c t of
boundary l a y e r on f i n e f f i c i e n c y of a S a t u r n I B Fin. T o t a l r u n s :
41.
The t u n n e l has experienced numerous d e l a y s i n r e c e i v i n g models f o r t e s t ing, r e s u l t i n g i n s h i f t e d schedules and t u n n e l down-time.
The m u f f l e r has been i n s t a l l e d on t h e t u n n e l dump v a l v e a f t e r
a n eight-month d e l a y . The n o i s e r e d u c t i o n has e l i m i n a t e d t h e previous
h e a r i n g hazard. Tunnel-wall a d j u s t i n g jacks were i n s t a l l e d d u r i n g t h i s
p e r i o d t o e n a b l e w a l l a n g l e s t o be s e t e x t e r n a l l y w i t h o u t opening t h e
t u n n e l . This should r e s u l t i n a more e f f i c i e n t system and i n c r e a s e d
run r a t e .
6.
Instrumentation
I n s t r u m e n t a t i o n was provided and o p e r a t e d f o r t h e R-AERO-AU
protuberance t e s t conducted a t t h e AEDC 1 6 - ~ o o tTransonic P r o p u l s i o n
Wind Tunnel. The 122-channel 20KHZ r e c o r d i n g system was used f o r t h e
t e s t . It was a l s o provided, a l o n g w i t h a c o u s t i c t r a n s d u c e r s and o t h e r
equipment, f o r a Lockheed-Sunnyvale a c o u s t i c t e s t i n v o l v i n g t h e upper
s t a g e s of t h e T i t a n . Technical and o p e r a t i n g a s s i s t a n c e was a l s o
provided f o r t h e Lockheed t e s t
.
Magnetic t a p e d u p l i c a t i n g o r "dubbing" has been completed
f o r t h e above t e s t s , a s w e l l a s f o r a n e a r l i e r 4 p e r c e n t S a t u r n V s u p e r s o n i c t e s t conducted a t t h e same f a c i l i t y . The dubbed r e e l s of t a p e
t o t a l e d 132, i n c l u d i n g copies made f o r Lockheed of t h e i r own t a p e s .
7.
Data Reduction
Besides t h e r o u t i n e f a c i l i t y t e s t d a t a , t h e f o r c e t e s t
from
t
h
e
p i l o t HRE from t h e IBFF were reduced and p l o t t e d . A
data
s p e c i a l program was w r i t t e n f o r t h e s e d a t a , u s i n g t h e o n - l i n e p l o t t e r .
This was our f i r s t p r o d u c t i o n a p p l i c a t i o n of t h e p l o t t e r , and i t was
extremely u s e f u l .
�D.
Thermal Environment Branch
1.
High Angle of Attack Heating T e s t
The t e s t runs t o be made i n t h e U n i t a r y P l a n Tunnel have
been completed and t h e model (75 p e r c e n t S a t u r n I B ) moved t o t h e Mach 6
tunnel f o r t h e f i n a l phase. The d a t a a r e now being reduced, and evaluat i o n w i l l begin s h o r t l y . Runs were completed f o r Mach numbers of 2.5
and 3.71 and Reynolds numbers of 1 . 5 x l o 6 and 3.5 x lo6.
2.
R a d i a t i o n View F a c t o r Program
Work was continued toward checking o u t t h e computer program.
S e v e r a l coding changes were made, reducing t h e r u n time by approximately
20 p e r c e n t . Documentation of t h e theory and program was a l s o continued,
and s e v e r a l s e c t i o n s of t h e r e p o r t were r e c e i v e d from t h e c o n t r a c t o r
f o r review.
E.
Unsteady Gas Dynamics Branch
1.
S a t u r n I B Ground Winds
P r e l i m i n a r y s t u d i e s f o r modifying a p r e v i o u s l y c o n s t r u c t e d
S a t u r n I B a e r o e l a s t i c wind t u n n e l model t o s i m u l a t e t h e AAP-2 and AAP-4
c o n f i g u r a t i o n s f o r ground wind s t u d i e s have been completed.
S a t u r n I B wind t u n n e l t e s t d a t a w i l l b e f u r t h e r reduced t o
b e t t e r p r e d i c t f u l l - s c a l e S a t u r n I B bending moments v e r s u s azimuth a n g l e .
2.
S a t u r n V Ground Winds
F a b r i c a t i o n of a n Uprated S a t u r n V ground winds a e r o e l a s t i c
model has been completed by Atkins and M e r r i l l , I n c . Dynamic q u a l i f i c a t i o n t e s t s were r e c e n t l y conducted on t h e model a t t h e company s i t e .
The model and i t s e l e c t r o n i c damper system should be shipped t o MSFC
shortly.
A s t u d y f o r determining t h e second mode e f f e c t s on ground
wind loadings of t h e S a t u r n V f u e l e d weight c o n d i t i o n i s s t i l l i n
progress.
P r e l i m i n a r y p r e d i c t i o n s of s t a t i c and r e s u l t a n t bending
moments v e r s u s azimuth a n g l e f o r t h e S a t u r n V v e h i c l e w i t h t h e LUT and
MSS c o n f i g u r a t i o n f o r t h e c a s e where t h e damper i s a t t a c h e d were
published on June 3 , 1968.
�P r e d i c t i o n s of S a t u r n V, AS-503 bending moments f o r a l l
azimuth a n g l e s u s i n g uprated dynamic c h a r a c t e r i s t i c s f o r t h e manned miss i o n a r e being made f o r a l l weight c o n f i g u r a t i o n s w i t h and w i t h o u t t h e
MSS and a l s o w i t h and w i t h o u t t h e damper a t t a c h e d .
These p r e d i c t i o n s ,
which w i l l s u p e r s e d e t h e p r e l i m i n a r y p r e d i c t i o n s mentioned above, should
be published soon.
Work has a l s o been i n i t i a t e d t o s t a t i s t i c a l l y a n a l y z e e x i s t ing S a t u r n V ground wind t e s t d a t a u s i n g t h e Lockheed-developed s t a t i s t i c a l a n a l y s e s program.
3.
I n f 1i g h t Acoustics
a . The ALOTS f i l m taken from AS-502 has been analyzed f o r
i n v e s t i g a t i o n of t h e r e c i r c u l a t e d flow c o n d i t i o n s on t h e S-IC and S - I 1
s t a g e s . The amplitude and s p e c t r a l i n f o r m a t i o n d e r i v e d from l i m i t e d
a p p l i c a b l e wind t u n n e l d a t a and from t h e f i l m enabled t h e e s t i m a t i o n
of t h e f l u c t u a t i n g p r e s s u r e s on t h e v e h i c l e v e r s u s f l i g h t time. ~ e s u l t ing v e h i c l e l o a d s were d e r i v e d from a n a l y s i s of t h e s e p a r a t e d flow
phenomenon observed d u r i n g f l i g h t and have been r e p o r t e d i n R-AERO-AU
memorandum. Concern f o r t h e s e l o a d s prompted management t o o r d e r a n
i n v e s t i g a t i o n of t h e p o s s i b i l i t y of implementing a measuring program on
AS-503 o r subsequent f l i g h t t o e s t a b l i s h a n a d d u r a t e d e s c r i p t i o n of t h e
phenomenon and t h e r e s u l t i n g l o a d s . The demands of such a program on
AS-503 a r e b e i n g met i n r e g a r d t o t r a n s d u c e r a d a p t a t i o n f o r t h e temperat u r e and frequency o p e r a t i o n a l l i m i t s r e q u i r e d . R-ASTR i s a l s o s t u d y i n g
t h e channel a v a i l a b i l i t i e s a n d / o r a1t e r n a t i v e s t o a c q u i r e d a t a f o r t h i s
area.
b. Comp. Lab. has r e c e n t l y r e p o r t e d that o v e r a l l time
h i s t o r y i n £ o n n a t i o n i s now a v a i l a b l e ( f o r continuous s i g n a l a n a l y s i s )
from t h e a c o u s t i c a n a l y z e r . None of t h e OASPL time h i s t o r y d a t a has
been provided f o r AS-501 o r 502. A s h o r t e r a v e r a g i n g time i s now b e i n g
r e q u e s t e d f o r more a c c u r a t e p r e s e n t a t i o n of c e r t a i n d a t a t y p e s . Output
from Comp. i s expected i n s e v e r a l weeks.
c. A d d i t i o n a l f l u c t u a t i n g p r e s s u r e d a t a have been r e c e i v e d
from Baganoff and A s s o c i a t e s . These d a t a a r e being prepared i n memorandum
form and w i l l b e forwarded t o R-P&VE-S by t h e f i r s t week i n August. The v o l ume of c r o s s power s p e c t r a l d e n s i t y i n f o r m a t i o n t o be forwarded i s v e r y
l a r g e . This r e p r e s e n t s f a i r l y comprehensive, p r e l i m i n a r y r e s u l t s f o r
t h e z e r o a n g l e of a t t a c k c o n d i t i o n .
d. A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l
I n - F l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " i s b e i n g i n i t i a t e d .
Data from Ames f o u r p e r c e n t S a t u r n V, PSTL-1 and PSTL-2 wind t u n n e l
c o n d i t i o n s , and f l i g h t w i l l be used. A l l o t h e r d a t a a v a i l a b l e i n t h e
l i t e r a t u r e w i l l be included.
�e . Requests f o r e s t i m a t e s of i n f l i g h t environments f o r f o u r
s p e c i f i c , modified launch c o n f i g u r a t i o n s have been r e c e i v e d . These conf i g u r a t i o n s involve t h e use of t h e S a t u r n V (J-2s c o n f i g u r a t i o n ) v e h i c l e
and t h e S a t u r n I B b o o s t e r w i t h a Centaur upper 9 t a g e . The environmental
e s t i m a t e s f o r t h e s e c o n f i g u r a t i o n s have been made and forwarded t o t h e
original requestors.
f . A wind t u n n e l program has been conducted i n t h e AEDC
1 6 - f o o t t r a n s o n i c t u n n e l t o provide experimental i n f o r m a t i o n t o h e l p
d e r i v e methods by which f l u c t u a t i n g a i r l o a d s can a c c u r a t e l y be p r e d i c t e d
on launch v e h i c l e s .
This wind tunnel t e s t program i s i n s u p p o r t of a
c o n t r a c t w i t h Wyle L a b o r a t o r i e s , H u n t s v i l l e , e n t i t l e d "Environment Around
Protuberances Submerged i n a Boundary Layer."
The wind t u n n e l t e s t s s t a r t e d on May 23 and l a s t e d
through June 4, 1968. S t a t i c and f l u c t u a t i n g p r e s s u r e s were measured
i n t h e v i c i n i t y of g e n e r a l i z e d protuberance mounted on a s p l i t t e r p l a t e
f o r a Mach number range of M = 0.6 t o M = 1.45. O i l flow s t u d i e s were
conducted a l s o .
A j o i n t MSFCIAir Force wind t u n n e l t e s t program was
conducted from June 4 u n t i l t h e l a s t week i n June. This t e s t program
cons i s ted of s e v e r a l b i c o n i c nose c o n f i g u r a t i o n s which w i l l provide a
bas i s f o r a n a l y s e s of t h e c r o s s c o r r e l a t i o n c h a r a c t e r i s t i c s (necessary
f o r d e s i g n c r i t e r i a ) of t h e i n f l i g h t f l u c t u a t i n g p r e s s u r e environment
f o r v a r i o u s AAP m i s s i o n s . A v e r y s m a l l amount of d a t a from t h e s e t e s t s
has been reduced i n t h e form of a few OASPL's ( o v e r a l l sound p r e s s u r e
l e v e l s ) and a few 113-octave s p e c t r a p r i m a r i l y f o r d a t i n g and e d i t i n g ,
and f o r g u i d e l i n e s f o r planning t h e n e c e s s a r y c r o s s c o r r e l a t i o n d a t a
r e d u c t i o n , which is a much more time-consuming p r o c e s s . C a r e f u l planning
i s r e q u i r e d t o a c h i e v e t h e optimum amount of d e s i g n i n f o r m a t i o n from t h e
tremendous amount of p o s s i b l e d a t a t o be reduced. The A i r Force, v i a
Lockheed, paid f o r t h e i n i t i a l d a t a r e d u c t i o n .
4.
Launch S i t e Acoustics
a. The papers f o r t h e conference on n o i s e a l l e v i a t i o n f o r
s u b s o n i c a i r c r a f t , t o be h e l d a t Langley Research Center i n October 1968,
, a r e being prepared.
The a b s t r a c t s f o r a l l t h e c e n t e r ' s p r e s e n t a t i o n s
have been provided f o r t h e MSFC personnel who a r e involved and i n t e r e s t e d
i n t h i s program. An a d d i t i o n a l paper i s being p r e s e n t e d on t h e "Typical
Response of t h e Human Auditory System" by J . H. Jones.
b. A program f o r t h e d e t e r m i n a t i o n of excess ground a t t e n u a t i o n i n t h e p r o p a g a t i o n of a c o u s t i c energy has been developed and i s
working a t Lockheed f o r some 60 t e s t s (100,000 d a t a p o i n t s ) of l a r g e
b o o s t e r s o r r o c k e t engines a t MSFC from 1965 t o 1967. The m e t e o r o l o g i c a l
d a t a were t o be used i n t h i s program t o b e s t e v a l u a t e t h e d a t a a c q u i s i t i o n
�c o n d i t i o n s and a l s o t o look f o r t h e p o s s i b l e i n f l u e n c e due t o s e v e r a l
parameter v a r i a t i o n s of t h e ground impedance f o r t h i s s t u d y . However,
t h e meteorologYca1 d a t a r e q u e s t e d from R-AERO-YT on May 28, 1968, a r e
n o t y e t a v a i l a b l e f o r use because of Comp. Lab. problems. These problems
may impact t h e t o t a l scope of t h e r e s u l t s f o r t h e p r e s e n t a t i o n t o t h e
conference on Subsonic A i r c r a f t Noise A l l e v i a t i o n a t Langley i n October
1968.
c . The A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t T e s t Lab.
has been e f f e c t i v e l y s h u t down because of t h e manpower s h o r t a g e f o r
o p e r a t i o n a l use. The S a t u r n V model p r e s s u r e amplitude and phase
i n f o r m a t i o n has thus been delayed and i s n o t of s u f f i c i e n t p r i o r i t y
i n T e s t Lab. t o b r i n g a b o u t any t e s t i n g i n t h e immediate f u t u r e . Other
s i m i l a r program have l i k e w i s e ceased.
d. I n i t i a l p r e d i c t i o n of t h e A c o u s t i c Environment f o r t h e
Nuclear Ground T e s t Module has been completed. These environmental
e s t i m a t e s were r e l e a s e d i n memorandum form. A c o u s t i c environments f o r
t h e J-2s n u c l e a r engine c o n f i g u r a t i o n s a l s o have been completed and
have been s u p p l i e d i n a r e c e n t memorandum t o P&VE-SV and o t h e r s .
5.
Panel F l u t t e r
a. I n i t i a l computer runs of t h e low a s p e c t r a t i o panel
f l u t t e r problem have been completed f o r s l e n d e r panels w i t h pinnededge c o n d i t i o n s . These v e r y s u c c e s s f u l runs showed t h a t t h e branch
l i n e s i n t h e K-S p l a n e contained e i t h e r z e r o o r two f l u t t e r p o i n t s .
The n e x t s t e p i s t o s e a r c h i n t h e thickness/dynamic-pressure p l a n e f o r
t h e c r i t i c a l f l u t t e r boundaries.
b. A n a l y s i s of t h e two-dimensional wavy-wall d a t a has
resumed a f t e r some d e l a y due t o c o o r d i n a t i o n problems between MSFC,
ARC and ARAP. Under t h e c u r r e n t agreement, MSFC w i l l provide p r e s s u r e
d i s t r i b u t i o n s on t h e w a l l o b t a i n e d by using l i n e a r i z e d p o t e n t i a l t h e o r y
a s w e l l a s shock wave p a t t e r n s and c o n s t a n t Mach l i n e p a t t e r n s o b t a i n e d
by t h e n o n l i n e a r m e t h o d - o f - c h a r a c t e r i s t i c s s o l u t i o n . I n a d d i t i o n ,
a d d i t i o n a l boundary l a y e r i n f o r m a t i o n i s t o be o b t a i n e d over a f l a t
w a l l i n t h e lower Mach number regime.
c . NASA c o n t r a c t NAS8-21250 e n t i t l e d "High Amplitude
S a t u r n S-IVB Panel F l u t t e r Tests" was i n i t i a t e d June 28, 1968, between
NASA, MSFC and t h e McDonnel-Douglas C o r p o r a t i o n of S t . Louis, M i s s o u r i .
This c o n t r a c t c a l l s f o r t h e McDonnell-Douglas C o r p o r a t i o n t o d e s i g n ,
conduct, and a n a l y z e t h e r e s u l t s of a panel f l u t t e r t e s t t o be conducted
i n t h e Ames 2 x 2 f o o t t r a n s o n i c wind t u n n e l . The primary purpose of
t h i s t e s t i s t o a s s e s s t h e magnitude of f l u t t e r , w i t h r e s p e c t t o dynamic
p r e s s u r e d e f i c i e n c y , on panels s i m i l a r t o t h o s e found on t h e forward
s k i r t of t h e S a t u r n S-IVB s t a g e .
�A t t h e p r e s e n t time, a l l p r e p a r a t i o n s a r e proceeding on
s c h e d u l e , l e a d i n g t o a t a r g e t d a t e of February 1, 1968, f o r t h e wind t u n n e l
test.
d. Boundary l a y e r and p r e s s u r e c o e f f i c i e n t d a t a from t h e
two-dimensional wavy-wall t e s t s have been compiled and e d i t e d on t h e
NASA 7094 computer, and have been forwarded t o ARAP, I n c . , t o be
analyzed under NAS8-21294.
e . S t u d i e s t o determine t h e l i m i t c y c l e behavior of f l u t t e r ing p a n e l s , t a k i n g i n t o account t h e e f f e c t s of i n - p l a n e compressive l o a d s
and d i f f e r e n t i a l p r e s s u r e l o a d i n g s , a r e being continued. The computer
program, developed by P r o f e s s o r E a r l H. Dowell a t P r i n c e t o n u n i v e r s i t y , *
was modified t o c a l c u l a t e t h e r e q u i r e d Bessel f u n c t i o n t o handle a e r o dynamics more completely. The computer program a l s o was extended t o g e t
c a l c u l a t i o n s of l a r g e r v a l u e s of i n p u t d a t a (mode number m = 6, a e r o dynamic d a t a number m = 90, e t c . ) by using t h e a c t u a l d a t a o b t a i n e d from
AS-502.
6.
S t a b i l i t y Derivatives
Two r e p o r t s have been published by Danny D . Liu of Lockheed's
H u n t s v i l l e Research and Engineering Center under NASA C o n t r a c t NAS8-20082:
a . "Quas i - S l e n d e r Body Theory f o r Unsteady L i n e a r i z e d
Transonic Flow P a s t Pointed Bodies of Revolution," (LMSC/HRECA791435)
A p r i l 1968. I n t h i s r e p o r t , t h e l i n e a r i z e d t r a n s o n i c p o t e n t i a l e q u a t i o n
i s solved f o r u s e i n c a l c u l a t i n g t h e unsteady aerodynamic p r e s s u r e s ,
f o r c e s , and moments f o r smooth, pointed r i g i d bodies of r e v o l u t i o n
o s c i l l a t i n g w i t h a s u f f i c i e n t l y h i g h frequency a t a f r e e s t r e a m Mach
number of one. This procedure y i e l d s s t a b i l i t y d e r i v a t i v e s expressed
i n terms of body geometry, reduced frequency and body t h i c k n e s s r a t i o .
S t a b i l i t y d e r i v a t i v e s were c a l c u l a t e d f o r a cone and
a convex p a r a b o l i c ogive y i e l d i n g r e s u l t s t h a t a g r e e q u i t e w e l l w i t h
a v a i l a b l e experimental s t a t i c s t a b i l i t y d a t a .
b. "Some Approximate S o l u t i o n s f o r O s c i l l a t i n g Bodies of
Revolution i n Nonlinear Transonic Flow," LMSC/HREC A791499, June 1968.
This r e p o r t p r e s e n t s low frequency and h i g h frequency "asymptotic" d i p o l e
s o l u t i o n s f o r bodies of r e v o l u t i o n o s c i l l a t i n g i n Mach 1 flow i n closed
form. This i s a n e x t e n s i o n of Oswatitsch and ~ e u n e ' sp a r a b o l i c method
f o r s t e a d y t r a n s o n i c flow.
>c'
Based on n o n l i n e a r p l a t e t h e o r y and f u l l l i n e a r i z e d ( i n v i s c i d , potent i a l ) aerodynamic theory.
�These s o l u t i o n s a r e q u i t e g e n e r a l and a r e o b t a i n e d i n
a form most convenient f o r performing s t a b i l i t y d e r i v a t i v e c a l c u l a t i o n s .
7.
Numerical A n a l y s i s of Unsteady Flow
Work under NASA c o n t r a c t NAS8-18034 w i t h Applied Theory,
I n c . , has been completed and f i n a l r e p o r t s a r e being paepared. Under
t h i s program, e x c e l l e n t r e s u l t s have been achieved u s i n g a f i n i t e d i f f e r e n c e numerical method t o s o l v e unsteady, compressible, v i s c o u s f l u i d
flow problems f o r - b o t h s u b s o n i c and s u p e r s o n i c flow a t s e v e r a l Reynolds
numbers. Of p a r t i c u l a r i n t e r e s t have been s t a t i o n a r y and o s c i l l a t i n g
two-dimensional c y l i n d e r problems; two-dimensional f l a t p l a t e flow, b o t h
w i t h and w i t h o u t boundary l a y e r t r i p s ; and axisymmetric flow over a
forward-facing s t e p .
8.
Quasi-Steady Analysis
The flow v i s u a l i z a t i o n t e s t s i n t h e 14-inch t u n n e l have been
completed, and t h e photographic coverage i s being processed.
F a b r i c a t i o n of t h e shock-induced s e p a r a t i o n model has been
completed, and t h e wind t u n n e l t e s t s w i l l b e g i n a b o u t t h e middle of
September. A new b a l a n c e , designed f o r t h i s t e s t , i s being checked o u t
and c a l i b r a t e d by Lockheed personnel.
VI.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
S c i e n t i f i c Advisory O f f i c e
1.
U n i v e r s i t y of Texas ( C o n t r a c t NAS8-18120)
Objective:
Study of s t a b i l i t y and s e n s i t i v i t y of guidance
systems.
During t h e course of t h i s c o n t r a c t , P r o f . Lyle C l a r k , t h e
p r i n c i p a l i n v e s t i g a t o r , and h i s c o l l e a g u e s and s t u d e n t s have s t u d i e d
t h e problems a s s o c i a t e d w i t h s e n s i t i v i t y and s t a b i l i t y of guidance and
c o n t r o l systems and have published many p a p e r s , i n c l u d i n g f i v e d o c t o r a l
t h e s e s on v a r i o u s a s p e c t s of t h e s e problems. The r e p o r t s r e c e i v e d
during t h i s reporting period include the following t i t l e s :
(1)
An approach t o suboptimal feedback c o n t r o l of nonl i n e a r systems ( t o be published i n t h e I n t e r n a t i o n a l
J o u r n a l of C o n t r o l ) .
(2)
On l i n e a r systems w i t h a g e n e r a l i z e d performance
criteria.
�(3)
On t h e s y n t h e s i s of suboptimal s p a c e c r a f t a t t i t u d e
c o n t r o l s y s tems (Doctoral t h e s i s ) .
(4)
S e n s i t i v i t y of l i n e a r c o n t r o l systems t o l a r g e paramet e r variations.
This l a s t paper gives. a d e f i n i t i o n of s e n s i t i v i t y which r e p r e s e n t s a n
e v o l u t i o n of t h e o r i g i n a l concept a s t h e i n v e s t i g a t o r s s t r o v e t o f i n d
a d e f i n i t i o n t h a t would be b o t h p r a c t i c a l and u s e f u l f o r .guidance and
c o n t r o l s y s tems
.
2.
In-House
E f f o r t s a r e c o n t i n u i n g i n t h e s t u d y of s t o c h a s t i c p r o c e s s e s .
P a r t i c u l a r emphasis is being placed on t r y i n g t o determine t h e c a p a b i l i t y of t h e modern computer i n f i n d i n g a t l e a s t approximate s o l u t i o n s t o
problems i n v o l v i n g t h e s e p r o c e s s e s . To t h i s end t h e van d e r Pol equat i o n ( a n o n l i n e a r second-order d i f f e r e n t i a l e q u a t i o n w i t h a s i n g l e
parameter) was s e l e c t e d f o r s t u d y . Numerical and g r a p h i c a l s o l u t i o n s
were o b t a i n e d f o r s e l e c t e d c o n s t a n t v a l u e s of t h e parameter.
Then s o l u t i o n s of t h e same type were o b t a i n e d as each c o n s t a n t v a l u e of t h e parame t e r was p e r t u r b e d i n a random manner, and t h e s o l u t i o n s were then compared
w i t h t h e unperturbed c a s e s . Work i s now i n p r o g r e s s t o perform t h e same
s o r t of s t u d y f o r h i g h e r o r d e r systems and f o r systems w i t h more t h a n one
parameter.
The o b j e c t of t h e s e s t u d i e s i s t o determine t h e e f f e c t i v e n e s s
of a g i v e n guidance o r c o n t r o l system t o do i t s job, s o t o speak, i n t h e
presence of unknown and, indeed, unknowable random v a r i a t i o n s i n t h e
miss i l e parameters.
(Dearman)
3 . The w r i t i n g up of what could be c a l l e d by a working t i t l e ,
"A C r i t i c a l Survey of Methods and Formulae of C e l e s t i a l Mechanics," has
been continued.
R e c e n t l y included i n c o n s i d e r a t i o n has been t h e method
proposed and p a r t l y e l a b o r a t e d by Groebner and Cap, using L i e s e r i e s .
While t h i s method permits s l i g h t l y more i n s i g h t i n t o t h e b e h a v i o r of
a p a r t from
t h e n o n - a n a l y t i c s o l u t i o n s of t h e n-body problem, i t i s
n o t y e t f i t f o r advantageous numerical a p p l i c a t h e two-body problem
t i o n s . It could n e v e r t h e l e s s be hoped t h a t t h i s method could be adapt6
and augmented f o r a p p l i c a t i o n s t o some s p e c i f i c problems i n c e l e s t i a l
mechanics. To avoid d u p l i c a t i o n of work, t h e a u t h o r s P r o f s . Groebner
and Cap have been c o n t a c t e d i n w r i t i n g .
(Festa)
--
--
�B.
Guidance Theory Branch
1.
Support C o n t r a c t S t u d i e s
a.
General I n t e r p l a n e t a r y S t u d i e s
The e r r o r s i n t h e computer program t o be used f o r t h e
FPR s t u d y (using load r e l i e f c o n t r o l ) have been c o r r e c t e d . A d e t a i l e d
checkout e f f o r t i s planned i n o r d e r t o p l a c e t h e program i n a product i o n s t a t u s i n t h e n e x t few weeks. This ef f o r t i s being c a r r i e d on a
low p r i o r i t y b a s i s .
The Guidance System E r r o r Study (GSES) computer program
has been used t o e s t a b 1 i s h covariance m a t r i c e s a t v a r i o u s p o i n t s b e f o r e
i n c l u d i n g t h e i n j e c t i o n p o i n t f o r a n E a r t h - to-Mars t r a j e c t o r y . The
covariance m a t r i c e s w i l l be used i n mid-course guidance and o r b i t
i n s e r t i o n guidance s tud i e s
.
b.
Optimum O r b i t Trim Analyses
This s t u d y was completed d u r i n g t h i s r e p o r t i n g p e r i o d
and t h e r e s u l t s have been p u b l i s h e d .
c.
Optimal Guidance Study
The a n a l y t i c a l and programming d i f f i c u l t i e g mentioned
d u r i n g t h e l a s t r e p o r t i n g p e r i o d have been c o r r e c t e d . A forthcoming
r e p o r t w i l l document t h e s e r e s u l t s , a l o n g w i t h some numerical examples
of burn-coast-burn optimized t r a j e c t o r i e s which have been g e n e r a t e d w i t h
t h e computer program. F u r t h e r e f f o r t s w i l l b e made t o improve and speed
up t h i s computer program s o t h a t i t can be used f o r optimal guidance
s imulation.
d
.
Quas i-Opt i m a l Guidance Study
Progress has been made r e g a r d i n g t h e i n c l u s i o n of t h e
c o n s t r a i n t i n t o t h e QUOTA guidance scheme. The r e s u l t s of t h i s s t u d y
w i l l be documented i n t h e near f u t u r e .
k
2.
Contracts
a.
Lockheed
-
Voyager Terminal Guidance Analysis
A rough d r a f t of t h e f i n a l r e p o r t has been r e c e i v e d .
The f i n a l r e p o r t should b e a v a i l a b l e soon.
�b.
-
IBM
A p p l i c a t i o n of Numerical Methods t o
Extend C a p a b i l i t i e s f o r Optimal Rocket Guidance
During t h i s r e p o r t i n g p e r i o d , i t was determined t h a t
t h e computing a l g o r i t h m w i l l f i t on t h e LVDC and t h a t guidance c y c l e s of
from 10 seconds a t t h e s t a r t t o 2 seconds near the end can be achieved.
Future work w i l l be c o n c e n t r a t e d on c o n t i n u i n g t h e a d a p t a t i o n of OPGUIDE
t o o t h e r types of m i s s i o n s such a s burn-coast-burn o r b i t a l t r a n s f e r and
rendezvous.
.
Lockheed
-
Rendezvous Guidance
I n t e r i m r e p o r t s summarizing t h e e f f o r t s on t h i s cont r a c t have been r e c e i v e d . An o r a l p r e s e n t a t i o n of t h e s e r e s u l t s was
made r e c e n t l y . The f i r s t - b u r n guidance e q u a t i o n s a r e being r e f o r m u l a t e d
u s i n g ~ e v i - ~ i v i t sa 'r e g u l a r i z i n g v a r i a b l e s
Using t h e s e v a r i a b l e s
a l l o w s t h e i n t r o d u c t i o n of n o n - c l a s s i c a l o r b i t a l elements t h a t a r e
d e f i n e d even f o r c i r c u l a r o r b i t s and a r e slowly time-varying.
The
assumptions b a s i c t o t h e f i n a l - b u r n guidance concept a r e more n e a r l y
f u l f i l l e d by i n t r o d u c i n g a n o t h e r burn phase n e a r t h e end of c o a s t .
S i m u l a t i o n s t u d i e s a r e being performed u s i n g t h i s t h i r d burn.
.
3.
In-House S t u d i e s
Some time was s p e n t d u r i n g t h i s r e p o r t i n g p e r i o d s t u d y i n g
t h e LVDC s c a l i n g problem.
It was decided t h a t a convenient way of
s c a l i n g would be t o change t h e u n i t s of measurement. A new u n i t of
l e n g t h , time and mass can be d e f i n e d such t h a t t h e n a v i g a t i o n and
guidance e q u a t i o n s a r e s c a l e d (normalized) t o p r e v e n t overflow. The
new u n i t s a r e o b t a i n e d by s e t t i n g t h e g r a v i t a t i o n a l c o n s t a n t equal t o
1, by s c a l i n g t h e l e n g t h by t h e r a d i u s of t h e e a r t h , and by s c a l i n g
the mass by t h e i n i t i a l mass of t h e v e h i c l e .
The QUOTA guidance scheme has been improved by updating
With t h e updated
t h e time d e r i v a t i v e s of t h e Lagrange m u l t i p l i e r s .
X's QUOTA has s u c c e s s f u l l y flosm m i s s i o n s ( n u c l e a r s t a g e ) w i t h burn
a r c s of 95 degrees w i t h a l o s s i n payload of l e s s than . O 1 p e r c e n t .
A new approach t o t h e Apollo t a r g e t i n g problem i s b e i n g
attempted. The problem i s being formulated s u c h that t h e guidance
scheme (QUOTA) i s o l a t e s on c o n d i t i o n s near t h e moon1s s p h e r e of i n f l u ence. This i s accomplished by adding a closed form s o l u t i o n f o r t h e
c o a s t phase t o t h e QUOTA guidance package. One advantage of t h i s
approach, i n a d d i t i o n t o t h e f a c t t h a t t h e t a r g e t i n g and guidance
problems have been combined, i s t h a t t h e s p e c i f i e d c o n d i t i o n s i n
l u n a r space a r e not' l i m i t e d t o R and t a s i n Lambertls problem.
�The two-impulse rendezvous problem has been formulated a s
a n o p t i m i z a t i o n problem, and a computer program is being developed which
minimizes t h e sum of t h e AV'S needed a t each end of t h e t r a j e c t o r y .
This program w i l l provide t a r g e t i n g c o n d i t i o n s f o r rendezvous.
C.
O p t i m i z a t i o n Theory Branch
1.
A p p l i c a t i o n of Optimal Control Theory t o CMG Momentum
Dump ing
Optimal c o n t r o l methods a r e being s t u d i e d a s a means of
determining t h e b e s t momentum dumping c o n t r o l subsystem f o r t h e ATM
v e h i c l e . The problem b e i n g i n v e s t i g a t e d i s t h e r e d u c t i o n of t h e accumul a t e d body-axis components of momentum s t o r e d i n t h e t h r e e control-moment
gyros due t o n o n - c y c l i c d i s t u r b a n c e t o r q u e s encountered i n c o n t r o l l i n g
t h e a t t i t u d e of t h e ATM c l u s t e r . The r e d u c t i o n must be accomplished
d u r i n g t h e shadowed p o r t i o n of o r b i t , and i d e a l l y w i l l b e accomplished
s t r i c t l y by maneuvers i n t h e g r a v i t y f i e l d which do n o t r e q u i r e use of
a gas r e a c t i o n system. E f f o r t s have been d i r e c t e d toward f o r m u l a t i n g
t h e problem i n a form which w i l l be amenable t o t h e a p p l i c a t i o n of
optimal c o n t r o l t e c h n i q u e s , cons i s t e n t w i t h t h e p h y s i c a l c o n s t r a i n t s
and n a t u r e of t h e C.M.G. c o n t r o l system.
2.
S t a t i s t i c a l Wind Model
-
Hayes I n t e r n a t i o n a l (NAS8-21444)
-
Objective
C o n s t r u c t i o n of a wind model f o r use i n
s t a t i s t i c a l a n a l y s i s of launch v e h i c l e performance.
The c e n t r a l i d e a of t h i s s t u d y i s t h e development of a
f i l t e r t h a t shapes t h e s t a t i s t i c s of a w h i t e n o i s e i n p u t i n t o t h e b a s i c
s t a t i s t i c s of measured wind and t u r b u l e n c e p r o f i l e s .
The b a s i c t h e o r y
and f e a s i b i l i t y of i t s a p p l i c a t i o n t o v e h i c l e d e s i g n and a n a l y s i s were
demonstrated i n a previous s t u d y . The p r e s e n t work i s aimed toward
using t h e f u l l body of a v a i l a b l e Jimsphere wind soundings t o develop a
h i g h e r o r d e r f i l t e r whose o u t p u t w i l l i n c l u d e a l l important wind and
t u r b u l e n c e f r e q u e n c i e s . Jimsphere sounding d a t a a r e now b e i n g reduced
Concurrently,
and covariances a r e b e i n g computed a t 50 meter i n t e r v a l s .
needed t h e o r e t i c a l work i s being done f o r u t i l i z a t i o n of computed d a t a
when they become a v a i l a b l e .
3.
Minimax Control
a.
General Dynamics/ ~ o n v a i r(NAS8-21454)
Objectives:
(1) To extend t h e c-minimax (minimum peak
v a l u e ) t h e o r y t o determine c-minimax performance i n t h e presence of
�incomplete s p e c i f i e d d i s t u r b a n c e s ; (2) t o determine i f a g e n e r a l a n a l y t i c
s o l u t i o n e x i s t s f o r c-minimax problems f o r l i n e a r dynamical s y s tems w i t h
bounded i n p u t s ; and (3) t o i n v e s t i g a t e t h e computational problems a s s o c i a t e d w i t h t h e c u r r e n t f l o o d i n g technique used t o s o l v e minimax problems.
The c o n t r a c t was signed d u r i n g t h i s r e p o r t i n g p e r i o d ;
no progress r e p o r t s have y e t been r e c e i v e d .
I n i t i a l emphasis w i l l be on
o b j e c t i v e s (2) and (3) i n l i g h t of t h e computational d i f f i c u l t i e s experienced by s u p p o r t c o n t r a c t personnel using t h e c u r r e n t computational
a l g o r i t h m and r e p o r t e d i n t h e April-May p r o g r e s s r e p o r t .
b.
Lockheed Support C o n t r a c t o r S t u d i e s
B a s i c computational d i f f i c u l t i e s i n a p p l y i n g t h e c-minimax theory t o s p a c e c r a f t and launch v e h i c l e models which included
a c t u a t o r dynamics were r e p o r t e d i n t h e April-May p r o g r e s s r e p o r t . The
i n t r o d u c t i o n of s a t u r a t i o n c o n s t r a i n t s on t h e a c t u a t o r k e p t t h e response
from going unbounded, b u t d i f f i c u l t y has been encountered i n f l o o d i n g
t h e s t a t e s p a c e because of t h e tendency of t h e a l g o r i t h m t o keep t h e
a c t u a t o r o p e r a t i n g on o r n e a r i t s s a t u r a t i o n bound.
4.
S t a t i s t i c a l Optimal Control
-
Horieywell (NAS8-21063)
O b j e c t i v e : To i n v e s t i g a t e f u r t h e r t h e a p p l i c a t i o n of t h e
s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206.
D r a f t copies of t h e f i n a l s t u d y r e p o r t and t h e computer
program documentation r e p o r t have been r e c e i v e d and reviewed.
The
reviewers' comments have been r e t u r n e d on t h e f i n a l r e p o r t . The s t u d y
r e s u l t s showed t h e optimum performance a v a i l a b l e and gave i n s i g h t i n t o
t h e optimum behavior of t h e launch v e h i c l e model, which included bending
and s l o s h i n g dynamics. Attempts t o develop a n a l y t i c means of s e l e c t i n g
a s e n s o r complement and f i l t e r s which a r e b e s t i n t h e s e n s e of most
c l o s e l y a c h i e v i n g t h e t h e o r e t i c a l optimum performance were d i s a p p o i n t i n g .
A r e a l i z a b l e system was designed based on t h e optimum ( u n r e a l i z a b l e )
system, b u t t h i s d e s i g n was n o t s o s t r a i g h t f o r w a r d a s would be d e s i r a b l e .
F u t u r e work i n t h i s a r e a would be u s e f u l , a l t h o u g h t h e b e s t approach i s
not yet clear.
The computer program documentation was r e q u e s t e d t o permit
f u r t h e r in-house inves t i g a t i o n s of t h e technique. The program i s c u r r e n t l y r u n on CDC-6600 computer, which uses a b o u t one-half of t h e s t o r a g e
a v a i l a b l e . One o p t i m i z a t i o n - e v a l u a t i o n r u n t a k e s a b o u t 20 minutes f o r
It a p p e a r s
t h e 25th o r d e r time-varying d e s c r i p t i o n of t h e v e h i c l e .
t h a t , on our t h i r d - g e n e r a t i o n equipment, t h e program w i l l r e q u i r e o v e r l a y s
f o r remote o p e r a t i o n and w i l l r e q u i r e 40 t o 100 minutes f o r one complete
run.
�5.
S a t u r n V / ~ p o l l oLoad R e l i e f S t u d i e s
-
Northrop
Rigid body a n a l y s e s a r e n e a r i n g completion. Two c a n d i d a t e
systems n o t considered i n t h e o r ' i g i n a l Boeing s t u d y have shown a s i g n i f ic a n t r e d u c t i o n i n t h e v e h i c l e bending moment and w i l l be considered i n
t h e more complete dynamic a n a l y s i s . An i n t e r i m r e p o r t w i l l be i s s u e d t o
document t h e r e s u l t s of t h e r i g i d body a n a l y s i s .
6.
Parameter Optimization Study f o r ATM
-
Lockheed
A-hybrid s i m u l a t i o n of a s i m p l i f i e d ATM p o i n t i n g system and
o p t i m i z e r c o n t i n u e s i n t h e check-out phase. The o p t i m i z a t i o n package
has been programmed and checked o u t on t h e d i g i t a l p o r t i o n of t h e comp u t e r ; however, t h e v e h i c l e dynamic s i m u l a t i o n on t h e a n a l o g p o r t i o n has
had d i f f i c u l t i e s w i t h s y s tem i n s t a b i l i t i e s
C u r r e n t l y t h e a n a l o g s imulat i o n i s being modified t o match a program r u n s u c c e s s f u l l y by t h e
Lockheed s u p p o r t group.
.
D.
As trodynamics Branch
1.
Broken Plane T r a j e c t o r i e s (Lockheed)
Work was continued on s t u d y and documentation of t h e brokenplane computer program i n use by t h e c o n t r a c t o r . It was determined t h a t
s e v e r a l s m a l l a n g l e approximations had been used i n t h e program which were
n o t a p p l i c a b l e f o r a l l our needs and t h e s e approximations a r e b e i n g
r e p l a c e d w i t h e x a c t f o r m u l a t i o n s . Also, t h e program was o r i g i n a l l y
developed f o r t r a j e c t o r i e s between E a r t h , Venus, and Mars o n l y and i s
being a l t e r e d t o accommodate f l i g h t s t o any of t h e p l a n e t s of t h e s o l a r
s y s tem.
I n a n e f f o r t t o a s c e r t a i n whether broken-plane t r a n s f e r s
could be i n c o r p o r a t e d i n t o t h e c o n s t r u c t i o n of swingby t r a j e c t o r i e s w i t h
any u s e f u l r e s u l t s , p r e l i m i n a r y t r a j e c t o r y c a l c u l a t i o n s were made w i t h
t h e broken-plane program and t h e MAOT (Medium Accuracy O r b i t T r a n s f e r )
c o n i c program. These p r e l i m i n a r y c a l c u l a t i o n s i n d i c a t e t h a t t h e combinat i o n of broken plane and swingby w i l l o f f e r some d e f i n i t e advantage when
one l e g of t h e s t a n d a r d swingby i s n e a r 180 d e g r e e s . These advantages
w i l l be r e a l i z e d through, and w i l l e x t e n d , t h e o p p o r t u n i t i e s f o r lowenergy swingbys.
2.
Miss i o n Des i g n C h a r t s (Lockheed)
The problem of c o n s t r u c t i n g g e n e r a l i z e d m i s s i o n maps i s
c e n t e r e d around t h e d e t e r m i n a t i o n of ways of p r e s e n t i n g a composite
p l o t of many t r a j e c t o r y parameters a s f u n c t i o n s of launch d a t e and
�a r r i v a l date.
I n p r e s e n t i n g t h e s e parameters i n m i s s i o n map format,
numerous i n t e r m e d i a t e c r o s s p l o t s of each t r a j e c t o r y parameter a r e
r e q u i r e d . The Lockheed i n t e r p l a n e t a r y t r a j e c t o r y programs a r e b e i n g
modified t o produce a u t o m a t i c p l o t s of t h e s e parameters a s f u n c t i o n s of
launch and a r r i v a l d a t e s .
3.
I n t e r p l a n e t a r y N-Body Programs
a.
Program Development
Various f o r m u l a t i o n s of t h e e q u a t i o n s of motion and
numerical i n t e g r a t i o n techniques considered b o t h a s s e p a r a t e u n i t s and
a s combined packages a r e c o n t i n u i n g .
b
.
T a r g e t i n g Research (Nor t h r o p )
An i n t e r n a l memo (68-15) has been published g i v i n g t h e
r e s u l t s of t h e s t u d y of p e r t u r b e d c o n i c s o l u t i o n s t o i n t e r p l a n e t a r y
t r a j e c t o r y problems. Work i s c o n t i n u i n g on t h e programming and checkout
of t h e " a n a l y t i c conglomerate mass technique
Investigation i s a l s o
c o n t i n u i n g on t h e l a r g e time-step numerical i n t e g r a t i o n method.
."
c.
I s o l a t i o n Routine Research (Northrop)
Recently programmed techniques a r e being checked o u t ,
and v a r i o u s r o u t i n e s a r e being compared.
4.
Conic Programs f o r Small Computers
Work i s c o n t i n u i n g on t h e program t o compute i n j e c t i o n p o s i t i o n and v e l o c i t y a s a f u n c t i o n of launch azimuth and i n j e c t i o n energy
(C3). P r o g r e s s on t h i s work i s s e v e r e l y r e s t r i c t e d by t h e c u r r e n t l a c k
of a c c e s s t o l o c a l computers.
5.
O r b i t T r a n s f e r S t u d i e s (United A i r c r a f t NAS8-21091)
The f i n a l r e p o r t on t h i s s t u d y has been r e c e i v e d , and a l l
copies have been d i s t r i b u t e d . The r e p o r t c o n t a i n s a v e r y comprehensive
assessment of t h e s t a t e of t h e a r t of impulsive s o l u t i o n s t o o r b i t t r a n s f e r and rendezvous problems and a b i b l i o g r a p h y of over 300 r e f e r e n c e
papers which, i t i s thought, r e p r e s e n t a complete coverage of a v a i l a b l e
knowledge i n t h e s e a r e a s . R e p r e s e n t a t i v e s of t h e AIAA J o u r n a l have cont a c t e d t h e a u t h o r s , and i t i s hoped t h a t t h e r e p o r t w i l l be p u b l i s h e d i n
the Journal.
�6.
Odyssey (Lockheed)
A r e p o r t presenting equations f o r the v a r i a t i o n i n perigee
a l t i t u d e due t o s o l a r p e r t u r b a t i o n s has been paepared and i s being
reviewed in-house. A low p r i o r i t y e f f o r t i s now under way t o d e f i n e
launch o p p o r t u n i t i e s and d a i l y launch windows t o accommodate r e s t r i c t i o n s on t h e t r a j e c t o r y which would be n e c e s s a r y f o r a n Odyssey m i s s i o n .
7.
Abort and A l t e r n a t e Mission S t u d i e s
Documentation of t h e d e t a i l s of S a t u r n V v e h i c l e p e r f o r mance, guidance and c o n t r o l c h a r a c t e r i s t i c s , m i s s i o n s , and t r a j e c t o r y
shaping i s being accumulated i n a p r o c e s s of f a m i l i a r i z a t i o n of branch
personnel w i t h t h e problems of c o n t i n g e n c i e s and a b o r t s i t u a t i o n s . A
r e q u e s t t o t h e Boeing Company f o r a s t u d y t o develop a comprehensive
system-oriented d e s i g n f o r a f i r s t - s t a g e t i l t program t o accommodate
a n S-IC engine f a i l u r e has been i n i t i a t e d . Work i s a l s o being' i n i t i a t e d
in-house t o s t u d y t h e approach used t o provide f o r s u c c e s s f u l campletion
of t h e m i s s i o n i n c a s e of l o s s of a n a c c e l e r o m e t e r o u t p u t .
8.
O r b i t s i n Noncentral F i e l d s
An e f f o r t i s b e i n g made t o assemble a l l u s e f u l closed-form
s o l u t i o n s t o problems i n o r b i t a l mechanics, and t o i n d i c a t e t h e p h y s i c a l
s i t u a t i o n s of which t h e s e a r e mathematical models. Problems a r e charact e r i z e d by a p o t e n t i a l f u n c t i o n i n t h e c o o r d i n a t e system used. Problems
s t u d i e d t o d a t e i n c l u d e o r b i t s a b o u t o b l a t e , p r o l a t e , and pear-shaped
objects.
VII.
DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Damping of Liquid O s c i l l a t i o n s by Wall Roughness
(Ref. April-May 1968)
T e s t s t o determine t h e e f f e c t s of w a l l roughness on t h e damping of l i q u i d o s c i l l a t i o n s have been extended t o cover t h e e f f e c t s of
Reynolds number, a s w e l l a s roughness h e i g h t and l o c a t i o n . The Reynolds
number was decreased by t e s t i n g i n a s m a l l e r t a n k and by u s i n g s u c r o s e w a t e r s o l u t i o n s w i t h v i s c o s i t i e s up t o 162 cp a s t e s t l i q u i d s . As
expected, t h e damping was i n c r e a s e d by d e c r e a s i n g t h e Reynolds number.
The d i f f e r e n c e between t h e smooth-wall damping and rough-wall damping
was l e s s a t low Reynolds number t h a n a t h i g h Reynolds number.
(DDS)
�B.
Saturn V
1.
M i s s i o n P r o f i l e ( T r a j e c t o r y S h a p i n g , O p t i m i z a t i o n , TimeLining, e t c . )
a.
S l i g h t s h o t D i s p o s a l Mode (Ref. Feb.-March
1968, p. 37)
A p r e s e n t a t i o n was g i v e n summarizing t h e c u r r e n t r e s u l t s
and c o n c l u s i o n s r e l a t i v e t o S-IVBIIU s p a c e c r a f t r e c o n t a c t and l u n a r
debris.
The s l i n g s h o t mode o f S-IVB d i s p o s a l p r e s e n t e d was b a s e d upon
the following g u i d e l i n e s :
( 1 ) I n i t i a t e a n S-IVB p o s t i n j e c t i o n r e s i d u a l dump a t
a n a t t i t u d e and t i m e s u c h t h a t
(a)
s p a c e c r a f t r e c o n t a c t is avoided,
(b)
e a r t h i m p a c t i s a v o i d e d , and
(c)
l u n a r impact i s minimized s u b j e c t t o ( a )
and (b) above.
( 2 ) The f o l l o w i n g recommendation was made.
To a c c o u n t
f o r t h e v a r i a b l e t i m e o f LM e x t r a c t i o n , t h e s l i n g s h o t a l t i t u d e r e q u i r e d
t o a c c o m p l i s h S-IVB d i s p o s a l s h o u l d be:
Time P a s t TL1
A t t i t u d e from Local H o r i z o n t a l
1 hr.
2 hr.
3-6 h r .
An a c t i o n i t e m r e s u l t e d from t h e m e e t i n g t o d e t e r m i n e t h e t r a d e - o f f i n
terms o f impact p r o b a b i l i t y of e a r t h impact v s l u n a r i m p a c t . I n s p e c t i o n
i n d i c a t e d t h a t a d d i n g AV from t h e APS s y s tem - w i l l produce a s m a l l i n c r e a s e
i n the earth-impact probability while reducing s i g n i f i c a n t l y the lunarimpact p r o b a b i l i t y .
b.
S - I 1 and S-IVB P r o p e l l a n t U t i l i z a t i o n System A n a l y s i s
(NEW)
( 1 ) S - I 1 p r o p e l l a n t u t i l i z a t i o n f a i l u r e c a s e s were
i n v e s t i g a t e d w i t h and w i t h o u t t h e time-guard a p p l i e d as a s a f e t y measure
t o f o r c e a PU s h i f t i f a f a i l u r e had o c c u r r e d . Payload l o s s e s ranged
from 40,000 l b s f o r a c l o s e d - l o o p PU f a i l u r e a t 2 . 5 s e c t o MR = 4 . 5 w i t h
no time g u a r d t o 510 l b s w i t h a time-guard s e t a t t h e mincmum p e r f o r mance p e n a l t y t i m e f o r t h e same f a i l u r e . Data a r e f o r a n o m i n a l l y l o a d e d
s t a g e w i t h 970K p r o p e l l a n t .
�( 2 ) Various S - I 1 burn m i x t u r e o p t i o n s wel,
-a c1gated w i t h open-loop PU o p e r a t i o n . Payload l o s s e s ranged from 518 l b s
f o r t h e p r o f i l e of 5 . 0 / 5 . 5 / 4 . 7 t o 3600 l b s f o r 5 . 0 / 5 . 0 / 5 . 0 .
(3) Closed-loop PU f a i l u r e c a s e s f o r o u t - o f - o r b i t
burn w i t h o u t t h e time-guard were i n v e s t i g a t e d f o r t h e S-IVB s t a g e .
Payload l o s s e s f o r a closed-loop PU a t f i r s t o p p o r t u n i t y v a r i e d from
9762 l b s (310 m/sec d e f i c i t ) f o r a f a i l a t 4.5 MR a t o r b e f o r e t h e
nominal s h i f t time (back t o 5 . 0 MR) t o 2472 l b s (76 m/sec d e f i c i t ) f o r
a f a i l u r e from 4.5 MR t o 5.5 MR a t t h e nominal s h i f t time back t o t h e
5.0 MR.
Second o p p o r t u n i t y f a i l u r e s y i e l d e d 14497 l b s (474 m/sec v e l o c i t y d e f i c i t ) f o r a f a i l a t 4.5 MR a t i g n i t i o n t o 2391 l b s (73 m/sec
v e l o c i t y d e f i c i t ) f o r a f a i l a t 5 . 5 MR.
These a r e t h e extreme f a i l u r e
c a s e s f o r t h e S-IVB closed-loop PU o p e r a t i o n .
(4) Using a time s h i f t arrangement t o d u p l i c a t e
closed-loop response y i e l d e d a payload l o s s of 500 l b s .
(5) Open-loop cases w i t h c o n s t a n t burn mixture r a t i o s
f o r t h e o u t - o f - o r b i t burn y i e l d e d payload l o s s e s of 481 l b s and 512 l b s
f o r t h e f i r s t and second o p p o r t u n i t i e s , r e s p e c t i v e l y , w i t h a nominally
loaded s t a g e . By adding 1800 l b s a d d i t i o n a l LH2 and changing t h e burn
m i x t u r e r a t i o s , r e s p e c t i v e l y , t h e payload l o s s e s changed t o 127 l b s and
121 l b s f o r t h e f i r s t and second o p p o r t u n i t i e s , r e s p e c t i v e l y . This LH2
i n c r e a s e would a l s o be a p p l i c a b l e t o t h e closed- and open-loop schemes
s t u d i e d and should provide approximately the' same performance e f f e c t .
(6) The above d a t a were p r e s e n t e d a t t h e PU s t a t u s
meeting t o D r . Rees, J u l y 16, 1968. (DAP)
2.
Guidance
a.
S-I1 2 Engine Out (Ref. April-May 1968, p. 34)
(1) O f f i c e Memo R-AERO-DGA-3-68 was a n a c t i o n item
This l o g i c change
from a j o i n t meeting i n A p r i l between ASTR and AERO.
r e q u i r e d e n g i n e s - o u t d i s c r e t e s which r e q u i r e d hardware changes. S i n c e
no a c t i o n was t a k e n t o implement t h e l o g i c changes, two-engines-out
c a p a b i l i t y has n o t changed.
(2) O f f i c e Memo R-AERO-DGA-5-68 r e d e f i n e s t h e S - I 1
s t a g e s o t h a t engine-out d i s c r e t e s a r e n o t r e q u i r e d . However, t h e
guidance e q u a t i o n s a r e a d j u s t e d i f engines do go o u t . This approach
i s more d e s i r a b l e than t h e one g i v e n i n R-AERO-DGA-3-68.
It now appears
t h a t t h e r e q u i r e d a c t i o n t o implement t h i s p r o p o s a l w i l l be slow, i f a t
all.
�( 3 ) The e f f e c t i v e d a t e was n o t s p e c i f i e d i n e i t h e r
memorandum becaus'e t h e i r primary advantages a r e f o r f a i l u r e modes which
have, i n t h e p a s t , been r u l e d o u t . These f a i l u r e modes a r e n o t a program
requirement a t t h e p r e s e n t time. However, they could v e r y w e l l become
a requirement a t a much more unfavorable time. For t h a t r e a s o n , DGA-7-68
was prepared. This memorandum recommends t h a t DM-5-68 be implemented f o r
AS-503 and s u b s .
(DM)
b.
E v a l u a t i o n of t h e AS-502 F l i g h t Anomaly (New)
The 502 S - I 1 s t a g e l o s t two engines 104 seconds b e f o r e
nominal S - I 1 c u t o f f . As a consequence, t h e S - I 1 s t a g e d burn-time was
59 seconds longer than expected. During t h i s time, t h e v e h i c l e f l e w a t
a c o n s t a n t a t t i t u d e . Because of t h e extended burn-time and c o n s t a n t
a t t i t u d e , t h e S-IVB s t a g e had t o make extreme maneuvers i n o r d e r t o meet
t h e m i s s i o n c o n s t r a i n t s . As expected, t h e s m a l l a n g l e approximation t o
t h e t r i g f u n c t i o n s of (K1 - K ~ impacted
~ )
t h e "switching function" during t h e S-IVB burn. The guidance e q u a t i o n can be c a l l e d h a r d l y more
than a s w i t c h i n g f u n c t i o n s i n c e t h e v e h i c l e i s r e q u i r e d t o 'tilt a t a
maximum r a t e +1 d e g / s e c b e t t e r than 90 p e r c e n t of t h e burn-time.
A
s i m u l a t i o n of t h e 502 S-IVB f l i g h t w i t h a b e t t e r t r i g f u n c t i o n a p p r o x i mation of (K1 - K ~ i n~ t h e) time-to-go e q u a t i o n showed a n i n j e c t i o n
e r r o r of 700 meters i n a l t i t u d e w i t h no v e l o c i t y and f l i g h t p a t h a n g l e
e r r o r s . This approach i s being f u r t h e r i n v e s t i g a t e d a s a p o s s i b i l i t y of
implementation.
(DGA)
3.
Dynamics and Control
a.
S a t u r n V, S-IVB S l o s h Damping (New)
A s t u d y of s l o s h damping i n t h e S-IVB, LH2 tank has
r e c e n t l y been completed. As a r e s u l t a new s e t of LH2 damping v a l u e s
i s being recommended.
These new d a t a a r e based on t h e l a t e s t published
i n f o r m a t i o n concerning w a l l damping i n c y l i n d r i c a l t a n k s . The r e v i s e d
damping v a l u e s a r e somewhat s m a l l e r than previous d a t a , b u t should n o t
c r e a t e any major problems.
(DDS)
b.
S a t u r n V L a t e r a l - L o n g i t u d i n a l Coupling SA-502 (New)
A two-degrees-of-freedom spring-mass model of t h e
LTA-2 has been developed from t h e 43 x 43 dynamic m a t r i x developed by
Boeing. The c o e f f i c i e n t s from t h i s model a r e being used i n analog
s t u d i e s of t h e coupling between l a t e r a l and l o n g i t u d i n a l v i b r a t i o n
modes which occurred d u r i n g AS-502.
The analog s i m u l a t i o n s a r e of
two types :
�(1) One c o n s i d e r s t h e magnitude of t h e Pogo t h r u s t
o s c i l l a t i o n a s a n 'open-loop f o r c i n g f u n c t i o n t o t h e l o n g i t u d i n a l mode,
and has a s o u t p u t t h e l a t e r a l v e h i c l e and LEM motion.
(2) The second has t h e Pogo closed-loop w i t h complete
time-varying c o e f f i c i e n t s and t h e l a t e r a l - l o n g i t u d i n a l coupling.
The r e s u l t s of t h e s t u d i e s show:
(1)
A good d u p l i c a t i o n of t h e i n s t a b i l i t y observed
on AS-502.
(2)
A l o n g i t u d i n a l LEM a c c e l e r a t i o n of 0 . 6 5 g t s w i t h
a l a t e r a l a c c e l e r a t i o n of 0.5g's f o r a peak t h r u s t
o s c i l l a t i o n of 20,000 l b s .
(3)
No evidence of c o n t r o l system coupling w i t h Pogo.
(4)
Detuning Pogo (reducing s u c t i o n l i n e frequency)
reduces l a t e r a l response by f a c t o r of 10 o r more.
(5)
Driving t h e l o n g i t u d i n a d mode w i t h 5,000 l b s peak
amplitude w h i t e n o i s e produces v e r y l i t t l e l a t e r a l
LEM response (> 0 . 2 g f s ) .
( 6 ) A h i g h s e n s i t i v i t y of t h e system t o s m a l l v a r i a t i o n s i n f r e q u e n c i e s , s t r u c t u r a l damping, and
in£ luence c o e f f i c i e n t s e x i s t s
(DD/DC)
.
c.
Pogo S t a b i l i t y S t u d i e s (Ref. April-May 1968, p. 36)
Equations d e s c r i b i n g t h e Pogo phenomenon have been
d e r i v e d i n a form which permits t h e i r use i n a n e x i s t i n g d i g i t a l computer
program f o r s t a b i l i t y a n a l y s i s . I n i t i a l computer runs have been made f o r
t h e purpose of matching t h e AS-502 r e s u l t s and t h e r e b y v e r i f y i n g t h e model
and t h e parameter v a l u e s used. These runs a l s o s e r v e a s a b a s e f o r parame t e r s e n s i t i v i t y s t u d i e s . The accumulator f i x i n t h e e q u a t i o n s w i l l be
included a f t e r t h e s e p r e l i m i n a r y runs a r e completed.
(DC)
d.
S a t u r n V Rigid Body Responses t o Plume Induced
O s c i l l a t o r y Forces (New)
A f i r s t - s t a g e f l i g h t s i m u l a t i o n was made which included
a f u n c t i o n approximating t h e plume-induced o s c i l l a t o r y f o r c e s . The plume
f o r c e was a 5 cps wave w i t h a peak-to-minimum v a l u e range of 11,500 pounds
t o z e r o pounds, a c t i n g on t h e v e h i c l e a t 2 c a l i b e r s forward of t h e gimbal
s t a t i o n . The f l i g h t time r e g i o n was 120 seconds t o 130 seconds. The
�e f f e c t s of t h i s f o r c e on t h e r i g i d body responses were found t o have
l i t t l e impact on t h e c o n t r o l system and r i g i d body bending moments.
(DC)
5.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
AS-504 S t a t i s t i c a l Wind Response (New)
C o n t r a c t NAS8-21314 i s i n i t s second month. The wind
model t h e c o n t r a c t o r was d i r e c t e d t o use i s n o t s t a b l e i n t h e low a l t i t u d e
ranges. A new wind model i s being r e f i n e d under a new c o n t r a c t u s i n g
1,000 Jimsphere p r o f i l e s . Now t h a t a d e c i s i o n has been made on t h e wind
model, t h e e q u a t i o n s of motion f o r t h e system a r e being formulated.
(DDD/GE)
b.
AS-503, S-LVB F l i g h t S t a g e Dynamic Data
(Ref. April-May 1968, p. 38)
An a n a l y s i s was made t o determine t h e p i t c h dynamic
c h a r a c t e r i s t i c s f o r t h e unmanned AS-503 v e h i c l e d u r i n g t h e S-IVB p o r t i o n
of f l i g h t . An a n a l y s i s was a l s o made of t h e manned v e r s i o n a f t e r S-IVB
f i r s t burn. The r e s u l t s of t h e s e a n a l y s e s were published i n memorandum
(D~s/~oeing)
R-AERO-DD-117-68.
c.
AS-503 On-Pad Dynamic C h a r a c t e r i s t i c s (New)
On-pad dynamic c h a r a c t e r i s t i c s were c a l c u l a t e d f o r s e v e r a l
f u e l i n g c o n d i t i o n s on AS-503.
These d a t a have been g i v e n t o R-AERO-AU f o r
(DDS)
p r e d i c t i o n of ground wind l o a d i n g s .
C.
Saturn I B
1.
Dynamic Data f o r AS-205 S-IVB F l i g h t S t a g e (New)
A bending and t o r s i o n a n a l y s i s was made of t h e S-IVB f l i g h t
s t a g e u s i n g ~ o e i n g ' s s h e l l model. This type of a n a l y s i s i s n e c e s s a r y
because of s h e l l - t y p e modes i n t h e range of 16-18 c y c l e s t h a t do n o t
show up i n a beam model a n a l y s i s . Dynamic c h a r a c t e r i s t i c s o b t a i n e d from
(~~S/~oeing)
t h e a n a l y s i s were published i n memorandum R-AERO-DD-118-68.
2.
Revised Bending A n a l y s i s of AS-205, F i r s t F l i g h t S t a g e
(Ref. Feb.-March 1968, p. 38)
An a n a l y s i s was made f o r AS-205 f i r s t - s t a g e f l i g h t and f o r
on-pad c o n d i t i o n s t o i n c o r p o r a t e new mass d a t a i n c l u d i n g t h e r e v i s e d
p r o p e l l a n t b u r n - r a t e w i t h t h e r e v i s e d inboard engine c u t o f f . Also
updated s p a c e c r a f t s t i f f n e s s d a t a were i n c o r p o r a t e d , w i t h t h e primary
change being i n t h e SLA a r e a . The r e s u l t s of t h e a n a l y s i s were publ(D~~/~hrysler)
ished i n memorandum R-AERO-DD-116-68.
�D.
S a t u r n Apollo A p p l i c a t i o n Program
1.
Cluster
a.
Mission P r o f i l e
(1)
Unmanned Rendezvous Using S-IVB S t a g e
(Ref. April-May 1968, p. 40)
Two b a s i c p r o f i l e s t o accomplish unmanned rendezvous
have been s t u d i e d u s i n g t h e S-IVB workshop a t t i t u d e c o n t r o l system (WACS)
modified f o r t r a n s l a t i o n a l t h r u s t .
One method assumed i n s e r t i o n i n t o a n o r b i t 5
n a u t i c a l m i l e s above and downrange from t h e OWS using a r e s t a r t of t h e
(P&VE Laboratory i n v e s t i g a t e d t h e m o d i f i c a t i o n s necesS-IVB J - 2 engine.
s a r y f o r t h e r e s t a r t . ) T r a n s f e r was made w i t h a modified WACS p r o p u l s i o n
system t o a w a i t i n g o r b i t 1 NM above t h e OWS. By v a r y i n g t h e time s p e n t
i n t h e w a i t i n g o r b i t , t h e c o r r e c t l i g h t i n g c o n d i t i o n s could be c o n t r o l l e d
f o r t h e t e r m i n a l phase. Rendezvous i s accomplished a s i n t h e Apollo
S a t u r n I B d u a l rendezvous except i n t h i s c a s e t h e c h a s e r v e h i c l e (LM/ATM)
w i l l be coming i n from above r a t h e r than below t h e t a r g e t . The o t h e r
rendezvous technique assumes a d i r e c t i n s e r t i o n of t h e S-IVB/LM i n t o t h e
OWS o r b i t 110 NM ahead of t h e OWS. (One hundred and t e n NM i s used t o
a l l o w f o r 40 NM 30 i n s e r t i o n d i s p e r s i o n s and a lSIsecond launch window.)
I n s e r t i o n i s then made w i t h t h e WACS i n t o a phasing o r b i t w i t h a p e r i o d
longer than t h a t of t h e OWS. A f t e r two complete r e v o l u t i o n s i n t h i s
o r b i t , t h e r e l a t i v e range has decreased t o 20 NM, and a second WACS
burn i s made p l a c i n g i t on a n e l l i p s e which i n t e r c e p t s t h e OWS a f t e r a
c e n t r a l a n g l e t r a v e l of 240". When s t a t i o n - k e e p i n g d i s t a n c e i s r e a c h e d ,
a t h i r d WACS burn is made which matches t h e S-IVB/L,M and OWS v e l o c i t i e s .
An a n a l y s i s has a l s o been made f o r t h e s e two rendezvous methods of t h e
a d d i t i o n a l WAC impulse n e c e s s a r y t o overcome i n s e r t i o n d i s p e r s i o n s (both
performance and n a v i g a t i o n ) and t o account f o r LM rendezvous r a d a r
e r r o r s . Both rendezvous p r o f i l e s r e q u i r e d l e s s p r o p e l l a n t than i s
a v a i l a b l e i n t h e WACS. It was found t h a t t h e d e t r i m e n t a l consequences
of t h e r a d a r e r r o r s could be reduced i f t h e l e s s a c c u r a t e a n g l e and
a n g l e r a t e r a d a r d a t a were ignored. To make up f o r t h i s , more t h a n one
measurement of range and range r a t e was taken t o determine t h e c o n i c
parameters and p o s i t i o n on t h e c o n i c through c a l c u l a t i o n s i n t h e I U
computer. The r e s u l t s of t h e s e s t u d i e s were p r e s e n t e d t o t h e AAP Basel i n e C o n f i g u r a t i o n Review on J u l y 23.
(~A~/~orthrop)
�(2)
E a r t h Resources Experiment Impact on C l u s t e r I
Mission (Ref. April-May 1968, p. 39)
This s t u d y was extended t o i n c l u d e the conseqyences
of t h e 34.26 i n c l i n a t i o n of AAP-2 on t h e UP-3A m i s s i o n . It was demons t r a t e d that s a t i s f a c t o r y launch o p p o r t u n i t i e s could be i n s u r e d a b o u t
every t h i r d day n e a r t h e d e s i r e d launch d a t e of AAP-3A.
(~AO/Northrop)
(3)
AAP-314 A l t e r n a t e Mission P r o f i l e and Launch
Window Analys i s (New)
During t h i s p e r i o d , a s t u d y was i n i t i a t e d t o d e t e r mine t h e m i s s i o n p r o f i l e and launch o p p o r t u n i t i e s assuming t h e AAP-314 i s
flow s e p a r a t e from t h e OWS. The following a r e t h e ground r u l e s under
which t h i s s t u d y i s being done:
(a)
A high i n c l i n a t i o n i s d e s i r a b l e t o increase
the ATM sun o b s e r v a t i o n time.
(b)
The IU has a 7 112-hour l i f e t i m e f o r s t a b i l i z a t i o n of AAP-4 f o r docking maneuvers.
(c)
There is a minimum AAP-3 i n s e r t i o n of 81 x 120 NM.
(d)
Rendezvous between U P - 3 and 4 i s t o be accomp1i s hed by t h e s tandard c o - e l l i p t i c technique.
It was found t h a t , i f a n i n c l i n a t i o n of 47" were used, two in-plane
in-phase o p p o r t u n i t i e s could be provided on t h e same day. To s a t i s f y
t h e second ground r u l e , t h e manned AAP-3 was launched f i r s t i n t o a n
81 x 120 NM o r b i t , c i r c u l a r i z i n g a t 120 NM w i t h t h e SPS. One day l a t e r
AAP-4 i s i n s e r t e d d i r e c t l y i n t o a c i r c u l a r o r b i t . The a l t i t u d e s f o r t h e
AAP-4 o r b i t being considered a r e 180, 170, and 200 NM. Various t r a d e - o f f s
between launch window width, payload, m i s s i o n p r o f i l e , and rendezvous time
have been made. Thus f a r , o n l y n o r t h e r l y launches i n t o t h e 47" i n c l i n a t i o n o r b i t have been considered. During t h e n e x t p e r i o d , a n a l y s i s f o r
s o u t h e r l y launches should be completed and documentation should begin.
(DAO/NO~
throp)
(4)
R o l l Required of UP-112 t o C a l i b r a t e S-049 (New)
Experiment S-049 on t h e AAP-112 m i s s i o n has a n
instrument t h a t must be c a l i b r a t e d sometime d u r i n g t h e m i s s i o n . The
instrument i s c a l i b r a t e d by t a k i n g a photograph of t h e moon when t h e
moon i s e q u a l t o o r g r e a t e r t h a n h a l f i l l u m i n a t e d . The o p t i c a l a x i s of
t h e instrument l i e s i n t h e o r b i t plane of t h e AAP-112 o r b i t and p o i n t s
i n t h e d i r e c t i o n of t h e m e r i d i a n which i s 180" away from t h e s u n ' s
m e r i d i a n . The o n l y maneuvers p e r m i t t e d t h e AAP-112 a r e r o l l maneuvers
�(no p i t c h o r yaw); thus t h e moon must l i e a t ( o r v e r y n e a r ) t h e i n t e r s e c t i o n of t h e moon's p l a n e and t h e AAP o r b i t p l a n e t o be v i s i b l e w i t h i n
t h e f i e l d of view of t h e instrument. Then w i t h a r o l l maneuver of t h e
AAP, t h e S-049 can view and photograph t h e moon. It i s immediately
obvious t h a t , s i n c e t h e moon must b e e q u a l t o o r g r e a t e r t h a n h a l f
i l l u m i n a t e d t o c a l i b r a t e t h e i n s t r u m e n t , t h e n o n l y h a l f of each l u n a r
month, from f i r s t q u a r t e r t o l a s t q u a r t e r , w i l l b e a v a i l a b l e f o r c a l i b r a t i o n . Also, because of t h e p o i n t i n g d i r e c t i o n of t h e i n s t r u m e n t w i t h
r e s p e c t t o t h e sun, t h e r e q u i r e d r o l l a n g l e of t h e AAP-112 w i l l always
b e e q u a l t o o r l e s s t h a n 90 d e g r e e s .
-
A complete a n a l y s i s of t h e problem has been done
u s i n g October 1, 1970, as a launch d a t e f o r UP-112.
I f the mission
lasts as long as 28 days, t h e n t h e r e w i l l always b e a time d u r i n g t h e
m i s s i o n when t h e c a l i b r a t i o n can be done. During October of 1970, t h e
c a l i b r a t i o n can b e done between October 8 and October 22. Given any
launch time d u r i n g t h e day and any launch d a t e d u r i n g t h e f i r s t of
October, i t is determined on what d a t e t h e c a l i b r a t i o n can be done and
what r o l l a n g l e w i l l b e r e q u i r e d . Some launch times d u r i n g t h e day
y i e l d s i n g l e s o l u t i o n s (one day on which t h e c a l i b r a t i o n i s p o s s i b l e ) ,
some launch times y i e l d double s o l u t i o n s , and some launch times y i e l d
t r i p l e solutions.
(DAO)
(5)
P r e l i m i n a r y F l i g h t P r o f i l e s f o r AAP-1 and 3A (New)
An a n a l y s i s t o determine AAP-1 and AAP-3A launch
v e h i c l e t a r g e t i n g parameters was made t o r e f l e c t v e h i c l e reassignments.
The i n e r t i a l descending node and i n c l i n a t i o n were v a r i e d t o s a t i s f y
t h r e e launch o p p o r t u n i t i e s f o r t h e AAP'1 and two launch o p p o r t u n i t i e s
f o r t h e AAP-3A.
The r e s u l t i n g optimum payloads f o r t h e f i r s t , second
and w o r s t launch o p p o r t u n i t i e s of AAP-1 were 39228 l b s , 39230 l b s , and
39128 l b s , r e s p e c t i v e l y . For t h e f i r s t and second o p p o r t u n i t i e s f o r
AAP-3A, t h e payload v a l u e s were 39865 l b s and 39897 l b s , r e s p e c t i v e l y .
The purpose of t h e r e g e n e r a t i o n of t h e AAP-1 and AAP-3A launch window
a n a l y s i s was t h e reassignment of SA-207 from AAP-1 t o AAP-3A and SA-206
from AAP-3A t o AAP-1.
(DAP)
(6)
Design Reference Mission Document (DRMD)
(New)
AAP-314
.
R e p r e s e n t a t i v e s of t h e Mar tin/Mar i e t t a Corp and
members of R-AERO-DAM completed a comprehensive review of t h e DRMD f o r
These s i x volumes p r o v i d e t h e Apollo A p p l i c a t i o n s
miss i o n AAP-3/AAP-4.
Program p l a n n e r s w i t h a c o n c i s e and dynamic d e f i n i t i o n of t h e b a s e l i n e
m i s s i o n f o r u s e a s a g u i d e l i n e and planning document. The a n t i c i p a t e d
r e l e a s e d a t e ( f o r review and comment) is t h e f i r s t of August. These
volumes f o l l o w t h e same g e n e r a l o u t l i n e as t h e DRMD of U P - 1 1 2 published i n May 1968 (Ref. n o t e s of Dec.-Jan.).
( ~ ~ ~ I ~ a r t i n )
�(7)
E a r t h Resources Experiments Impact on UP-l/AAP-2
AAP-3A (Ref. April-May 1968, p. 39)
F u r t h e r s t u d i e s have been made i n t h e d e t e r m i n a t i o n
of t h e c o m p a t i b i l i t y of performing e a r t h r e s o u r c e s experiments on t h e
AAP-l/AAp-2 m i s s i o n . One a r e a under i n v e s t i g a t i o n i s t h e impact of t h e s e
experiments on t h e AAP-3A m i s s i o n . It was found t h a t no r e a l i n c r e a s e i n
s u n l i g h t time could be expected, a l t h o u g h t h e t o t a l time a v a i l a b l e was
increased s i g n i f i c a n t l y
.
Another a r e a i n v e s t i g a t e d was t h e impact on t h e
e a r t h r e s o u r c e s experiments of cloud cover. The r e s u l t s of t h i s s t u d y
from R-AERO-YT show t h a t t h e t o t a l c l e a r (< 3 cloud cover) s u n l i g h t time
(DAM)
a v a i l a b l e f o r e a r t h r e s o u r c e s experiments i s s e v e r e l y reduced.
b.
Dynamics and C o n t r o l
(1)
CMG Maximum Volume C o n t r o l Law (Ref. April-May
1968, p. 44)
A d i g i t a l s i m u l a t i o n of t h e c o n t r o l law i s i n
progress.
The r e s u l t s of t h e s i m u l a t i o n thus f a r look encouraging i n
t h a t t h e law provides a n i s o g o n a l d i s t r i b u t i o n of t h e i n d i v i d u a l momentum
v e c t o r s w h i l e f o l l o w i n g t h e commanded momentum v e c t o r . One limitation of
t h e law t h a t has been observed i s a r a t e l i m i t a t i o n on how £as t t h e cont r o l may r e a c t . This l i m i t a t i o n i s being s t u d i e d t o s e e i f i t i s of
p r a c t i c a l s i g n i f i c a n c e , and i f t h i s l i m i t a t i o n i s a problem, how i t may
eliminated.
(DDD)
(2)
Revised V i b r a t i o n Data f o r t h e AAP C l u s t e r
(Ref. April-May 1968, p. 44)
A new v i b r a t i o n a n a l y s i s was made f o r t h e AAP
Cluster.
The con£ i g u r a t i o n analyzed cons i s ts of t h e CSM docked a x i a l l y
and t h e LM/ATM docked r a d i a l l y t o t h e MDA/AM/SLA/OWS. The ATM/OWS s o l a r
panels a r e deployed w i t h consumables aboard and experiments deployed.
The new a n a l y s i s was n e c e s s a r y because of a l a r g e i n c r e a s e i n f u r n i s h e d
s t i f f n e s s v a l u e s of t h e OWS s o l a r panel s u p p o r t beams. The new d a t a
(~~S/Martin)
were published i n memorandum R-AERO-DD-119-68.
(3)
S-IVB P r o p e l l a n t S l o s h (New)
A s i m u l a t i o n s t u d y of a c o a s t i n g S-IVB s t a g e i s
underway t o determine t h e f e a s i b i l i t y of a n engine r e s t a r t a t low propell a n t l e v e l s . Various u l l a g i n g schemes w i l l a l s o be c o n s i d e r e d . Excess i v e p r o p e l l a n t s l o s h i n g could uncover t h e s u c t i o n l i n e i n l e t and cause
a r e i g n i t i o n f a i l u r e . The purpose of t h i s s t u d y i s t o d e f i n e l i m i t s on
u l l a g e t h r u s t i n g , p r o p e l l a n t l e v e l s , and maneuvers.
(DDS)
�(4)
AAP-2 and AAP-4 Nose Cone J e t t i s o n w i t h Tower
J e t t i s o n Motor (Ref. Feb. Mar. 1968, p. 42)
S t u d i e s of nose cone j e t t i s o n w i t h t h e tower j e t t i son motor have continued a s v e h i c l e d e f i n i t i o n becomes more complete.
I n c o r p o r a t e d i n t h e more r e c e n t s t u d i e s a r e the s w i t c h t o t h e AS-203 type
nose cone w i t h a c y l i n d r i c a l e x t e n s i o n , t h e d e l e t i o n of s e v e r a l p o r t s on
t h e MDA, and t h e a d d i t i o n of t h e probe cover and i t s m e t e o r i t e s h i e l d .
Short-term c l e a r a n c e does n 6 t appear t o be a problem. Work has continued
t o i d e n t i f y t h e plume impingement p r e s s u r e s on t h e AAP-4 LM where e x i s t ing s p e c i f i c a t i o n p r e s s u r e s a r e q u i t e low. Long-term c l e a r a n c e i n t h e
absence of l a r g e guidance a c t i o n s i s a d e q u a t e , b u t t h e expected maximums
of guidance a c t i o n s i n c o n j u n c t i o n w i t h t h e j e t t i s o n a r e s t i l l to b e
(DC)
investigated.
(5)
A c t i v e A t t i t u d e Control (New)
S i m u l a t i o n w i t h t h e d i g i t a l computer r e a c t i o n cont r o l program has r e v e a l e d a need f o r improving t h e a c c u r a c y of t h e s o l u t i o n f o r t h e a t t i t u d e e r r o r s i n long r u n s . The problem g e n e r a l l y o c c u r s
when t h e i n i t i a l a t t i t u d e e r r o r s a r e v e r y l a r g e . S i n c e t h i s l e n g t h y
computation i s being performed i n d o u b l e - p r e c i s i o n w i t h a m a t r i x smoothing
r o u t i n e , i t has been decided t q s w i t c h t h e e x a c t computation t o one based
on s m a l l a n g l e approximations when t h e e r r o r s f a l l w i t h i n a cone where
such approximation i s j u s t i f i e d .
On t h e g r a v i t y g r a d i e n t momentum dumping s t u d y ,
a d a p t a t i o n of a d i g i t a l program t o t h i s s t u d y i s proceeding on s c h e d u l e .
(DGA)
The major t a s k remaining i s t o add t h e c o n t r o l l a w s .
c.
P r o j e c t Information A p p l i c a b l e t o Many Vehicles
(1)
Poss i b l e AAP Payload Improvements (New)
A s a means of i n c r e a s i n g payload f o r AAP, v a r i o u s
5-2 engine swaps on t h e S-IVB s t a g e s were i n v e s t i g a t e d , a l o n g w i t h subo r b i t a l s t a r t s of t h e s e r v i c e module (2 112 s t a g e s ) , S-IVB s t a g e 208,
and use of t h e p a s s i v a t i o n impulse f o r c i r c u l a r i z a t i o n . The engines
analyzed were 5-2104 and 5-2111, e x t r a s from t h e S - I 1 s t a g e program,
Payload g a i n s f o r t h e manned miss ions ranged from a minimum
and J - 2 s .
of 500 pounds f o r AAP-3 t o a maximum of 4600 pounds f o r AAP-1.
For t h e unmanned m i s s i o n s , payload g a i n s ranged
from a minimum of 360 pounds t o a maximum of 2270 pounds f o r AAP-2.
(DAP)
�(2)
AAP-4 P r e l i m i n a r y Rigid Body Response
A n a l y s i s (New)
The s t u d y of t h e AAP-4 m i s s i o n , f i r s t f l i g h t s t a g e
p r e l i m i n a r y r i g i d body responses has been completed and p u b l i s h e d .
Vehicle responses and bending moments were determined f o r RSS bending
moment c o n d i t i o n s i n t h e presence of 95 p e r c e n t i l e n o n - d i r e c t i o n a l
wind p r o f i l e s . The f l i g h t c o n d i t i o n s i n v e s t i g a t e d were March 1, q a m a x ,
q max, and n e a r inboard engine c u t o f f . The maximum bending moment of
t h e c a s e s was 66 m i l l i o n i n c h pounds n e a r t h e S-IBIS-IVB s e p a r a t i o n
p l a n e i n t h e q max c a s e (T = 68 seconds). The maximum c o n t r o l a n g l e
(DC)
i n c u r r e d was 6.7 d e g r e e s f o r t h e wind p r o f i l e peaking a t q max.
2.
OWS O r i e n t a t i o n S t u d i e s (Ref. April-May 1968, p. 45)
The computer s i m u l a t i o n has been changed t o accommodate a
d i f f e r e n t method of computing t h e atmospheric d e n s i t y . The method curve
f i t s d e n s i t y d a t a s u p p l i e d by R-AERO-YS f o r d i f f e r e n t d a t e s , a l t i t u d e s ,
and solar-geomagnetic a c t i v i t i e s .
The s i m u l a t i o n i s a l s o being changed
t o make p o s s i b l e t h e e v a l u a t i o n of OWS maneuvers away from t h e X-POP
o r i e n t a t i o n , and i n c l u d e s t h r u s t impingement on t h e OWS and t h e s o l a r
arrays.
Computer s i m u l a t i o n s of s o l a r p o i n t i n g experiments have
been r u n f o r p a n g l e s o t h e r t h a n z e r o and i n d i c a t e a s e v e r e c o n t r o l
impulse p e n a l t y . Also t h e c o n t r o l impulse budget f o r a 220-nauticalm i l e o r b i t i n November 1970 has been o b t a i n e d . S t u d i e s t h a t i n d i c a t e
a n e g l i g i b l e e f f e c t on impulse requirements when t h e a r r a y s a r e r o t a t e d
t o t h e s o l a r v e c t o r have a l s o been made.
(DD)
3.
ATM
a.
V i s i b i l i t y of t h e Earth-Moon L i b r a t i o n P o i n t s
from ATM (Ref. April-May 1968, p. 38)
The e q u a t i o n s f o r determining t h e a n g u l a r displacement
of L4 and L5 from t h e l i n e of s i g h t between t h e ATM and t h e sun have been
i n c o r p o r a t e d i n t o t h e N-body deck and checked o u t . Some runs have been
made on t h e deck, and i t has been determined t h a t L5 would be v i s i b l e
w i t h i n t h e f i e l d of view of t h e HA0 i n s t r u m e n t on J u l y 27, 1971, from
approximately 1600 hours GMT t o approximately 2400 hours GMT. L4 would
be v i s i b l e on August 1 5 , 1971, a g a i n approximately between t h e hours of
1600 GMT and 24 GMT. Then L5 would a g a i n be v i s i b l e on August 26, 1971,
between t h e hours of 0600 GMT and 1300 GMT. This l a s t s i g h t i n g i s o u t
n e a r t h e edge of t h e f i e l d of view of t h e HA0 instrument. No more
viewing w i l l be p o s s i b l e u n t i l a b o u t s i x months l a t e r f o r r e a s o n s s t a t e d
i n t h e April-May p r o g r e s s r e p o r t . Work i s c o n t i n u i n g t o determine t h e
e x a c t viewing times f o r t h e time p e r i o d Jan.-Feb., 1972.
(DAO)
�b.
AAP-4 LM/ATM Unmanned Rendezvous (Ref. Feb.-Mar.
1968, p. 45)
D e t a i l e d guidance and n a v i g a t i o n a l a n a l y s e s have been
g e n e r a t e d f o r one and two S-IVB i g n i t i o n p r o f i l e s . This w i l l a l l o w more
r e a l i s t i c APS ( a u x i l i a r y p r o p u l s i o n systems) p r o p e l l a n t budgets t o be
d e f i n e d . MSC was f u r n i s h e d w i t h a s e t of t h e s e d a t a t o use i n t h e i r
a n a l y s i s of t h e LM/ATN p r o p e l l a n t budgets. Work c o n t i n u e s i n t h e a r e a
of low AV rendezvous t r a n s f e r maneuvers and e s t a b 1 i s h i n g i g n i t i o n c r i t e r i a
f o r t h e s e t h r u s t e v e n t s . The u s e of r a d a r d a t a i n c o n j u n c t i o n w i t h t h e
ST-124M p l a t f o r m looks promising a s a s o u r c e of n a v i g a t i o n update.
(DG/Nor t h r o p )
c.
AAP Rendezvous S i m u l a t i o n Program (New)
A rendezvous s i m u l a t i o n computer i s b e i n g developed that
w i l l permit simultaneous s i m u l a t i o n of (1) a t a r g e t - s a t e l l i t e s t a t e ,
(2) p u r s u i t - e s t i m a t e d ( n a v i g a t i o n ) s t a t e , and (3) a c t u a l s t a t e , s o
t h a t d e t a i l e d a n a l y s i s of rendezvous problems can be made i n a n o r d e r l y
fashion.
(DG)
d.
P a s s i v e A t t i t u d e C o n t r o l (New)
(1) A l l p e r t i n e n t e q u a t i o n s f o r , a completely g e n e r a l
s i m u l a t i o n of t h e aerodynamic damping concept have been completed. The
system of e q u a t i o n s c o n t a i n s t h r e e r o t a t i o n a l degrees of freedom f o r t h e
main body and a n independent s i n g l e degree of freedom f o r each p a n e l .
The f o r m u l a t i o n a l s o a l l o w s t h e i n s e r t i o n of a n a r b i t r a r y d i h e d r a l a n g l e
f o r each p a n e l . S i n c e t h e e q u a t i o n s have been c a s t completely i n m a t r i x
form, they can be e a s i l y extended t o a d d i t i o n a l d e g r e e s of freedom.
(2) E f f o r t i s being expended t o d e f i n e t h e aerodynamics
f o r this particular application, since data a r e not available for the
main body and each of t h e panels t a k e n s e p a r a t e l y . The procedure t h a t i s
being followed i s t o use f o r t h e main body t h e aerodynamic d a t a a s
r e p o r t e d i n document LMSC/HREC A791488 f o r t h e workshop w i t h t h e panels
r e t r a c t e d and t o u s e a s e p a r a t e model f o r t h e p a n e l s . The shortcoming
of t h i s procedure i s t h a t i t w i l l n o t i n c l u d e t h e e f f e c t of "shadowing"
between t h e b o d i e s . A s b e t t e r d a t a become a v a i l a b l e , t h o s e new models
can be added t o t h e program.
( 3 ) A c o n s i d e r a b l e number of d i g i t a l computer runs f o r
t h e " s t o r e d c o n f i g u r a t i o n " w i t h t h e p a n e l s p a r a l l e l t o t h e OWS a x i s have
been made. The s i m u l a t i o n s a r e g e n e r a l l y r u n up t o 360,000 seconds of
r e a l time. Both t h e s t a b i l i t y f o r v a r i o u s i n i t i a l c o n d i t i o n s and t h e
e f f e c t of t h e maximum i n t e g r a t i o n i n t e r v a l on t h e s o l u t i o n a c c u r a c y a r e
being studied.
�( 4 ) A r o u t i n e f o r f i t t i n g t h e OWS aerodynamic d a t a t o
a double F o u r i e r s e r i e s has been programmed, and i s being checked o u t .
The prog ram is s e t up f o r t h e 7 0 9 4 computer.
(DCA)
e.
ATM S t a b i l i t y and Response (New)
For new A'IM bending d a t a , f i l t e r s and g a i n s have been
o b t a i n e d . Parameter s t u d i e s a r e being made t o i n v e s t i g a t e t h e s t a b i l i t y
and time r e s p o n s e of t h e system a s t h e bending d a t a changes.
(DDD)
E.
Generation of Real E a r t h Model C i r c u l a r and E l l i p t i c a l
O r b i t V e l o c i t y Requirements (New)
Data a r e b e i n g g e n e r a t e d t o determine i n s e r t i o n v e l o c i t i e s
r e q u i r e d t o a t t a i n d e s i r e d o r b i t s ( r a d i u s of p e r i g e e and apogee a l t i tude) based on t h e F i s c h e r E l l i p s o i d r a t h e r than t h e s p h e r i c a l e a r t h
g r a v i t y model. For a g i v e n o r b i t , i n s e r t i o n v e l o c i t y i s a f u n c t i o n
of o r b i t a l i n c l i n a t i o n and i n s e r t i o n l a t i t u d e when t h e o b l a t e e a r t h
g r a v i t y model i s employed. As a r e s u l t , i n s e r t i o n v e l o c i t y i s n o t cons t a n t over t h e e a r t h ' s s u r f a c e a s assumed when u s i n g t h e s p h e r i c a l e a r t h
g r a v i t a t i o n a l c o n s t a n t . For example, t h e v e l o c i t y a t p e r i g e e of a n
81 x 120 NM o r b i t based on t h e s p h e r i c a l e a r t h model i s 7 8 3 5 . 4 6 mlsec.
Assuming a n o r b i t a l i n c l i n a t i o n of 28.50 and a n i n s e r t i o n l a t i t u d e of
2 7 " , a p e r i g e e v e l o c i t y of 7 8 3 8 . 4 5 m/sec i s r e q u i r e d u s i n g t h e o b l a t e
e a r t h g r a v i t y model.
The d i f f e r e n c e between t h e two v e l o c i t i e s i s 2.98 m/sec. I f
o r b i t a l i n s e r t i o n occurs a t t h e v e l o c i t y based on a s p h e r i c a l e a r t h
model, t h e apogee a l t i t u d e w i l l b e l e s s t h a n t h a t d e s i r e d .
The maximum d i s p e r s i o n s from t h e s p h e r i c a l e a r t h model v e l o c i t i e s occur f o r a n i n c l i n a t i o n of 9 0 d e g r e e s .
(DAP)
F.
S a t u r n V Launch Vehicle and S p a c e c r a f t Launch P r o b a b i l i t y (New)
A c o n t r a c t e d s t u d y has been undertaken by t h e Lockheed M i s s i l e s
and Space Company under the d i r e c t i o n of -DAM f o r t h e purpose of c a l c u l a t i n g t h e p r o b a b i l i t y of a s u c c e s s f u l s p a c e m i s s i o n f o r a S a t u r n V
launch v e h i c l e .
It i s a n t i c i p a t e d t h a t t h i s s t u d y w i l l use t h e t h e o r y
of Markov P r o c e s s e s f o r m i s s i o n s i m u l a t i o n , w i t h t h e end r e s u l t b e i n g
a computer program g e n e r a l enough t o be used f o r a v a r i e t y of launch
(~AM/Lockheed)
v e h i c l e c o n f i g u r a t i o n s and v a r i o u s m i s s i o n t y p e s .
�VIII.
F'LIGHT TEST ANALYSIS DIVISION
A.
F l i g h t Mechanics Branch
1.
S a t u r n IB
a.
A S - ~ O ~ / C S M - LRendezvous
O~
~ i si os n
A b a s i c r e v i s i o n t o t h e launch v e h i c l e o p e r a t i o n a l mode
was made w i t h t h e d e c i s i o n t o f l y w i t h open-loop o p e r a t i o n of t h e S-IVB
p r o p e l l a n t u t i l i z a t i o n system. This d e c i s i o n r e q u i r e s t h e r e g e n e r a t i o n
of t h e nominal o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s (S-IVB phase
o n l y ) , range s a f e t y , and a b o r t and a l t e r n a t e m i s s i o n s t u d i e s .
Analysis of f a i l u r e modes of t h e p r o p e l l a n t u t i l i z a t i o n (PU) s y s tem r e v e a l e d t h a t t h e primary m i s s i o n could n o t be a t t a i n e d
by t h e launch v e h i c l e f o r most of t h e f a i l u r e s considbred. It was t h u s
determined by Program Management t h a t i t would be p r e f e r a b l e t o commit
t h e m i s s i o n t o a l e s s t h a n 30 p e r f o m a n c e margin w i t h a n open-loop PU
s y s tem r a t h e r t h a n r i s k completion of t h e m i s s i o n due t o a PU f a i l u r e .
The a b o r t and a 1 t e r n a t e miss i o n document r e f l e c t i n g
closed-loop o p e r a t i o n of t h e p r o p e l l a n t u t i l i z a t i o n system should be
published i n e a r l y August. These d a t a should g i v e c h a r a c t e r i s t i c
behavior similar t o t h a t of a n open-loop system.
b.
AS-206/AS-207 Dual Launch
The S-IB s t a g e t i l t programs were r e g e n e r a t e d by CCSD
t o e l i m i n a t e a d i s c r e p a n c y i n t h e time argument. These d a t a a r e a g a i n
being reviewed f o r acceptance.
The AS-207 I n t e r f a c e Control Document (ICD) was modified
t o r e f l e c t P&VE o r b i t a l v e n t i n g d a t a which d i d n o t a g r e e t o t h e o r i g i n a l
v e n t schedule.
The o p e r a t i o n a l t r a j e c t o r i e s a r e expected from CCSD i n
e a r l y Augus t .
2.
Saturn V
D i s t r i b u t i o n of t h e f i n a l o p e r a t i o n a l t r a j e c t o r y was
delayed by a n e r r o r d i s c o v e r e d i n t h e S-IVB s t a g e s i m u l a t i o n
The
e r r o r has been c o r r e c t e d , and t h e document should be d i s t r i b u t e d soon.
�The d i s p e r s i o n a n a l y s i s , which was r e turned t o Northrop
t o c o r r e c t d e f i c i e n c i e s , i s expected t o be completed on,August 1.
Range S a f e t y d a t a have been forwarded t o KSC r e f l e c t i n g
launch from Complex 39B. The launch was s u b s e q u e n t l y rescheduled t o
Complex 39A. No update i n t u r n i n g r a t e s w i l l be recorded; however,
r e v i s e d envelope t r a j e c t o r i e s have been t r a n s m i t t e d v i a magnetic t a p e .
No f u r t h e r requirements from KSC a r e a n t i c i p a t e d .
b.
A S - 5 0 3 / ~ - ~ i si os n
The o p e r a t i o n a l t r a j e c t o r y was d i s t r i b u t e d on June 20,
1968. A l l MSC c o p i e s , however, were l o s t i n t h e m a i l . T r a j e c t o r y d a t a
were a v a i l a b l e t o c r i t i c a l a r e a s by means of t h e magnetic t a p e normally
t r a n s m i t t e d b e f o r e document r e l e a s e . The document d i d n o t r e f l e c t t h e
f o l l o w i n g changes i n hardware, s o f t w a r e d a t a , and t r a c k i n g requirements:
2 deg c a n t i n S-IC outboard e n g i n e s , aerodynamic d a t a r e v i s i o n , and
i n c r e a s e d e l e v a t i o n a n g l e requirement f o r Guaymas v i s i b i l i t y ( r e q u i r e d
s h i f t i n 2nd burn i g n i t i o n ) . These changes w i l l b e i n c o r p o r a t e d i n a n
update t o be published by August 3 , 1968. A f u r t h e r change due t o t h e
s p a c e c r a f t 4g a c c e l e r a t i o n l i m i t a t i o n w i l l n o t be r e f l e c t e d f o r s e v e r a l
weeks. The v e h i c l e maximum a c c e l e r a t i o n w i l l be' reduced by a l l o w i n g a
10-second e a r l i e r shutdown of t h e S-IC c e n t e r engine.
The d i s p e r s i o n a n a l y s i s w i l l b e a v a i l a b l e i n e a r l y
August. E f f e c t s of t h e above changes w i l l be a s s e s s e d b e f o r e planning
a n update of t h e document.
c.
O r b i t a l Debris
The S u r v i v a l and Risk Hazard r e p o r t s f o r AS-503 have
been approved and forwarded t o t h e P r o j e c t s O f f i c e f o r d i s t r i b u t i o n .
B.
Tracking and O r b i t a l Analysis Branch
1.
Saturn I B
(1) The AS-205 S-IVB p r e d i c t e d l i f e t i m e and decay
r a t e s were p r e s e n t e d a t t h e G&P Subpanel h e l d a t MSC on June 19, 1968.
(2) Tracking and communications a n a l y s e s f o r t h e AS-205
Abort and A l t e r n a t e Missions have been completed and w i l l be included i n
t h e Abort and A l t e r n a t e Mission document.
�2.
Saturn V
(1) TBC has d e l i v e r e d p r e l i m i n a r y l i s t i n g of t r a c k i n g
s t a t i o n a c q u i s i t i o n and l o s s times f o r t h e AS-503 I'D" Mission. The formal
documentation w i l l n o t be a v a i l a b l e b e f o r e e a r l y September; however, t h e
p r e l i m i n a r y d a t a (Memorandum R-AERO-FT-23-68) w i l l be s u f f i c i e n t l y a c c u r a t e
t o a l l o w t h e u s e r s t o make p r e l i m i n a r y a n a l y s e s .
(2) Because of t h e n e c e s s a r y r e p r e s s u r i z a t i o n of t h e LM,
concern developed over t h e p o s s i b i l i t y of t h e CSM/LM n o t s e p a r a t i n g from
t h e S-IVB i n time t o do t h e nominal two r e s t a r t s . Requests f o r d a t a of
t r a c k i n g and communication coverage i f t h e two r e s t a r t s were delayed f o r
a r e v o l u t i o n were honored by TBC.
These d a t a v e r i f i e d t h a t t h e coverage
was n o t a v a i l a b l e f o r t h e c r i t i c a l p e r i o d s of i n t e r e s t .
Tracking a c q u i s i t i o n and l o s s d a t a updating t h e RT
a n a l y s i s of t h e o r b i t a l and f i r s t o p p o r t u n i t y , a s w e l l a s t h e planned
second o p p o r t u n i t y , were g e n e r a t e d a t t h e r e q u e s t of I-MO, and were d i s t r i b u t e d under Memorandum R-AERO-FT-24-68.
c.
General
1. I n response t o Action Item 21.2(R.T.), a p r e s e n t a t i o n on t h e key-hole e f f e c t v e r s u s v a r i a b l e launch azimuth was g i v e n a t
t h e G&P Subpanel Metting a t MSC on June 19, 1968. The d a t a have a l s o
been d i s t r i b u t e d under Memorandum R-AERO-FT-28-68.
3.
AAP
a.
S a t u r n I B Workshop
(1) The p r i n t o u t and a n e x p l a n a t o r y memorandum were
s e n t t o t h e I&C Panel on t r a c k i n g - s t a t i o n look-angle i n f o r m a t i o n f o r t h e
AAP-2/0WS.
S i n c e t h e look a n g l e i n f o r m a t i o n i s dependent on t h e o r i e n t a t i o n of t h e OWS which is dependent upon s e v e r a l f a c t o r s , t h e look-angle
a n a l y s i s could be used a s o n l y t y p i c a l information.
(2) An approximate 20 p e r c e n t d e c r e a s e i n l i f e t i m e was
noted i n our l a t e s t s t u d y on t h e c l u s t e r m i s s i o n . These l i f e t i m e s were
based on a n e n l a r g e d s o l a r a r r a y (approximately 40% ) on t h e OWS. The
s t u d y a l s o r e f l e c t s t h e l a t e s t s o l a r d a t a , aerodynamic d a t a , i n s e r t i o n
v e c t o r (220 n.mi.), ML-14 s c h e d u l e , ecc.
�( 3 ) Data a r e being g a t h e r e d on t h e workshop t o a n a l y z e
p o s s i b l e s o l a r r a d i a t i o n e f f e c t s on t h e o r b i t a l decay and l i f e t i m e f o r
t h e c l u s t e r m i s s i o n . P r e l i m i n a r y a p p r a i s a l s i n d i c a t e t h a t t h e r e should
be no major p e r t u r b a t i o n s on our previous l i f e t i m e s t u d i e s . However,
s i n c e t h e p a y l o a d / a l t i t u d e t r a d e o f f s a r e q u i t e c r i t i c a l , we p l a n t o
check our e a r l i e r a p p r a i s a l .
b.
General
(1) AAP L i f e t i m e
A meeting was h e l d t o determine what atmospheres
should be used by t h e C e n t e r s i n AAP s t u d i e s . It was decided t h a t t h e
S p e c i a l 1962 U. S . Standard Atmosphere would be used f o r l i f e t i m e s t u d i e s ,
and t h e MSFC modified J a c c h i a 1967 model would be used f o r o t h e r AAP
s t u d i e s where atmospheric v a r i a t i o n s need t o be accounted f o r .
4.
General
a . A meeting was h e l d June 3 w i t h D r . Leland Cunningham
a t t h e U n i v e r s i t y of C a l i f o r n i a a t Berkeley t o i n i t i a t e t h e c o n t r a c t on
p a s s i v e a t t i t u d e p r e d i c t i o n . Data on t h e OWS and Pegasus A v e h i c l e s
were d e l i v e r e d t o f a c i l i t a t e h i s s t u d i e s , and t h e t a s k s and d i r e c t i o n
of approach t o t h e problem were d i s c u s s e d .
D r . Cunningham expressed h i s f e e l i n g t h a t t h e b e s t
approach t o a n a l y z i n g t h e motion of t h e OWS i s a numerical i n t e g r a t i o n
program (because of t h e s m a l l magnitudes of t h e i n i t i a l a n g u l a r r a t e s of
t h e OWS). Under previous work done f o r MSFC, D r . Cunningham developed
a numerical i n t e g r a t i o n program t o a n a l y z e t h e a t t i t u d e motion of
Pegasus A; however, MSFC d i d n o t r e q u i r e documentation of t h i s program.
T h e r e f o r e , i t was decided t h a t i n i t i a l e f f o r t on t h i s c o n t r a c t would b e
d i r e c t e d toward documenting t h i s program and a d a p t i n g i t t o perform
a n a l y s e s on t h e OWS. I f a v e r a g i n g techniques l a t e r appear t o be a usef u l approach t o t h e p a s s i v e OWS a n a l y s i s , then t h e numerical i n t e g r a t i o n
program w i l l be used t o v e r i f y t h e average s o l u t i o n s .
b. A program w r i t e u p has been r e c e i v e d from NSL on t h e
Automatic Experiment Scheduling and O p t i m i z a t i o n Program (AESOP).
Copies w i l l be d i s t r i b u t e d t o v a r i o u s Aero-Astrodynamic Laboratory
personnel a f t e r t h e document has been reviewed. We s t i l l have some
problems i n g e t t i n g t h e program t o r u n on t h e Univac 1108; however, we
f e e l t h e s e a r e n o t unsolvable problems.
�c. M r . H. Hufnagel, R-ASTR-BE, r e q u e s t e d i n f o r m a t i o n on
ground-tracking i n s t r u m e n t a t i o n a c c u r a c i e s .
M r . Hufnagel i s a member
of t h e E l e c t r o n i c T r a j e c t o r y Measurements Working Group which is under
t h e Inter-Range I n s t r u m e n t a t i o n Group Range Commanders Council. He was
i n t e r e s t e d i n t h e a c c u r a c i e s of t h e v a r i o u s r a d a r measurements (range,
aximuth, e l e v a t i o n , e t c . ) f o r USB and C-Band r a d a r s . We gave him t h e
t a b l e s of a c c u r a c i e s from t h e Apollo Navigation Working Group Technical
Report No. AN-1.3, dated December 1 5 , 1967, and informed him that t h e s e
a c c u r a c i e s met t h e ,launch t r a j e c t o r y and o r b i t r e c o n s t r u c t i o n r e q u i r e ments f o r p o s t f l i g h t e v a l u a t i o n . He was a l s o informed t h a t contitluous
coverage w i t h some redundancy was r e q u i r e d d u r i n g t h e launch phase.
d . D r . H. 3 . Zimmennan, D i r e c t o r of t h e I n s t i t u t e f o r
S c i e n t i f i c Research i n Aachen, Germany, has r e q u e s t e d a copy of t h e
p a p e r , "A Mathematical Programming Approach t o t h e Scheduling of Experiments i n Space," co-authored by M r . Fleischman and p r e s e n t e d a t t h e
TIMS
Meeting i n San Francisco.
-
C.
F l i g h t E v a l u a t i o n Branch
1.
S a t u r n LB
a.
S-IVB Workshop
R-ASTR-IE has developed a new measurement l i s t f o r
d a t a t r a n s m i s s i o n a f t e r L+7 hours on t h e S-IVB Workshop. Except f o r
l i n e a r a c c e l e r a t i o n d a t a , our i n s t r u m e n t a t i o n r e q u e s t i s s a t i s f i e d .
Horizon s e n s o r d a t a f o r determining a t t i t u d e w i l l b e recorded on t a p e
a t a sample r a t e of 1.25 samples/sec. A t t i t u d e c o n t r o l engine d a t a w i l l
n o t be recorded on t a p e , b u t i t w i l l be t e l e m e t e r e d c o n t i n u o u s l y .
R-P&VE i s a t t e m p t i n g t o have a t e l e m e t r y package added which w i l l i n c l u d e
l i n e a r accelerometer data.
A d i s c r e p a n c y was found between i n f o r m a t i o n concerning
p a s s i v a t i o n i n t h e AS-204 FEWG Report and t h e AS-204 T r a j e c t o r y Report.
The cause of t h e d i s c r e p a n c y was found t o be a gap i n t h e d a t a used t o
determine t h e a c c e l e r a t i o n p r o f i l e p r e s e n t e d i n .the T r a j e c t o r y Report.
A d d i t i o n a l d a t a were o b t a i n e d , and a n a l y s i s y i e l d e d r e s u l t s which
agreed v e r y f a v o r a b l y w i t h t h e FEWG Report. Memorandum R - A E R O - F F - ~ ~ - ~ ~
p r e s e n t s t h e r e v i s e d d a t a . S t e p s have been t a k e n t o a s s u r e t h a t t h e r e
w i l l be no d a t a gaps d u r i n g p e r i o d s of o r b i t p e r t u r b i n g a c t i v i t y
(passivation, etc.) i n the future.
�c.
S a t u r n I B 6-D T r a j e c t o r y Simulator
The o b j e c t i v e of t h i s program is t o develop a S a t u r n I B
t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom that runs from guidance
r e f e r e n c e r e l e a s e through a l l powered f l i g h t and o r b i t a l phases t o t h e
p o i n t of s p a c e c r a f t s e p a r a t i o n . This program i s intended t o f u l f i l l
our requirements f o r p r e f l i g h t and p o s t f l i g h t s t u d i e s on t h e I B v e h i c l e .
The r e q u i r e d c a p a b i l i t y i s a complete six-degrees-of-freedom t r a j e c t o r y ,
a closed-loop guidance system, and closed-loop c o n t r o l f i l t e r s . The
s t a t u s of t h e s e c a p a b i l i t i e s i n t h e program i s a s follows:
(1) Complete six-degrees-of-freedom:
A six-degrees-offreedom t r a j e c t o r y g e n e r a t e d from guidance r e f e r e n c e r e l e a s e through a l l
powered f l i g h t phases i s implemented i n t h e S a t u r n I B deck. The c a p a b i l i t y t o s i m u l a t e t h e o r b i t a l f l i g h t of t h e S-IVB s t a g e a f t e r i n s e r t i o n
u n t i l s p a c e c r a f t s e p a r a t i o n i s being developed.
(2) Closed-loop c o n t r o l f i l t e r s : The complete c l o s e d loop c o n t r o l f i l t e r system of t h e S a t u r n I B v e h i c l e has been implemented
i n t o t h e S a t u r n I B 6-D program.
( 3 ) Closed-loop guidance: The i t e r a t i v e guidance
scheme a s implemented i n t h e onboard S a t u r n I B guidance computer has
been i n c o r p o r a t e d i n t o t h e I B program i n closed-loop from guidance
r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s , which
w i l l s i m u l a t e parking o r b i t u n t i l s p a c e c r a f t s e p a r a t i o n and w i l l a l s o
have t h e c a p a b i l i t y f o r a c c e l e r o m e t e r f a i l u r e c a s e s and v e c t o r updates
t o t h e o r b i t a l n a v i g a t i o n s y s tem, a r e being implemented i n t h e deck.
2.
Saturn V
b \
a.
C l u s t e r e d Engine A n a l y s i s Computer Graphics A p p l i c a t i o n
An SSR was submitted t o t h e Boeing ~ o m p a n y / ~ u n t s v i l l e
t o i n v e s t i g a t e t h e advantages of u s i n g a g r a p h i c s d i s p l a y computer program on t h e c l u s t e r e d - e n g i n e s i m u l a t i o n method of a n a l y s i s . The g r a p h i c
d i s p l a y c a p a b i l i t y could reduce t h e manpower requirements and s h o r t e n
t h e turn-around time on s t a g e e v a l u a t i o n s . This method of e v a l u a t i o n
computes p r o p u l s i o n and t r a j e c t o r y d a t a i n t h e u s u a l manner, b u t i t
g r a p h i c a l l y d i s p l a y s prime parameters on a s c r e e n f o r o b s e r v a t i o n w h i l e
r e t a i n i n g computer d a t a . The e n g i n e e r performing t h e a n a l y s i s can make
adjustments t o p r o p u l s i o n parameters on the s p o t , and immediately s e e
g r a p h i c a l l y t h e r e s u l t s of h i s a d j u s t m e n t s . I f t h e r e s u l t s a r e n o t a s
he expected, he can add a d d i t i o n a l adjustments o r he can go back t o t h e
o r i g i n a l d a t a and t r y completely new a d j u s t m e n t s , s i n c e b o t h t h e o r i g i n a l
and a d j u s t e d d a t a a r e r e t a i n e d i n t h e computer. This procedure can be
-epeated u n t i l h i s a n a l y s i s i s s a t i s f a c t o r y . Supposedly, t h e complete
�a n a l y s i s can be performed w i t h o u t g e t t i n g o f f of t h e computer; a c t u a l l y ,
t h i s much s u c c e s s may n o t be a c h i e v e d . However, r e l a t i v e t o the time
involved i n performing t h e a n a l y s i s a s it i s being done now, i t would
appear t h a t a manpower s a v i n g s and a q u i c k e r turn-around time can be
accomplished i f t h e g r a p h i c s d i s p l a y c a p a b i l i t y can be a p p l i e d t o t h e
p r o p u l s i o n s i m u l a t i o n method. The c o s t of t h e SSR w i l l involve o n l y
e x t r a computer h o u r s ; no a d d i t i o n a l manpower i s needed.
b.
SD-53 Guidance
An e r r o r a n a l y s i s of t h e strapdown guidance i n e r t i a l
measuring u n i t (IMU) has been done. The e r r o r model f o r t h e i n d i v i d u a l
i n e r t i a l s e n s o r s i s e s s e n t i a l l y t h e same a s t h a t f o r i n s t r u m e n t s mounted
on a gimbaled system. However, t h e e f f e c t s a r e n o t t h e same i n terms of
a c c e l e r a t i o n e r r o r f e d i n t o t h e guidance computer. The strapdown a c c e l e r ometer measures a n g u l a r motion from t h e a c c e l e r o m e t e r o u t p u t s . Theref o r e , gyro e r r o r s , i n s t e a d of m i s a l i g n i n g t h e a c c e l e r o m e t e r measuring
d i r e c t i o n a s f o r a gimbal system, r e s u l t i n erroneous a d j u s t m e n t s of t h e
accelerometer outputs.
c.
AS-503 Abort and A l t e r n a t e Mission A n a l y s i s
(1)
Ground Rules
-
Complete.
-
(2) GFD
Complete e x c e p t f o r v e r i f i c a t i o n of t h e
S-11 s t a g e "Pu f a i l u r e t o t h e low s t o p f f p r o p u l s i o n p r e d i c t i o n c a s e .
(3)
Analysis S t a t u s
(a)
The document d e l i v e r y d a t e i s August 30, 1968.
(b) The nominal t r a j e c t o r y has been g e n e r a t e d , and
a few of t h e f a i l u r e c a s e s a r e b e i n g s t u d i e d . Two of t h e f a i l u r e c a s e s
f o r which p r e l i m i n a r y t r a j e c t o r i e s have been g e n e r a t e d a r e :
(1) "X" and "Z" a c c e l e r o m e t e r f a i l u r e s : Only
s i n g l e a c c e l e r o m e t e r f a i l u r e s a r e being s t u d i e d . There appear t o b e
problems i n r e a c h i n g t h e d e s i r e d e a r t h parking o r b i t should a n "X"
a c c e l e r o m e t e r f a i l d u r i n g S-IC burn. The problems seem t o be r e l a t e d
t o a n t n c o m p a t i b i l i t y between p r o p u l s i o n d a t a and t h e backup a c c e l e r o m e t e r
presettings.
F u r t h e r a n a l y s i s w i l l be made b e f o r e changes can be recommended.
(2) S - I 1 p r o p e l l a n t u t i l i z a t i o n v a l v e f a i l u r e :
The p r e l i m i n a r y c a s e s i n d i c a t e t h a t a f a i l u r e of t h e v a l v e a t 90 p e r c e n t
t h r u s t t o t h e n u l l o r low "step" p o s i t i o n would r e q u i r e a n extended S-IVB
burn t o r e a c h e a r t h parking o r b i t . The "range v e r s u s time" p l o t i n d i c a t e s
that f o r a n e a r l y PU v a l v e f a i l u r e t h e v e h i c l e w i l l be r e q u i r e d t o "dive"
t o g e t t o t h e d e s i r e d range a t i n s e r t i o n i n t o e a r t h parking o r b i t . These
�p r e l i m i n a r y t r a j e c t o r i e s must be checked o u t b e f o r e a f i r m s t a t e m e n t
can be made.
(c)
I-MO has r e q u e s t e d t h a t t h e following f a i l -
u r e c a s e s be s t u d i e d :
(1)
S-IVB 2nd and 3rd burns w i t h t h e LEM
a t t a c h e d and t h e p a n e l s detached.
(2)
S-IVB contingency burn w i t h t h e LEM
a t t a c h e d and t h e panels detached.
Data n e c e s s a r y t o compute t r a j e c t o r i e s corresponding t o Lllese f a i l u r e s
have been o b t a i n e d and t h e c o n t r a c t o r (TBC) has agreed t o a "no c o s t
I-MO would l i k e t o have t h e s e t r a j e c t o r i e s
o r schedule impact
extended t o 3 hours a f t e r S-IVB f i n a l c u t o f f (where t h e f i n a l c u t o f f
r e f e r s a l s o t o e a r l y S-IVB c u t o f f s ) . A f t e r d i s c u s s i o n s were h e l d w i t h
t h e c o n t r a c t o r (TBC) concerning t h e extended t r a j e c t o r i e s , i t was
decided t h a t t h i s a d d i t i o n a l work would be done in-house.
."
(d) I-MO a l s o r e q u e s t e d an S-111s-IVB d i r e c t
s t a g i n g t r a j e c t o r y w i t h t h e LET remaining a t t a c h e d t o t h e S-IVB s t a g e .
I-MO s t a t e d t h a t t h e r e was some disagreement between o r g a n i z a t i o n s
w i t h i n MSC concerning t h e type of a b o r t r e q u i r e d should S - I 1 i g n i t i o n
f a i l t o occur b e f o r e t h e "100 s e c - 300,000 f t a b o r t f r e e f a l l l i m i t
l i n e " i s reached.
The Abort and A l t e r n a t e Mission a n a l y s i s uses
a "six-degrees-of-freedom r i g i d body" s e t of e q u a t i o n s of motion; t h e r e f o r e , t h e s t a b i l i t y a n a l y s i s must be made u s i n g o t h e r t o o l s . R-ASTR-I,
c o n t a c t e d concerning t h e s t a b i l i t y a s p e c t , s t a t e d t h a t a n a n a l y s i s which
i s a p p l i c a b l e t o t h i s problem was made u s i n g e a r l y AS-504 v e h i c l e mass
The 504 a n a l y s i s r e v e a l e d t h a t t h e S-IVB w i t h tower
and p r o p u l s i o n d a t a .
on was only m a r g i n a l l y s t a b l e and t h e recommendation was t o j e t t i s o n t h e
LET w i t h i n 1 0 seconds of S-IVB i g n i t i o n time. They p l a n t o do a n up-tod a t e a n a l y s i s of t h e AS-503 v e h i c l e w i t h i n t h e n e x t two weeks.
d.
AS-504 and 505 Abort and A 1 t e r n a t e Mission A n a l y s i s
Ground r u l e s a r e being reviewed, and t h e GFD i s comp l e t e except f o r dual-engine-failure propulsion data.
The d e l i v e r y d a t e f o r t h e a n a l y s i s document i s October 18,
f o r 504, and December 9 f o r 505.
�e
.
Navigation Update Analys i s
An SSR was g i v e n t o TBC f o r t h i s s t u d y on June 28 and
t h e a n a l y s i s r e s u l t s a r e scheduled f o r d e l i v e r y September 30. The
AS-504 r e f e r e n c e t r a j e c t o r y w i l l be used f o r t h i s s t u d y .
f.
AS-501 P o s t f l i g h t T r a j e c t o r y
NASA TM X-53746, e n t i t l e d "Saturn AS-501 P o s t f l i g h t
Lrajeccory," has been p u b l i s h e d . The AS-502 t r a j e c t ~ r yr e p o r t , b e i n g
done by The Boeing Company, w i l l be ready f o r d i s t r i b u t i o n i n August.
g.
' S a t u r n V 6-D T r a j e c t o r y Simulator
The o b j e c t i v e of t h i s program is t o develop a S a t u r n V
t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom t h a t runs from guidance
r e f e r e n c e r e l e a s e through a l l powered f l i g h t , t h e parking o r b i t , and
w a i t i n g o r b i t phases of t h e l u n a r t r a j e c t o r y . This program i s intended
t o f u l f i l l requirements f o r p r e f l i g h t and p o s t f l i g h t s t u d i e s on t h e
Saturn V vehicle.
The r e q u i r e d c a p a b i l i t y i s a complete s i x - d e g r e e s of-freedom t r a j e c t o r y , a closed-loop guidance system, a closed-loop
p r o p e l l a n t u t i l i z a t i o n system, a closed-loop p r o p u l s i o n system, and
closed-loop c o n t r o l f i l t e r s . The s t a t u s of t h e s e c a p a b i l i t i e s i n
t h e program i s a s follows:
(1) Complete s i x degrees of freedom: A complete s i x degrees-of-freedom t r a j e c t o r y has been g e n e r a t e d from guidance r e f e r e n c e
r e l e a s e through a l l powered f l i g h t , t h e parking o r b i t , and t h e w a i t i n g
o r b i t phases of t h e l u n a r t r a j e c t o r y .
(2) Closed-loop c o n t r o l f i l t e r s : The complete c l o s e d loop c o n t r o l f i l t e r system of t h e S a t u r n V v e h i c l e i n each phase of
powered f l i g h t has been implemented i n t o t h e S a t u r n V 6-D program.
(3) Closed-loop guidance: The i t e r a t i v e guidance
scheme implemented i n t h e onboard S a t u r n V guidance computer has been
i n c o r p o r a t e d i n t o t h e S a t u r n V 6-D program i n closed-loop f r o m guidance
r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which
s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , second powered
f l i g h t , and w a i t i n g o r b i t have been p r e p a r e d , and a r e being implemented
i n t h e deck.
( 4 ) Closed-loop p r o p u l s i o n s i m u l a t i o n s y s tern and
closed-loop p r o p e l l a n t u t i l i z a t i o n system: The closed-loop PSM i s
being developed i n a p a r a l l e l 6-D program. When d e c l a r e d o p e r a t i o n a l ,
i t w i l l b e t r a n s f e r r e d t o t h e 6-D program.
C o n t r a c t NAS8-21160, which
was completed on January 12, 1968 by O R I , provided t h e p o t e n t i a l
a b i l i t y f o r closed-loop p r o p u l s i o n s i m u l a t i o n . The PSM provided by
�O R 1 was n o t completely u s a b l e because s e v e r a l r e f i n e m e n t s were needed.
S i n c e t h e above d a t e , in-house e f f o r t s t o make t h e PSM o p e r a t i o n a l have
r e s u l t e d i n t h e following:
-
The complete c o n t r o l f i l t e r
( a ) Control F i l t e r s
s i m u l a t i o n needed f o r a S a t u r n V v e h i c l e can now b e used w i t h t h e PSM.
Machine core s t o r a g e problems i n t h i s a r e a have been s o l v e d .
-
(b) Mass D i s c o n t i n u i t i e s
These a r e now handled
a c c u r a t e l y . The PSM c o n s i d e r s t h e proper d i s c o n t i n u i t y i n t h e c e n t e r of
g r a v i t y and moment of i n e r t i a computations.
-
For a more r e a l i s t i c
(c) P r e s s u r i z a t i o n Tables
s i m u l a t i o n of d i s p e r s i o n c a s e s (engine o u t , e t c . ) , p r e s s u r i z a t i o n t a b l e s
a r e now i n p u t a s a f u n c t i o n of s t a g e mass l o s s i n s t e a d of s t a g e f l i g h t
time
.
Before t h e PSM can be used i n s i m u l a t i o n s , t h e following o b j e c t i v e s must be completed:
( a ) The v a l i d i t y of t h e S-IVB p r o p e l l a n t u t i l i z a t i o n model must be v e r i f i e d . Some q u e s t i o n s a b o u t t h e completeness of
t h e e q u a t i o n s have been r a i s e d .
I
(b) The PSM must b e demonstrated i n a continuous
s i m u l a t e d f l i g h t from guidance r e f e r e n c e r e l e a s e through f i n a l S-IVB
burn. This i n v o l v e s e s t a b l i s h i n g a nominal PSM g e n e r a t e d t r a j e c t o r y
t h a t w i l l compare c l o s e l y w i t h a n o p e r a t i o n a l t r a j e c t o r y .
C o n t r a c t NAS8-21467 w i t h O R 1 was l e t June 20, 1968, t o
accomplish t h e two above o b j e c t i v e s . E f f o r t on t h e 7-month c o n t r a c t
was i n i t i a t e d J u l y 1 7 , 1968 when OR1 met w i t h R-AERO-F, R-COMP, and CSC
representatives.
h.
AS-503 Control
The AS-503 wind launch c r i t e r i a document r e c e i v e d from
TBC i s b e i n g reviewed b e f o r e p u b l i c a t i o n of t h e wind l i m i t s memorandum.
The i n f l i g h t wind speed l i m i t s f o r t h e AS-503 "D" (wind b i a s e d t r a j e c t o r y ) a t t h e most c r i t i c a l a l t i t u d e (10 km) a r e 103 m/sec, 45 mlsec,
and 29 m/sec f o r t a i l w i n d , crosswind, and headwind, r e s p e c t i v e l y , f o r
a f a c t o r of s a f e t y of 1.4.
Outboard engine c a n t was n o t c o n s i d e r e d ;
however, i t i s n o t a n t i c i p a t e d that t h i s c a n t w i l l degrade t h e wind
c a p a b i l i t y due t o reduced c o n t r o l a u t h o r i t y o r s t r u c t u r a l i n t e g r i t y .
�3.
General S t u d i e s
The s t u d y c o n t r a c t NAS8-21289, e n t i t l e d " S t u d i e s i n t h e
Theory and A p p l i c a t i o n of Kalman F i l t e r i n g , " was awarded to.UNIVAC.
The p r i n c i p a l i n v e s t i g a t o r , M r . L. Teng, is l o c a t e d i n H u n t s v i l l e f o r
t h e d u r a t i o n of t h e c o n t r a c t . The m a j o r e f f o r t t o d a t e h a s i n v o l v e d
g a t h e r i n g i n £ o r m a t i o n and s t u d y i n g t h e d e v i a t i o n s of t h e Kalman f i l t e r
and s i m i l a r methods. P a r t i c u l a r emphasis h a s b e e n p l a c e d on t h e assumpt i o n s r e q u i r e d by t h e v a r i o u s methods and d e r i v a t i o n s and how w e l l o u r
p a r t i c u l a r problem c a n s a t i s f y t h e s e a s s u m p t i o n s .
PUBLICATIONS
1.
H a u s s l e r , J. and C . L. Varnado, " S a t u r n AS-501 P o s t light T r a j e c t o r y , " NASA TM X-53746, J u n e 1 8 , 1968, U n c l a s s i f i e d .
2.
Lovingood, J . , 11Dynamical Polys ys tems as G e n e r a l i z a t i o n s o f C o n t r o l
Systems," NASA TM X-53750, J u n e 26, 1968, U n c l a s s i f i e d .
3.
Vaughan, W. W. and M. Susko, "Accuracy of Wind Data Obtained b y
T r a c k i n g a J i m s p h e r e Wind S e n s o r S i m u l t a n e o u s l y by Two FPS-Radars,"
NASA TM X-53752, J u l y 5 , 1968, U n c l a s s i f i e d .
4.
Heybey, W. H . , "Wind V e c t o r C a l c u l a t i o n s Using Crossed-Beam Data and
D e t e c t o r Arrangement f o r Measuring H o r i z o n t a l Winds , I ' NASA TM X53754, J u l y 11, 1968, U n c l a s s i f i e d .
5.
Buchannan, H. J . , "Drag on F l a t P l a t e s O s c i l l a t i n g i n I n c o m p r e s s i b l e
F l u i d s a t Low Reynolds Numbers," NASA TM X-53759, J u l y 22, 1968,
Unclass i f i e d
.
6.
-
Gold, R i c h a r d , "Nonper i a p s i s t o - P e r i a p s i s T a n g e n t i a l T r a n s f e r s i n t o
O r b i t s About Venus, Mars, and J u p i t e r , " Aero-Astrodynamics I n t e r n a l
Note R-AERO-IN-68-3, J u l y 1 9 , 1968, U n c l a s s i f i e d .
�APPROVAL
~
e t e~ i ue f
, Aero-As trodynamics L a b o r a t o r y
ero-As trodynamics L a b o r a t o r y
DISTRIBUTION
R-AERO-DIR
Dr. Geisslei
M r . Jean
Mr. B u t l e r
R-AERO-R
M r . B e a n (4)
Mrs. Hightower
R- AERO- T
Mr. Murphree
Mr. Curnmings
Dr. Heybey
Mr. J a n d e b e u r
Dr. Krause
Mr. N a t h a n
Mr. Few
M r . von P u t t k a m e r
R-AERO-P
R-AERO-D
R-AERO-G
R-AERO-Y
R-AERO-F
R-AERO-X
(8)
(16)
(6)
(8)
(8)
(4)
PAO, M r . K u r t z
R-DIR, M r . W e i d n e r
MS-H,
I-V-P,
M i s s J e r r e l l (3)
Mr. Price
�
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Saturn V Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000038
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: June - July 1968."
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Includes Technical and Scientific Staff; Advanced Studies Office; Projects Office; Aerospace Environment Division; Aerophysics Division; Astrodynamics and Guidance Theory Division; Dynamics and Flight Mechanics Division; Flight Test Analysis Division.
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George C. Marshall Space Flight Center
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1968-08-01
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1960-1969
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Saturn Project (U.S.)
NASA space programs
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Saturn V Collection
Box 27, Folder 37
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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Text
AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
April-May 1968
INDEX
Page
ADVANCED STUDIES OFFICE
.
I1
...................................
............................
...........................
..............................
.....................
........................
AEROSPACE ENVIRONMENT DIVISION
Environment Research O f f i c e
A
Space Environment Branch
B
C
Environmental A p p l i c a t i o n s Branch
D
T e r r e s t r i a l Environment Branch
.
.
.
.
AND GUIDANCE THEORY DIVISION ................
. ASTRODYNAMICS
A . Astrodynamics Branch ..................................
I11
................................
............................
PROJECTS OFFICE ...........................................
V.
AEROPHYSICS DIVISION ......................................
A . Mechanical Design O f f i c e ..............................
B . Design Branch .........................................
C . Experimental Aerophysics Branch .......................
D . Thermal Environment Branch ............................
E . Unsteady Aerodynamics Branch ..........................
V I.
DYNAMICS AND FLIGHT MECHANICS DIVISION ....................
A . M u l t i - P r o j e c t s ........................................
B . S a t u r n V ..............................................
C . AAP ...................................................
VII.
FLIGHT TEST ANALYSIS DIVISION .............................
A . S p e c i a l P r o j e c t s O f f i c e ...............................
B . F l i g h t Mechanics Branch ...............................
C . Tracking and O r b i t a l A n a l y s i s Branch ..................
D . F l i g h t E v a l u a t i o n Branch ..............................
B
C
.
.
Guidance Theory Branch
O p t i m i z a t i o n Theory Branch
1
�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
April-May 1968
I.
ADVANCED STUDIES OFFICE
A.
Miss i o n A n a l y s i s and A s trodynamics Group
1.
Unmanned P l a n e t a r y
Mission d e s i g n c h a r t s f o r t h e 1975 Mars o p p o r t u n i t y a r e
being developed f o r type I and I1 h e l i o c e n t r i c p r o f i l e s .
These d a t a
w i l l be used t o determine s p a c e c r a f t s i z i n g and Mars' c a p t u r e o r b i t
selection.
The o v e r a l l unmanned p l a n e t a r y a c t i v i t y a t MSFC has been
c u r t a i l e d f o r t h e l a s t month s i n c e M r . J i m Belew has been a s s i g n e d a s
c h i e f o f t h e Lunar Group i n t h e ASO, and a replacement t o d i r e c t t h e
unmanned p l a n e t a r y e f f o r t has n o t been d e s i g n a t e d .
2.
S-IB, T i t a n Performance and Miss i o n C a p a b i l i t y Comparison
This o f f i c e has g e n e r a t e d d a t a which w i l l d e p i c t t h e p e r formance and miss i o n payload c a p a b i l i t y comparison f o r the f o l l o w i n g
launch v e h i c l e c o n f i g u r a t i o n s :
+ Centaur as upper s t a g e
+ SM a s upper s t a g e
(1)
S-IB
(2)
S-IB
(3)
T i t a n 111 D
(4)
T i t a n 111 C .
+ Centaur
a s upper s t a g e
These d a t a w i l l be included i n t h e m a t e r i a l f o r D r . von ~ r a u n ' sp r e s e n t a t i o n t o M r . Webb on t h e f u t u r e r o l e of t h e S-IB and T i t a n 111 launch
vehicle.
Documentation of t h e performance and m i s s i o n c a p a b i l i t y
d a t a w i l l be a v a i l a b l e i n a memorandum.
�3.
JPL Double P r e c i s i o n T r a j e c t o r y Program (DPTRAJ)
A meeting was h e l d a t JPL on A p r i l 16, 1968, (1) t o f a m i l i a r i z e f u t u r e u s e r s of t h e DPTRAJ w i t h t h e c a p a b i l i t y and development
o u t l i n e , and (2) t o d i s c u s s t h e p o t e n t i a l problems of a d a p t i n g t h e program t o t h e UNIVAC 1108 computer system. Messrs. Bob E l l i s o n (R-AERO-X),
Reynolds Duncan (R-AERO-G) and P e t e Boykin (CSC) a t t e n d e d from MSFC.
The DPTRAJ w i l l be r e l e a s e d a t d i f f e r e n t phases of development. The
phase I program, which has o r b i t - t r a c k i n g c a p a b i l i t y , i s b e i n g s e n t f a
MSFC'S Computation Laboratory t h e week of June 3 , 1968.
4.
S a t u r n V Workshop
MSFC'S documentation of t h e three-month NASA Space S t a t i o n
planning s t u d y , now i n f i n a l form, i s being reviewed by t h e Advance
S t u d i e s Off i c e , Chief of R-AERO, R-ASTR and R-P&VE
Continued e f f o r t w i l l i n v o l v e (1) f i n a l rendezvous and docking p r o f i l e a n a l y s i s , (2) space-s t a t i o n crew r e s c u e modes and t h e i r
implementation, and ( 3 ) atmospheric e n t r y a n a l y s i s t o d e f i n e e n t r y
c o r r i d o r s and s u r f a c e f o o t p r i n t a r e a s .
B.
F l i g h t Mechanics and Performance A n a l y s i s Group
The problems and manpower requirements a s s o c i a t e d w i t h t h e
i n t e g r a t i o n of t h e CSM o n t o t h e T i t a n 111 M a r e b e i n g a n a l y z e d . Before
t h e T i t a n I11 could be used f o r manned f l i g h t by NASA, i t would be
n e c e s s a r y t o r u n some q u a l i f i c a t i o n s s t u d i e s i n t h e f i e l d s of a e r o dynamics, thermodynamics, f 1i g h t mechanics, guidance, c o n t r o l and
v e h i c l e dynamics.
This o f f i c e i s s u p p o r t i n g t h e p r e s s u r e - f e d launch v e h i c l e study,
d i r e c t e d by M r . Laue, and t h e S a t u r n u t i l i z a t i o n s t u d y .
General f l i g h t mechanical s t u d i e s w i t h r e s p e c t t o s t a g e s i z i n g ,
module s i z e , and o v e r a l l performance e v a l u a t i o e a r e i n p r o g r e s s .
C.
Systems A n a l y s i s Group
1. The t e c h n i c a l i m p l i c a t i o n s of c o n v e r t i n g AS-210 t o a S a t u r n V
launched m i s s i o n w h i l e r e t a i n i n g i t s S a t u r n I Workshop backup s t a t u s a r e
b e i n g e v a l u a t e d . The i n i t i a l s t e p i s a n assessment of t h e impact of t h i s
Light payload (= 63,500 l b s ) on t h e launch v e h i c l e , a s w e l l a s t h e impaet
of t h e S a t u r n V launch environment on t h e workshop. P r e l i m i n a r y t r a j e c t o r y and aerodynamic d a t a f o r t h i s c o n f i g u r a t i o n have been g e n e r a t e d ,
.
�A wind r e s p o n s e a n a l y s i s has been completed, and t h e r e s u l t i n g c o n t r o l
data have been t r a n s m i t t e d t o R-P&VE-AV f o r load c a l c u l a t i o n s . The
l o a d s d a t a on t h e workshop have been s e n t toMSC f o r t h e i r assessment
of t h e impact on t h e workshop. The impact of t h e l i g h t payload on t h e
launch v e h i c l e s t r u c t u r e w i l l be e v a l u a t e d a t M a r s h a l l .
2. The Boeing Company has begun f a b r i c a t i o n of a low c o s t p r e s s u r e - f e d "Ground Demonstration Stage" (GDS). The 8 112-foot diameter
s t a g e i s t o be mated w i t h t h e TRW s c a l e d - u p LEMDE engine. T h r u s t of
t h e TRW engine i s 250,000 pounds, f i r i n g d u r a t i o n is t o be 120 seconds,
p r o p e l l a n t s a r e N204/U~MH, t a n k s t r u c t u r e i s HY 140 s t e e l , t a n k p r e s s u r e i s 390 p s i , and engine p r e s s u r e i s 300 p s i . The p r e s s u r i z a t i o n
scheme f o r t h e GDS c o n s i s t s of p a s s i n g H202 over a c a t a l y s t f o r t h e
N,94 tank p r e s s u r e and UDMH over a c a t a l y s t f o r the UDMH tank p r e s s u r e .
T e s t t a r g e t d a t e i s November 1968.
11,
AEROSPACE ENVIRONMENT DIVISION
A.
Environment Research O f f i c e
1. M r . 0. H. Vaughan reviewed Surveyor program r e p o r t s and
o t h e r l i t e r a t u r e on t h e l u n a r s u r f a c e and environment. Also, d i s c u s s i o n s were h e l d w i t h D r . C. Wys, of JPL, a b o u t h i s M a r t i a n S u r f a c e
Monograph. L i t e r a t u r e surveys of t h e thermal environment of Mercury
and Mars c o n t i n u e d .
2. M r . Dalton has surveyed many books, r e p o r t s , and papers
f o r p o s s i b l e r e l a t i o n t o h i s comparative a n a l y s i s of two sub-samples
of 333 s p o r a d i c photographic meteors ( s e l e c t e d f o r minimum a b s o l u t e
magnitude h y p o t h e t i c a l l y s c a l e d f o r escape v e l o c i t y by a l t e r n a t i v e
f r o m u l a t i o n s of luminous e f f i c i e n c y )
The o u t 1 i n e f o r t h i s a n a l y s i s
was p r e s e n t e d by M r . Dalton at: t h e Research Achievements Review h e r e
on September 28 (NASA Technical Memorandum X-53706). About one
hundred of t h o s e which were s t u d i e d were found t o be p e r t i n e n t r e f e r cnccs f o r t h i s purpose. This e f f o r t has been r e s t r i c t e d t o n o t more
t h a n h a l f of M r . ~ a l t o n ' s r e g u l a r hours t o i n s u r e a more a c t i v e
involvement i n b r o a d e r a r e a s of s p a c e p h y s i c s , mathematics and
s t a t i s t i c s , and a e r o s p a c e environment r e s e a r c h .
.
3.
Atmospheric Research F a c i l i t y
During t h i s p e r i o d , 100 rawinsonde f l i g h t s were made by
t h e MSFC Atmospheric Research F a c i l i t y . A l l b u t f o u r of t h e s e f l i g h t s
were made i n s u p p o r t of t h e s t a t i c f i r i n g s conducted by T e s t Laboratory.
�The CPS-9 Weather Radar has been down a g r e a t d e a l of t h e
time d u r i n g t h i s r e p o r t i n g p e r i o d . S e v e r a l u n i t s developed t r o u b l e s
which seemed t o s p r e a d throughout t h e system. Major problems occurred
w i t h t h e magnatron, p u l s e c a b l e and p u l s e c a p a c i t o r , and t h e p u l s e
t r a n s f o r m e r and t h e d r i v e motor i n t h e modulator. These m a l f u n c t i o n s
have beefi c o r r e c t e d and t h e system i s now o p e r a t i o n a l . A CPS-9 Radar/
thunders t o m s t u d y b e i n g p e r f brmed by R-AERO-YE was i n l t i a ted t h i s
p e r i o d . This s t u d y w i l l use wind d a t a from 1 4 anemometer i n s t a l l a t i c l r t s
w i t h i n a f i v e - m i l e r a d i u s of t h e r a d a r s i t e and t h e p i c t u r e s from t h e
cPS-9 PPI: scope. These d a t a w i l l b e c o r r e l a t e d w i t h thunders tam a c t i v i t y
as i t p a s s e s through<t h e a r e a .
The ionosphere stari'on is o p e r a t i o n a l , and has been o p e r a t e d
d u r i n g a l l s t a t i c t e s t s t h i s p e r i o d . Data were recorded by b o t h t h e
scope-mounted p o l a r o i d and t h e 35-mm cameras. These d a t a were f ~ r w a r d e d
t o R-AERO-YS f o r p r o c e s s i n g .
The MSFC c l i m a t o l o g i c a l d a t a , cons i s t i n g of h o u r l y temperat u r e , humidity, p r e s s u r e , wind d i r e c t i o n , and wind speed d a t a d a t i n g
from October 1961 t o t h e p r e s e n t has been reduced, t a b u l a t e d , and s e n t
t o t h e Computation Laboratory t o be keypunched and s t o r e d on magnetic
tape f o r f u t u r e reference.
The Atmospheric Research F a c i l i t y has s u p p o r t e d s e v e r a l
l a b o r a t o r i e s w i t h meteo'rological equipment and d a t a i n t h e f o l l o w i n g
areas :
(a) An instrument s h e l t e r , h y g r o t h e m g r a p h , and a comp l e t e aerovane system i n c l u d i n g a tower were i n s t a l l e d f o r Space Sciences
L a b o r a t o r y a t t h e l r Radio As t r o n m y s i t e .
(b) An i n s t r u m e n t s h e l t e r and hygrothesthograph were
i n s t a l l e d f o r t h e Experimental Aerophys i c s Branch t o provide temperature
measurements a t t h e High Reynolds Number F a c i l i t y .
(c) Test U b o t a t 6 r y r e q u e s t e d , and was provided w i t h ,
r e l a t i v e humidity d a t a f o r a l l s t a t i c t e s t f i r i n g s dating back t o
e a r l y 1964.
(d) An Aerovane Sys tem was i n s tsllled a t t h e West F-1 T e s t
Stand a t the r e q u e s t of R-P&VE.
( e ) The A m y ' s Range 1 was provided w i t h m a t e r i a l f o r
c a l i b r a t i o n of t h e i f l a r g e r a d a r systems.
(f)
llg" e x p e r h e n t *
Support wag provided Q u a l i t y Laboratory i n t h e i r z e r o
�(g) T e s t Laboratory' s Hydrogen Hand1 ing F a c i l i t y was
provided i n f o r m a t i o n concerning l i g h t n i n g a c t i v i t y i n t h e a r e a .
(h) The dynamic wind s t a n d and d a t a a c q u i s i t i o n system
were moved d u r i n g t h i s p e r i o d . The s t a n d was moved t o t h e open f i e l d
s o u t h of Bldg. 4614, and t h e r e c o r d i n g equipment was moved t o a r a d a r
van i n t h e same a r e a . S e v e r a l t e s t s have been conducted on f o u r Climets
and t h e d a t a s e n t t o Computation Laboratory f o r r e d u c t i o n . More t e s t s
a r e scheduled f o r t h e summer months.
The Easterline-Angus S t r i p C h a r t Recorders a t t h e 150-meter
m c t c o r o l o g i c a l tower a t KSC a r e beginning t o show t h e e f f e c t of c o n t i n u ous o p e r a t i o n s . The take-up r e e l s were r e p l a c e d d u r i n g t h i s p e r i o d , and
arrangements a r e being made t o have a l l t h e s e r e c o r d e r s e i t h e r r e p l a c e d
o r r e b u i l t . With t h e e x c e p t i o n of t h e r e c o r d e r s , a l l o t h e r equipment
and s e n s o r s a r e f u n c t i o n i n g satis f a c t o r i l y , and continuous wind and temp e r a t u r e d a t a a r e b e i n g a c q u i r e d from t h e 150-meter tower.
B
.
Space Environment Branch
S t u d i e s r e l a t e d t o t h e s t r u c t u r e and v a r i a b i l i t y of t h e thermos p h e r e have been d i r e c t e d t o (1) t h e documentation of t h e "MSFC S t a t i c
D i f f u s i o n Model (1967) ," (2) t h e d e t a i l e d a n a l y s i s of s i x MSFC thermosphere
probes, ( 3 ) t h e development of t h e "MSFC Thermosphere Model (1968)
P r e l i m i n a r y , " and ( 4 ) t h e e s t a b l i s h m e n t of t y p i c a l atmospheric d e n s i t y time p r o f i l e s f o r ATM environment c r i t e r i a .
-
The "MSFC S t a t i c D i f f u s i o n Model (1967)" i s b a s i c a l l y a comp u t e r i z e d v e r s i o n of J a c c h i a ' s S t a t i c D i f f u s i o n Model w i t h Walker's
This
d i f f u s i o n e q u a t i o n used i n p l a c e of ~ a c c h i as' t a b l e look-up.
model i s documented i n d e t a i l i n memorandum R-AERO-YS-160-68.
The
documentation c o n t a i n s no new changes t o t h e model; i t i s provided
mainly t o a s s i s t o t h e r ' d i v i s i o n s / l a b o r a t o r i e s i n t h e i n c o r p o r a t i o n of
t h e model i n t h e i r e n g i n e e r i n g programs. A f t e r a d e t a i l e d comparative
a n a l y s i s , we have found t h i s model t o b e s t d e f i n e t h e environment c r i t e r i a
f o r a l l engineering studies
However, t h i s model, l i k e ~ a c c h i as' , is
s e r i o u s l y handicapped by t h e assumed c o n s t a n t boundary c o n d i t i o n s a t
120 h.
.
A d e t a i l e d a n a l y s i s of s i x MSFC thermosphere probes, launched
January 24, 1967, has provided a d d i t i o n a l i n f o r m a t i o n concerning t h e
d i u r n a l v a r i a t i o n s of t h e thermosphere. This i n f o r m a t i o n w i l l b e used
t o e s t a b l i s h v a r i a b l e boundary c o n d i t i o n s a t 120 km a l t i t u d e and t h e r e b y
r e f i n e our p r e s e n t atmospheric model. A p r e l i m i n a r y computer program
1~11ichhas been w r i t t e n f o r t h i s new atmospheric model w i l l be used as a
f o c a l p o i n t f o r s u p p o r t c o n t r a c t o r and NASA s m e r employee s t u d i e s .
This computer program is d e s c r i b e d i n memorandum R-AERO-YS-157-68.
�Typical atmospheric d e n s i t y - t i m e p r o f i l e s which have been
e s t a b l i s h e d f o r a 28-day ATM m i s s i o n a r e provided i n memorandum
R-AERO-YS-153-68.
A s i m i l a r p r o f i l e f o r a 56-day m i s s i o n w i l l be
completed soon.
P r e l i m i n a r y d i s c u s s ions have been completed w i t h t h e Space
Sciences Laboratory r e l a t i v e t o t h e 1968 r e v i s i o n of NASA TM X-53521,
"Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development 1967 Revision," which i s p r o g r e s s i n g on s c h e d u l e . The new r e v i s i o n
w i l l c o n t a i n a more d e t a i l e d d i s c u s s i o n of t h e e a r t h ' s upper atmosphere,
r e v i s e d atmospheric models f o r Mars and Venus, r e f i n e d and expanded
d a t a concerning t h e s u r f a c e s of Mars and t h e Moon, and expanded r a d i a tion data.
P a r t I of t h e atmospheric d e n s i t y d e t e r m i n a t i o n program i s
almost completed. This program w i l l be used t o compute atmospheric
d e n s i t i e s from s a t e l l i t e o r b i t d a t a which w i l l be used i n t h e development of t h e MSFC Thermosphere Model (1968). R-AERO-FT w i l l provide
s u p p o r t i n t h e o r b i t d e t e r m i n a t i o n a r e a , and t h e e q u a t i o n s i n t h e i r
program a r e being s t u d i e d .
Upper Atmospheric Dynamics
A newphase i n t h e s t u d y of T r a v e l i n g I o n o s p h e r i c Disturbances
(TID'S) i s being unaertaken i n c o n j u n c t i o n w i t h t h e Aeronomy Laborat o r y a t ESSA. A new instrument c a l l e d a "kinesonde" has been developed
by ESSA which provides d a t a on i o n o s p h e r i c motions u s i n g t h e s i g n a l
f a d i n g p r i n c i p l e . M r . J. W. Wright of ESSA has o f f e r e d t o c o l l e c t
d a t a a t MTF d u r i n g times of s t a t i c t e s t f i r i n g s of t h e SIC t o i n c o r p o r a t e i n t o our a c o u s t i c g r a v i t y wave s t u d y program. The d a t a would
be of obvious i n t e r e s t t o our s t u d y and would a l s o p r o v i d e M r . Wright
w i t h e x t e n s i v e d a t a and e x p e r i e n c e w i t h which t o f u r t h e r develop t h e
techniques r e q u i r e d i n d a t a c o l l e c t i o n , a n a l y s i s , and i n t e r p r e t a t i o n .
We a r e c u r r e n t l y a t t e m p t i n g t o provide M r . Wright w i t h a n antenna
a r r a y and power s o u r c e a t MTF.
Solar Activity Prediction
A r e c e n t v i s i t t o t h e 4 t h Weather Wing i n Colorado S p r i n g s , t h e
S o l a r F o r e c a s t F a c i l i t y a t NORAD, and t h e ESSA Boulder L a b o r a t o r i e s have
served t o emphasize t h e d i f f i c u l t y of f o r e c a s t i n g s o l a r a c t i v i t y .
Solar
f l a r e s a r e r e l a t i v e l y e a s y t o p r e d i c t i n l o c a t i o n on t h e s o l a r d i s k ; howe v e r , i t i s v i r t u a l l y impossible t o p r e d i c t t h e s i z e , d u r a t i o n , and time
of s o l a r a c t i v i t y
of the f l a r e . Long range p r e d i c t i o n -- a y e a r o r more
Even
though t h e
i s v i r t u a l l y impossible u n l e s s we can d e r i v e t h e c a u s e s .
c
e
n
t
e
r
of
mass
t
h
e
o
r
i
e
s
l
e
a
d
t
o
long
range p r e p l a n e t a r y p e r t u r b a t i o n and
d i c t i o n s of s o l a r a c t i v i t y which a r e b o r d e r l i n e , t h e a c c e p t e d p r e d i c t i o n
--
�of s o l a r a c t i v i t y t h r e e t o f o u r days i n advance i s n o t r e a l l y that much
b c t t c r . Research needs t o be i n c r e a s e d i n view of t h e importance of
t h c s c p r e d i c t i o n s t o o u r o r b i t a l l i f e t i m e and dynamic p r e d i c t i o n s .
C.
Environmental A p p l i c a t i o n s Branch
1.
A n a l y s i s of Atmospheric Turbulence from FPS-16 Radar/
Jimsphere Data (NASA C o n t r a c t No. NAS8-21331 w i t h
Meteorology Research, I n c . )
Work on t h i s c o n t r a c t is p r o g r e s s i n g smoothly. Approximately 95 p e r c e n t of t h e d a t a t o perform t h e c o n t r a c t has been r e c e i v e d
by t h e c o n t r a c t o r .
The d a t a that w i l l be analyzed by t h e c o n t r a c t o r
i n c l u d e s (1) n i n e Jimsphere p r o f i l e s observed over Wallops I s l a n d w i t h
a s s o c i a t e d p i l o t r e p o r t s f o r t h e month of December 1967, (2) two
sequences of Jimsphere d a t a c o n t a i n i n g approximately 15 wind p r o f i l e s
and each s e p a r a t e d i n time by one and one-half h o u r s , and (3) twelve
c h a r t r o l l s which c o n t a i n t u r b u l e n c e d a t a o b t a i n e d by a n instrumented
a i r c r a f t over Wallops I s l a n d d u r i n g February and March 1968. The
a i r c r a f t d a t a mentioned i n item (3) i n c l u d e t r u e a i r speed, a l t i t u d e ,
a c c e l e r a t i o n of t h e c e n t e r of g r a v i t y of t h e a i r c r a f t , r o l l and p i t c h
a n g l e s and a n g l e of a t t a c k .
The c o n t r a c t o r i s now p r o c e s s i n g t h e Jimsphere d a t a t o
determine t h e r e s o l v i n g power of t h e Jimsphere b a l l o o n f o r v e r t i c a l
l e n g t h s c a l e s l e s s than 25 m.
This i n f o r m a t i o n needs t o be e s t a b l i s h e d
i n o r d e r t o determine i f t h e Jimsphere b a l l o o n i s capable of y i e l d i n g
d a t a t h a t can be used t o determine t h e spectrum of t u r b u l e n c e i n t h e
i n e r t i a l subrange s o t h a t v i s c o u s d i s s i p a t i o n r a t e s can b e determined.
The v i s c o u s d i s s i p a t i d n r a t e is a key parameter i n a t m o s p h e r i c t u r b u l e n c e , and i t perhaps could be used a s a n i n d i c a t o r of t h e i n t e n s i t y
of t u r b u l e n c e .
2.
F i n a l Report on C o n t r a c t NAS8-21138 w i t h NAR
The f i n a l r e p o r t , "Wind F i e l d A n a l y s i s f o r C a n t i l e v e r Loads,"
has been r e c e i v e d i n a c c e p t a b l e form. This work was completed by North
American Rockwell C o r p o r a t i o n , Downey, C a l i f o r n i a , on which Ben U j i h a r a
was t h e p r i n c i p a l i n v e s t i g a t o r . The r e p o r t , being p u b l i s h e d a s a NASA CR,
w i l l be d i s t r i b u t e d by R-AERO-Y.
Wind d a t a from t h e 500F t e s t s were used
t o i l l u s t r a t e pad wind flow c o n d i t i o n s and flow a b o u t t h e ~ ~ ~ / ~ e h i c l e .
�3.
F a s t Response Anemometer
Twenty-five p r o p o s a l s were r e c e i v e d i n r e p l y t o a n RFP f o r
t l ~ cdevelopment of a £as t response anemometer. This anemometer w i l l be
used t o o b t a i n d a t a f o r f r e q u e n c i e s > 1 cps t o be used i n s e l e c t e d
s t r u c t u r a l r e s p o n s e s t u d i e s and aerodynamic s c a l i n g a n a l y s i s . The
p r o p o s a l s have been e v a l u a t e d and a c o n t r a c t o r t e n t a t i v e l y s e l e c t e d .
N e g o t i a t i o n w i t h t h e p r o s p e c t i v e c o n t r a c t o r should t a k e p l a c e soon, Tf
t h e p r o s p e c t i v e c o n t r a c t o r a g r e e s t o meet c e r t a i n c o n d i t i o n s added t o
t h e proposed development, work should begifi on t h e anemometer w i t h i n a
few weeks.
4.
Recent Reports on NASA1 s 150 m M e t e o r o l & i c a l
Facility
Tower
Two r e p o r t s have r e c e n t l y been made a v a i l a b l e on NASA's
150 m M e t e o r o l o g i c a l Tower l o c a t e d a t KSC, F l o r i d a :
(1) GP-465
e n t i t l e d , "Meteorological Measuring and Recording Equipment Descript i o n , C a l i b r a t i o n and Maintenance Procedures f o r NASA's 150 m Meteorol o g i c a l Tower F a c i l i t y , Kennedy Space C e n t e r , F l o r i d a , " d a t e d February 15,
1968; and (2) NASA
X-53699 e n t i t l e d , "NASA's150 m M e t e o r o l o g i c a l
Tower Located a t t h e Kennedy Space C e n t e r , F l o r i d a , " d a t e d January 1968
( r e v i s e d ) . Copies of t h e s e r e p o r t s may be o b t a i n e d by c o n t a c t i n g
R-AERO-YE, A t tn: John W. Kaufman (6-6392).
5.
Winds Which Adversely A f f e c t Vehicle Operations
( C o n t r a c t NAS8-21292)
M r . Joseph Goldman, p r i n c i p a l i n v e s t i g a t o r under c o n t r a c t
NAS8-21292, of t h e U n i v e r s i t y 6f S a i n t Thomas (UST) v i s i t e d t h e Aeros p a c e Environment D i v i s i o n on A p r i l 1 2 t h t o c o o r d i n a t e and d i s c u s s work
t o be done on t h e c o n t r a c t e n t i t l e d , "Analysis of Wind F i e l d Conditions
which Adversely A f f e c t Vehicle Operations."
It was agreed t h a t t h e
( I ) L i t e r a t u r e survey on t h e
f o l l o w i n g work would b e completed by UST:
s t a t e - o f - t h e - a r t of r e s e a r c h on winds a s s o c i a t e d t o thunderstorms
( l i g h t n i n g , h a i l , s t o r m d u r a t i o n , e t c . ) w i l l b e reviewed.
(2) UST
w i l l develop a t h e o r e t i c a l model and e m p i r i c a l model a s developed from
a c t u a l atmospheric d a t a o b t a i n e d d u r i n g t h e occurrence of thunders torms
(some of t h e s e d a t a w i l l be from NASA's 150 m ~ e t e o r ' o l o g i c a l Tower a t
ICSC).
(3) UST w i l l e v a l u a t e t h e s p e c t r a l a a a l y s i s of wind d a t a a c q u i r e d
(Data a c q u i r e d a t NASA's 150 m M e t e o r o l o g i c a l
d u r i n g thunders torms a t KSC.
Tower w i l l be analyzed a t MSFC.)
( 4 ) F o r e c a s t techniques of wind a s s o c i a t e d t o thunderstorms, from t h e s y n o p t i c - t o m i c r o - s c a l e , w i l l be
documented.
(5) UST w i l l provide recommendations on f u t u r e d a t a r e q u i r e ments t o s t u d y thunders torms a t KSC. R e s u l t s of t h i s s t u d y a r e t d prov i d e a d d i t i o n a l environmental c r i t e r i a on s e v e r e s t o m s a s r e q u i r e d
f o r d e s i g n and A p o l l o / S a t u r n v e h i c l e o p e r a t i o n s . M r . Goldmn v i s i t e d
�KSC on May 21-22, 1968. The purpose of t h i s v i s i t was to-become f a m i l i a r
w i t h KSC wind s e n s o r f a c i l i t i e s and l o c a l t e r r a i n e s p e c i a l l y i n t h e
v i c i n i t y of Launch Complexes 37 and 39.
6.
Revised MSFC Peak Wind Design Envelope
A r e v i s e d MSFC peak ground wind speed envelope v a l i d f o r
KSC has been developed by R-AERO-YE.
This wind envelope w i l l s u p e r s e d e
t h c envelope c o n s t r u c t i o n d a t a g i v e n f o r E a s t e r n T e s t Range a s shown i n
t a b l e s 5.6A, 5.6B7 and 5.6C on pages 5.21 and 5.22 i n " ~ e r r e tsr i a l
Environment ( C l i m a t i c ) C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle
~ e v e l o p m e n t , 1966 Revision,'' NASA TM X-53328.
The new d e s i g n wind
envelope i s g i v e n by
where u ( h ) i s t h e peak wind speed a t h e i g h t h ( i n m e t e r s ) above n a t u r a l
g r a d e , and ulaa3 i s a known peak wind speed a t h = 18.3 m e t e r s . The
parameter, k, i s g i v e n by
Thus, upon s p e c i f y i n g t h e peak wind a t
is i n m sec-l.
where u18.
11 = 18.3 m sec'l, t h e peak wind p r o f i l e w i l l be completely s p e c i f i e d .
However, i n o r d e r t o a c c o u n t f o r t h o s e c a s e s i n which peak wind d a t a a r e
g i v e n a t h e i g h t s o t h e r 'than a t 18.3 m e t e r s , R-AERO-YE has developed a
t a b l e of peak wind p r o f i l e s f o r a wide range of peak wind speed
conditions.
7.
I n v e s t i g a t i o n of t h e Turbulent Wind F i e l d Below 500 F e e t
A l t i t u d e a t t h e E a s t e r n T e s t Range, F l o r i d a (NASA
C o n t r a c t NAS8-21140)
This c o n t r a c t , which i s being performed by t h e Pennsylvania
S t a t e U n i v e r s i t y (PSU) i s p r o g r e s s i n g smoothly i n a l l a r e a s . The cont r a c t o r i s now a n a l y z i n g t h e coherence f u n c t i o n of t u r b u l e n c e and t h e
s t a t i s t i c s of t h e l o n g i t u d i n a l and l a t e r a l wind f l u c t u a t i o n s of turbul e n c e i n t h e f i r s t 150 m of t h e atmosphere a t KSC. The c o n t r a c t o r found
t h a t t h e coherence of t h e l o n g i t u d i n a l component of t u r b u l e n c e a t KSC
i s v e r y s i m i l a r t o t h a t found a t Brookhaven, New York, w h i l e i t d i f f e r s
somewhat from t h a t observed a t White Sands, New Mexico. The s t a t i s t i c a l
s t u d i e s a r e aimed a t determining t h e d i s t r i b u t i o n f u n c t i o n of t h e wind
J,
�.
I n a d d i t i o n , t h e s t a t i s t i c a l s t u d i e s w i l l determine the
clcgrcc 01 d e p a r t u r e of t h e t u r b u l e n c e from a Gaussian p r o c e s s . A t the
p r e s e n t time, i t a p p e a r s t h a t t h e l o n g i t u d i n a l component of t u r b u l e n c e
i s almost a Gaussian p r o c e s s , w h i l e t h e l a t e r a l component t u r b u l e n c e
has a bimodal d i s t r i b u t i o n f u n c t i o n . The bimodal c h a r a c t e r of t h e
l a t e r a l d i s t r i b u t i o n i s due t o t h e t u r n i n g of t h e s t e a d y - s t a t e wind
p r o f i l e w i t h h e i g h t (Ekman l a y e r ) i n t h e atmospheric boundary l a y e r .
f 1 uctuations
8.
A n a l y s i s of Ground Wind F i e l d A n a l y s i s f o r Design
and Operation of Space Vehicles ( C o n t r a c t NAS8-21178)
This c o n t r a c t i s being performed by C o r n e l l A e r o n a u t i c a l
L a b o r a t o r i e s (CAL) of B u f f a l o , New York. During t h i s p e r i o d , CAL
r e c e i v e d t h e l a s t shipment of d a t a t o complete t h e c o n t r a c t . The main
emphasis d u r i n g t h i s p e r i o d was placed upon p r e s c r i b i n g l a t e r a l spectrum
of t u r b u l e n c e f o r launch v e h i c l e response c a l c u l a t i o n s . F i n a l r e s u l t s
a r c n o t y e t a v a i l a b l e , CAL has r e q u e s t e d a three-month no-cost extens i o n t o complete t h e c o n t r a c t , because of unavoidable d e l a y s i n programming and compute_ p r o c e s s i n g . This means t h a t t h e c o n t r a c t w i l l n o t
be completed u n t i l September 30, 1968.
9.
P r e l a u n c h Monitorship Program
The M a r t i n - M a r i e t t a Corporation (Denver) i s developing a
p r e l a u n c h m o n i t o r i n g program, which w i l l p r e d i c t t h e i n - f l i g h t l o a d s
a t launch time based upon t h e wind p r o f i l e seven hours b e f o r e launch of
a S a t u r n V launch v e h i c l e and c e r t a i n KSC i n - f l i g h t wind s t a t i s t i c s .
I n o r d e r t o develop t h i s program t h e Martin-Marietta C o r p o r a t i o n
r e q u i r e s wind s t a t i s t i c s f o r KSC t h a t d e s c r i b e (1) t h e wind d i r e c t i o n
and speed v a r i a t i o n s i n t h e 10-15 krn a l t i t u d e r e g i o n , (2) t h e v a r i a t i o n s
i n a l t i t u d e of t h e l e v e l of maximum wind i n t h e 10-15 km a l t i t u d e r e g i o n ,
and ( 3 ) t h e p e r s is t e n c e s t a t i s t i c s of in-£1 i g h t t u r b u l e n c e s p e c t r a . To
determine t h e s p e c i f i c s t a t i s t i c s needed by t h e c o n t r a c t o r , a meeting
was h e l d on May 29, 1968, a t MSFC w i t h M a r t i n - M a r i e t t a Corporation.
The a t t e n d e e s were Messrs. Vaughan, K a u h a n , H i l l , and F i c h t l of
R-AERO-Y and M r . Wilkining of t h e M a r t i n - M a r i e t t a C o r p o r a t i o n , and
M r . R. Ryan and Mrs. A . King ( c o n t r a c t o r monitor) of R-AERO-DD.
Wind
speed p e r s i s t e n c e s t a t i s t i c s have been s u p p l i e d t o M a r t i n - M a r i e t t a
Corporation f o r t h i s s t u d y . Computer programs t o c a l c u l a t e t h e o t h e r
At
s t a t i s t i c s mentioned above a r e now being w r i t t e n by.R-COMP-RRP.
t h i s s t a g e , i t was decided t o c o n c e n t r a t e on s t a t i s t i c a l p r e d i c t i o n s
of wind p r o f i l e c h a r a c t e r i s t i c s ( t u r b u l e n c e , s h e a r s , wind s p e e d s ) and
v e h i c l e responses t h e r e t o .
�10.
Jimsphere Temperature Sensor (NASA C o n t r a c t NAS8-20588)
Work on a temperature s e n s o r f o r t h e Jimsphere b a l l o o n
has recommenced. The c o n t r a c t o r i s t h e GCA C o r p o r a t i o n of Bedford,
Massachusetts.
This c o n t r a c t w i l l be completed i n a b o u t s i x months.
This f i n a l phase of t h e c o n t r a c t w i l l be concerned w i t h performing a
d e t a i l e d e r r o r a n a l y s i s of t h e temperature s e n s o r system.
11.
T r a i n i n g on M e t e o r o l o g i c a l Sensors
M r . Wade P e r r y a t t e n d e d a t r a i n i n g
s e n s o r s (wind s e n s o r s ) and a s s o c i a t e d equipment
ments, I n c . f a c i l i t y a t Sunnyvale, C a l i f o r n i a .
r e s p o n s i b l e f o r r e p a i r i n g wind s e n s o r s t h a t a r e
150 m M e t e o r o l o g i c a l Tower F a c i l i t y a t KSC.
D.
c o u r s e on m e t e o r o l o g i c a l
a t t h e Climet I n s t r u M r . P e r r y w i l l soon be
being used a t t h e NASA
T e r r e s t r i a l Environment Branch
1. The major t a s k of f i t t i n g a n extreme v a l u e f u n c t i o n t o t h e
Cape Kennedy peak wind speeds i s n e a r i n g completion.
2. M r . 0. E. Smith p r e s e n t e d a paper e n t i t l e d , "Atmospheric
S t a t i s t i c s f o r Aerospace Vehicle Design, Mission Planning and Operat i o n s , " a t t h e Third N a t i o n a l Conference on Aerospace Meteorology,
May 6-7, 1968, a t New Orleans. The meeting was sponsored by t h e
American M e t e o r o l o g i c a l S o c i e t y , t h e American I n s t i t u t e of Aeronautics
and A s t r o n a u t i c s Committee on Atmospheric Environment, and t h e I n s t i t u t e
of Environmental S c i e n c e s .
3 . Standard ' d e v i a t i o n s of p r e s s u r e , t e m p e r a t u r e , and d e n s i t y
t o 120 km w i t h r e s p e c t t o t h e 1963 P a t r i c k Reference Atmosphere were
published i n memorandum R-AERO-YT-27-68, d a t e d A p r i l 4 , 1968, t o provide
atmospheric d a t a f o r u s e i n t r a j e c t o r y h e a t i n g s t u d i e s .
4. Considerable work on background m a t e r i a l f o r LOX and f u e l
temperature p r e d i c t i o n s was done. Although no s a t i s f a c t o r y s o l u t i o n
t o t h e p r e d i c t i o n problem was developed, e r r o r s i n t h e proposed C h r y s l e r
method were d i s c o v e r e d i n time t o p r e v e n t e x t e n s i v e work a l o n g unprod u c t i v e l i n e s . To e n i b l e a l l concerned t o b e t t e r understand t h e problem,
a c o o r d i n a t i o n meeting was h e l d i n New Orleans w i t h C h r y s l e r Corporation
Space D i v i s i o n and P&VE personnel on May 6 .
�The f i r s t of s e v e r a l computer programs being developed f o r
5.
use w i t h t h e World-Wide Cloud Cover S t a t i s t i c s was completed a t t h e end
of May. S e v e r a l a d d i t i o n a l computer programs w i l l be r e q u i r e d t o make
f u l l use of t h e cloud s t a t i s t i c s i n miss i o n s i m u l a t i o n e x e r c i s e s ; howe v e r , some b a s i c m a t e r i a l u s e f u l i n m i s s i o n a n a l y s i s s t u d i e s can be
f u r n i s h e d now. A memorandum c o n t a i n i n g cloud s t a t i s t i c s f o r t h e E a r t h
Resources Experiment was i s s u e d on May 24, 1968, R-AERO-YT-32-68.
6.
Lockheed Support C o n t r a c t
An a n a l y t i c a l s t u d y of t h e Cape Kennedy low l e v e l winds
(0-2 km) has begun. The s u r f a c e f r i c t i o n l a y e r and t h e Ekman s p i r a l
t h e o r y a r e now being i n v e s t i g a t e d .
The h o u r l y peak wind speeds and two a d d i t i o n a l y e a r s of
winds a l o f t d a t a a r e being added t o t h e program from which "launch
p r o b a b i l i t i e s ' ' a r e computed.
7.
NWRC C o n t r a c t
-- Government
Order 76789
An i n v e s t i g a t i o n o f t h e s e a b r e e z e a t Cape Kennedy is being
conducted f o r u s e i n t h e near-pad a b o r t problem.
111,
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
As trodynamics Branch
1.
Miss i o n A n a l y s i s Programs (Lockheed)
A u s e r ' s manual f o r s e v e r a l small m i s s i o n a n a l y s i s programs e n t i t l e d "Quick-Look Miss i o n Analys i s Programs ," has been camp l e t e d and d e l i v e r e d t o R-AERO-GA f o r review.
This document d i s c u s s e s
t h e t e c h ~ i q u e sused t o c a l c u l a t e some of t h e more important t r a j e c t o r y
d e s i g n parameters f o r the d e s i g n of a n o r b i t a b o u t a t a r g e t p l a n e t .
It a l s o i n c l u d e s a u s e r ' s manual f o r t h e P l a n e t a r y O r b i t Design and
O c c u l t a t i o n Computer Program.
2.
Broken Plane T r a j e c t o r i e s (Lockheed)
Work w a s continued on t h e a n a l y s i s of b r ~ k e n - p l a n e i n t e r p l a n e t a r y t r a n s f e r s . Broken-plane t r a j e c t o r y d a t a f o r t h e 1973, 1975,
1977 and 1979 Mars m i s s i o n o p p o r t u n i t i e s have been g e n e r a t e d and a
Lockheed t e c h n i c a l n o t e p r e s e n t t n g t h e s e d a t a has been w r i t t e n . The
TN has been reviewed and i s being prepared f o r p u b l i c a t i o n . The o p t i m i z a t i o n scheme used i n t h e broken-plane computer program is being
i n v e s t i g a t e d i n a n e f f o r t t o complete a thorough documentation of t h e
mathematical approach used as w e l l a s a u s e r ' s manual f o r t h e program.
�3.
Miss ion Design Charts (Lockheed)
I n i t i a l work was begun on a n a n a l y s i s t o determine t h e
t r a j e c t o r y design parameters t h a t a r e t h e most meaningful i n d e s c r i b i n g
p l a n e t a r y and i n t e r p l a n e t a r y miss i o n requirements. This analys i s i s
d i r e c t e d toward t h e des ign and c o n s t r u c t i o n of g e n e r a l m i s s i o n des ign
c h a r t s p o r t r a y i n g t h e s e parameters a s f u n c t i o n s of launch and t a r g e t p l a n e t encounter d a t e s f o r a l l types of i n t e r p l a n e t a r y t r a n s i t s ( i . e . ,
s i n g l e plane Type I and Type 11, broken-plane, and p l a n e t a r y swinbys).
These mission design c h a r t s w i l l be designed t o show t h e mission
requirements f o r a l l types of t r a n s i t s during a given mission opport u n i t y , t o enable t h e t r a j e c t o r y a n a l y s t t o r a p i d l y a s s e s s t h e type of
t r a n s i t t h a t y i e l d s t h e most d e s i r a b l e t r a n s f e r c h a r a c t e r i s t i c s . An
e x i s t i n g i n t e r p l a n e t a r y t r a j e c t o r y computer program i s being modified
t o extend i t s c a p a b i l i t y , f o r use i n t h i s a n a l y s i s , through the addit i o n of automatic p l o t r o u t i n e s and a s u b r o u t i n e f o r computing t o t a l
miss i o n A,.
4.
O r b i t s i n Non-Central F i e l d s
There is a l a r g e number of f a i r l y g e n e r a l non-central
p o t e n t i a l f u n c t i o n s which g i v e r i s e t o a s e p a r a b l e Hamil ton-Jacobi
equation, and hence a closed-form s o l u t i o n f o r the corresponding
o r b i t . I n p o l a r c o o r d i n a t e s , f o r example, any p o t e n t i a l of t h e form
V(r,O) = Vl(r)
v 2 ( 8 ) / r 2 l e a d s t o a closed-form s o l u t i o n . A program has been w r i t t e n t o compute and p l o t t h e r e s u l t i n g o r b i t s .
+
Coordinate systems beyond t h e conventional ones can be
developed by noting t h a t con jugate harmonic f u n c t i o n s w i l l y i e l d a
Hamiltonian w i t h no cross-products of momenta, i . e . , one t h a t may be
a ttaclced convenient2y.
Any closed-form s o l u t i o n w i l l be examined f o r a p p l i c a b i l i t y
t o some a c t u a l physical s i t u a t i o n , f o r example, o r b i t s about non-spherical
b o d i e s , o r o r b i t s of s p a c e c r a f t s u b j e c t t o s e v e r a l a t t r a c t i o n s . Applicat i o n s w i l l most l i k e l y c o n s i s t of t h e development of o s c u l a t i n g o r b i t s ,
o r of patching techniques.
5.
I n t e r p l a n e t a r y N-Body Programs
a.
Program Development
A r e p o r t on t h e i n i t i a l phases of a s t u d y of e f f i c i e n t
i n t e r p l a n e t a r y i n t e g r a t i n g computer programs was given a t t h e r e c e n t
Research Achievements Review. An o u t l i n e of t h e s t r u c t u r e of t h e s t u d y
was given, a s w e l l a s a few examples of how t h e p r o j e c t e d s t u d y r e s u l t s
might be used i n t h e c o n s t r u c t i o n of e f f i c i e n t i n t e r p l a n e t a r y programs.
The paper w i l l be published i n t h e MSFC Research Achievements Review a2
(Third S e r i e s ) .
�b.
T a r g e t i n g Research
Work i n t h i s a r e a has proceeded w e l l . S e v e r a l of t h e
o r i g i n a l approaches have been e l i m i n a t e d a s good c a n d i d a t e s f o r use i n
advanced programs.
I n p a r t i c u l a r , t h e two-body approximations i n
g e n e r a l have been found l a c k i n g and w i l l no l o n g e r b e considered. A
r e p o r t on t h e s t u d i e s of two-body approaches s u p p o r t i n g t h i s conclusion
w i l l be prepared. A method c a l l e d t h e " A n a l y t i c Conglomerate Mass
~ e c h n i q u e "which i s based on a paper by W. Bollennan of t h e German
Aeronautics and Space Experimental S t a t i o n , e n t i t l e d , " R e p r e s e n t a t i o n
of T r a j e c t o r y and V e l o c i t y Coordinates f o r Space F l i g h t by a Generalized
Icepler Approximation and C o r r e c t i o n s i n t h e I t e r a t i o n Procedure , I '
March 1966, a v a i l a b l e a s NASA TT F-11, 387, i s being g i v e n f u r t h e r
cons i d e r a t i o n . Also a n approach u s i n g l a r g e time s t e p i n t e g r a t i o n
( c o n s t a n t o r v a r i a b l e s t e p s i z e ) and a s i m p l i f i e d s o l a r system model
i s s t i l l being i n v e s t i g a t e d
.
c
.
I s o l a t i o n Routine Research
Some c a n d i d a t e r o u t i n e s a r e now being programmed f o r
comparison on t h e computer t o a s s i s t i n t h e s e l e c t o r y r o u t i n e s f o r
use i n d i f f e r e n t a p p l i c a t i o n s
.
6.
Conic Program f o r Small Computers
The programs b e i n g combined t o form t h i s c o n i c program
have a l l been transformed i n t o s u b r o u t i n e form. The remaining work
w i l l be c o n c e n t r a t e d on t h e d r i v e r program and a few s m a l l a d d i t i o n s
which a r e n e c e s s a r y f o r t h e needed accuracy. One of t h e s e a d d i t i o n s
i s t h e computation of t h e n e c e s s a r y burn a r c s a s a f u n c t i o n of launch
The computation of t h e i n j e c t i o n
azimuth and i n j e c t i o n energy (C3).
p o s i t i o n and v e l o c i t y w i l l b e checked a g a i n s t i n t e g r a t e d b o o s t t r a j e c t o r i e s f o r a c c u r a c y , and a comparison w i l l be made of t h e e f f i c i e n c y
and a c c u r a c y of t h i s method a s opposed t o i n t e r p o l a t i o n f o r t h e
i n j e c t i o n s t a t e v e c t o r from a precomputed volume of i n t e g r a t e d b o o s t
trajectories.
7.
O r b i t T r a n s f e r S t u d i e s (United A i r c r a f t NAS8-21091)
The rough d r a f t of t h e f i n a l r e p o r t has been reviewed,
and r e s u l t s of our review have been d i s c u s s e d w i t h t h e c o n t r a c t o r .
A l l c o r r e c t i o n s and r e v i s i o n s have been agreed upon, and t h e f i n a l
copies w i l l be a v a i l a b l e f o r d i s t r i b u t i o n soon.
�8.
Odyssey (Lockheed)
Worlc was continued on t h e i n v e s t i g a t i o n of t h e v a r i a t i o n
i n pclrigcc a l t i t u d e of h i g h l y e c c e n t r i c e a r t h o r b i t s a s a r e s u l t of
l u n a r and s o l a r p e r t u r b a t i o n s . A closed-form a n a l y t i c a l e q u a t i o n ,
g i v i n g t h e v a r i a t i o n i n p e r i g e e a l t i t u d e p e r r e v o l u t i o n , due t o s o l a r
p e r t u r b a t i o n s , i s being used i n a n e f f o r t t o choose t h e i n i t i a l launch
c o n d i t i o n s t h a t r e s u l t i n t h e d e s i r e d o r b i t l i f e t i m e and p e r i g e e a l t i tude v a r i a t i o n .
A r e p o r t on t h e s e e q u a t i o n s and t h e i r a p p l i c a t i o n t o t h i s
problem i s being prepared and should be a v a i l a b l e by t h e time of t h e
next progress r e p o r t .
B.
Guidance Theory Branch
1.
Support C o n t r a c t S t u d i e s
a.
General I n t e r p l a n e t a r y S t u d i e s
The FPR s t u d y u s i n g load r e l i e f c o n t r o l has been
delayed due t o slow turn-around on t h e 1108 computer. Also, e r r o r s i n
t o r q u e computations have been found i n t h e computer program. Correct i o n s a r e b e i n g made.
b.
Quas i-Optimal Guidance Study
The AS-502 m i s s i o n (S-IVB s t a g e o n l y ) has been s u c c e s s f u l l y s i m u l a t e d u s i n g QUOTA as t h e guidance scheme. Nominal S-IVB performance and i d e a l n a v i g a t i o n v a l u e s f o r t h e s t a t e v a r i a b l e s were
assumed. An a t t e m p t i s being made t o i n c o r p o r a t e t h e c o n s t r a i n t on t h e
c o n t r o l v a r i a b l e (2 r a t e l i m i t ) i n t o t h e QUOTA l o g i c . I f s u c c e s s f u l ,
t h i s w i l l a l l o w QUOTA t o o p t i m a l l y f l y m i s s i o n s where c o n s t r a i n t s on
the control variable a r e c r i t i c a l .
c.
Optimum O r b i t Trim Analyses
The r e s u l t s of t h e s t u d y u s i n g QUOTA f o r a n o r b i t
t r i m a n a l y s i s a r e b e i n g documented.
d.
Optimal Guidance Study
Because of a n a l y t i c a l and programming d i f f i c u l t i e s
encountered d u r i n g t h i s r e p o r t i n g p e r i o d , much e f f o r t was expended on
c o r r e c t i n g e r r o r s and o r g a n i z i n g r e s u l t s . Some a d d i t i o n a l p r o g r e s s was
made i n f o r m u l a t i n g and programming t h e e q u a t i o n s f o r t h e d e t e r m i n a t i o n
of t h e m a t r i x of p a r t i a l s of t h e i n i t i a l unknowns w i t h r e s p e c t t o t h e
initial state.
�2.
Contracts
a.
Lockheed
-
Voyager Terminal Guidance A n a l y s i s
A closed-loop guidance model f o r t e r m i n a l guidance has
been i n v e s t i g a t e d . The closed-loop s y s tem shows a s i g n i f i c a n t improvement over t h e p r e v i o u s l y p o s t u l a t e d open-loop model. With a closed-loop
s y s tem, t h e d i s p e r s i o n of t h e o r b i t a l elements a b o u t t h e i r nominals , i s
almost e n t i r e l y a f u n c t i o n of t h e n a v i g a t i o n accuracy assumed. Highly
a c c u r a t e i n s e r t i o n s can be accomplished, i f t r a c k i n g d a t a can b e taken
and processed v e r y c l o s e (4 t o 6 h o u r s ) t o t h e i g n i t i o n p o i n t .
b.
-
IBM
A p p l i c a t i o n o f Numerical Methods t o
Extend C a p a b i l i t i e s f o r Optimal ~ o c k e tGuidance
The o b j e c t i v e of t h i s new c o n t r a c t i s t o provide a
r e l i a b l e , f l e x i b l e , and e f f i c i e n t method f o r computing f u e l - o p t i m a l
r o c k e t t r a j e c t o r i e s ( w i t h b o t h burn and c o a s t a r c s ) . A t a meeting h e l d
w i t h t h e c o n t r a c t o r t o d i s c u s s t h e d e t a i l s of t h e t e c h n i c a l approach
t o t h e problem, i t was decided t h a t c a n d i d a t e s f o r t h e main a l g o r i t h m
which computes optimal f i n i t e - t h r u s t o r b i t t r a n s f e r s w i l l i n c l u d e a
mu1 ti-dimens i o n a l s e c a n t method, quas i - l i n e a r i z a t i o n , and a modified
~ e w t o n ' smethod.
c.
Lockheed
-
Rendezvous Guidance
The IBM 7094 computer programs developed under t h i s
c o n t r a c t have been converted t o r u n on t h e CDC-3200 and t h e SDS-930.
The r e s u l t i n g i n c r e a s e i n computer a c c e s s i b i l i t y i s a l l o w i n g a l a r g e r
amount of s i m u l a t i o n t o be done u s i n g t y p i c a l AAP g u i d e l i n e s . These
r e s u l t s w i l l be p r e s e n t e d soon.
3.
In-House S t u d i e s
a . Work i s c o n t i n u i n g on t h e computer program based on
the techniques developed i n t h e f i n a l r e p o r t f o r c o n t r a c t NAS8-20269
(Optimal C o n t r o l Theory w i t h A p p l i c a t i o n s t o Optimal T r a j e c t o r y and
Guidance Problems by Charles M. Chambers).
Another method, ~ e w t o n ' smethod f o r t h e s o l u t i o n of
boundary v a l u e problems by u s e of p a r t i a l d e r i v a t i v e s , i s b e i n g
developed a s a computer program which i s t o be compared t o chambers'
method ,
�b. A guidance s i m u l a t i o n deck i s being developed by
mott i f y ing a n c x i s t ing computer program. Various guidance schemes w i l l
hc progri~mccl a s s u b r o u t i n e s .
Guidance schemes can be compared by
s i~nula t i n g a miss i o n using t h e v a r i o u s guidance s u b r o u t i n e s .
c . Closed-form s o l u t i o n s f o r powered f l i g h t i n a c o n s t a n t
g r a v i t y f i e l d have been developed w i t h mass a s t h e independent v a r i a b l e .
This a l l o w s a l l of t h e p a r t i a l d e r i v a t i v e t r a n s i t i o n m a t r i c e s t o be
o b t a i n e d i n c l o s e d form. These r e s u l t s have been used t o c o n s t r u c t a
computer program t o s o l v e t h e COV boundary v a l u e problem.
d. The three-dimensional COV deck f o r t h e CDC-3200 comp u t e r i s now capable of f l y i n g t o s i x d i f f e r e n t c u t - o f f s u r f a c e s . A
t r a j e c t o r y w i t h a n optimal c o a s t p e r i o d was r e c e n t l y obtained using a
v e h i c l e and geometry a p p r o p r i a t e t o a n U P m i s s i o n . A c a p a b i l i t y t o
handle i n e q u a l i t y c o n s t r a i n t s and a rendezvous c a p a b i l i t y i s planned
f o r the future.
e . A computer program which w i l l perform a p r e f l i g h t
e r r o r a n a l y s i s on i n t e r p l a n e t a r y t r a j e c t o r i e s i s b e i n g developed. This
program a s s e s s e s t h e probable midcourse AV requirements and p r o v i d e s ,
a f t e r each midcourse c o r r e c t i o n , t h e c o v a r i a n c e m a t r i x of t h e e r r o r s i n
time of f l i g h t , and i n t h e miss parameters a t t h e t a r g e t p l a n e t .
C.
O p t i m i z a t i o n Theory Branch
1.
Review of S t a b i l i t y Requirements
Some r e c e n t d i s c u s s i o n s have been h e l d concerning t h e necess i t y of imposing s t a b i l i t y margin requirements on a launch v e h i c l e f l i g h t
c o n t r o l system. No c o n c l u s i o n s have y e t been reached. NASA TM X-53735,
"A D i s c u s s i o n of t h e S t a b i l i t y Requirements f o r a Launch Vehicle F l i g h t
Control Sys tern," has been published t o document t h e d i s c u s s i o n t o d a t e
and t o s o l i c i t p a r t i c i p a t i o n i n t h e d i s c u s s i o n by o t h e r s . Some responses
t o t h e r e p o r t have a l r e a d y been r e c e i v e d .
2.
S t a t i s t i c a l Wind Model
A c o n t r a c t i s being n e g o t i a t e d w i t h Hayes I n t e r n a t i o n a l t o
use t h e c u r r e n t l y a v a i l a b l e Jimsphere d a t a t o c o n s t r u c t a new wind model
f o r use i n s t a t i s t i c a l a n a l y s e s of launch v e h i c l e performance.
The model
w i l l assume t h e wind ( n o n - s t a t i o n a r y ) t o be Gaussian t o p e r m i t l i n e a r
a n a l y s i s of t h e v e h i c l e ' s performance, b u t i t w i l l be of h i g h e r o r d e r
and more a c c u r a t e t h a n c u r r e n t l y a v a i l a b l e models of t h i s t y p e . M r .
George F i c h t l of R-AERO-Y i s p a r t i c i p a t i n g i n t h e s t u d y .
�3.
A n a l y t i c a l Study of S p a c e c r a f t P o i n t i n g E r r o r
Research i s being done on a n a n a l y t i c approach t o t h e
problem of minimizing s p a c e c r a f t p o i n t i n g e r r o r d u r i n g midcourse, o r b i t
i n s e r t i o n , and o r b i t t r i m maneuvers d u r i n g i n t e r p l a n e t a r y f l i g h t .
Various c o n t r o l laws a r e being used and s e n s i t i v i t y f u n c t i o n s a r e
employed t o determine s u i t a b l e g a i n s f o r minimizing t h e t e r m i n a l p o i n t ing e r r o r . A Voyager c l a s s s p a c e c r a f t is being used i n t h e s t u d y ; howe v e r , t h e r e s u l t s may b e extended t o t h e g e n e r a l c l a s s of i n t e r p l a n e t a r y
vehicles.
4.
Minimax Control
A s t u d y of a minimax c o n t r o l computational a l g o r i t h i s
being performed by Lockheed s u p p o r t c o n t r a c t o r s i n c o n j u n c t i o n w i t h
D r . C. D. Johnson of t h e U n i v e r s i t y of Alabama and in-house personnel.
The s t u d y has been p r o d u c t i v e from a p r a c t i c a l v i e w p a i n t i n b r i n g i n g
t o l i g h t some problems i n t h e s y n t h e s i s of minimax c o n t r o l l e r s . F i r s t ,
s i n c e t h e a l g o r i t h m u s e s backward-time i n t e g r a t i o n , f a s t time-constant
elements s u c h a s a c t u a t o r s can g i v e problems u n l e s s t h e i r n o n l i n e a r
c h a r a c t e r i s t i c s a r e modeled i n s u c h a way a s t o p r e v e n t divergence.
Second, t h e d i m e n s i o n a l i t y of high-order systems can q u i c k l y l e a d t o
unwieldy v i s u a l i z a t i o n and long computer times. The r e s u l t s of t h e
s t u d y a r e expected t o be p r e s e n t e d a t t h e A N Guidance, C o n t r o l , and
F l i g h t Dynamics Conference i n August
.
5.
Parameter Optimization Study f o r ATM
Support C o n t r a c t o r
-
Lockheed
The a n a l o g phase of t h e hybrid s i m u l a t i o n i s undergoing
check-out, and t h e o p t i m i z a t i o n package i s b e i n g p r o g r a m e d on t h e
d i g i t a l computer as t h e n e x t p o r t i o n of t h e program sequence. The
t o t a l program should be i n t h e check-out phase by mid-July.
It is
hoped t h e a n a l y s i s w i l l e s t a b l i s h t h e u s e f u l n e s s of t h e c o n j u g a t e
g r a d i e n t technique f o r parameter o p t i m i z a t i o n problems by developing
c o n t r o l l e r f o r a complex s y s tern such a s t h e ATM.
an "~ptimum'~
6.
Nor t h r o p Support C o n t r a c t o r
a.
S a t u r n po pol lo Load R e l i e f S t u d i e s
I n i t i a l r i g i d body s t u d i e s (time v a r y i n g c o e f f i c i e n t s )
d r e under way f o r a t y p i c a l S a t u r n VIApollo c o n f i g u r a t i o n (SA-504)Candidate c o n t r o l l e r s must provide a s i g n i f i c a n t r e d u c t i o n i n t h e
v e h i c l e bending moment t o be considered f o r t h e more complete a n a l y s i s
which w i l l i n c l u d e t h e v e h i c l e bending dynamics. These s t u d i e s , which
a r e supplemental t o e a r l i e r ones made by Boeing, s e e k t o answer
ques t i o n s r a i s e d by t h e e a r l i e r work.
�b.
Numerical Methods i n T r a j e c t o r y Optimization
A new r e p o r t being prepared on t h e e q u a t i o n s of v a r i a t i o n w i l l examine t h e e f f e c t of d i s c o n t i n u i t i e s on t h e e q u a t i o n s of
v a r i a t i o n i n more d e t a i l than has been done p r e v i o u s l y .
c.
Analytical F i l t e r Synthesis
A r e p o r t on a n a p p l i c a b i l i t y s t u d y of a r e c e n t (1967)
f i l t e r s y n t h e s i s technique proposed by R. W. Bass has been d r a f t e d .
In
g e n e r a l , t h e c o n c l u s i o n s were n e g a t i v e . I n i t s p r e s e n t s t a t e , t h e
technique does n o t appear t o be a s u s e f u l a s was o r i g i n a l l y expected.
7.
North American (NAS8-21077)
O b j e c t i v e : Development of means of computing optimal
orbital transf ers for f i n i t e thrust.
The c o n t r a c t was completed d u r i n g t h i s r e p o r t i n g p e r i o d .
Because t h e r e s u l t s were incomplete, a g e n e r a l d i s t r i b u t i o n of t h e
r e p o r t s was n o t made. An e x t e n s i o n of t h i s c o n t r a c t t o complete t h e
d e t a i l s of t h e three-dimensional, s i n g l e - c e n t e r case and t o extend
t h e e x i s t i n g work t o t h e r e s t r i c t e d three-body problem, i s expected.
8.
Honeywell (NAS8-21063)
O b j e c t i v e : To i n v e s t i g a t e f u r t h e r t h e a p p l i c a t i o n of
t h e s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206.
The o p t i m i z a t i o n program has been s u c c e s s f u l l y extended
t o use a h i g h - o r d e r model of t h e launch v e h i c l e , and t h e optimum
g a i n s have been c a l c u l a t e d assuming t h a t a l l s t a t e s a r e measurable.
A d i s c r e p a n c y i n t h e q u a l i t a t i v e r e s u l t s o b t a i n e d under
t h i s c o n t r a c t and t h e p r o j e c t - o r i e n t e d r e s u l t s o b t a i n e d on t h e same
v e h i c l e under c o n t r a c t NAS8-21171 l e d t o t h e d i s c o v e r y of a d a t a e r r o r
i n t h e i n p u t d a t a f o r t h e o p t i m i z a t i o n program. This e r r o r has been
c o r r e c t e d i n s o f a r a s p o s s i b l e w i t h i n t h e a v a i l a b l e funds. However,
some of t h e q u a l i t a t i v e r e s u l t s on t h e s e n s o r c h o i c e problem appearing i n t h e f i n a l r e p o r t w i l l have t o be based on t h e i n c o r r e c t d a t a .
�There s t i l l e x i s t some convergence problems i n t h e i t e r a schcmc used t o o b t a i n t h e q u a d r a t i c o p t i m i z a t i o n problem equival c n t t o t h c o r i g i n a l o p t i m i z a t i o n problem, which i s minimizing t h e
1 i k c L illood of f a i l u r e . However, a g r a d u a t e s t u d e n t a t Purdue, motiv a t c d by t h e g e n e r a l a p p l i c a b i l i t y of t h e o p t i m i z a t i o n technique used
i n t h e s t u d y , has provided a n improved convergence technique. I f t h i s
technique checks o u t , i t w i l l be documented i n t h e f i n a l r e p o r t .
lr i v c
A s m a l l c o n t r a c t e x t e n s i o n has been l e t t o permit t h e
documentation o f t h e o p t i m i z a t i o n program used i n t h i s s t u d y , s o t h a t
the program can b e used i n f u t u r e in-house r e s e a r c h w i t h o u t d u p l i c a t i n g
t h e expense involved i n developing t h e program. It i s planned t h a t
MSFC personnel w i l l go t o ~ o n e y w e l l ' s f a c i l i t y t o become f a m i l i a r w i t h
the o p e r a t i o n of t h e program b e f o r e i t s t r a n s f e r r a l t o MSFC. F i n a l
w r i t t e n and o r a l r e p o r t s on t h e r e s u l t s of t h i s s t u d y a r e expected
w i t h i n the next reporting period.
�IV.
PROJECTS OFFICE
1.
AAP Experiments C a p a b i l i t y
This Laboratory has been p a r t i c i p a t i n g i n AAP Experiments Comp a t i b i l i t y s t u d i e s d u r i n g A p r i l and May t o determine t h e f e a s i b i l i t y of
i n c l u d i n g experiments which w i l l r e t u r n d a t a p e r t a i n i n g t o the n a t u r a l
r e s o u r c e s on e a r t h . These e a r t h r e s o u r c e s experiments a r e p r i m a r i l y
photographic experiments i n b o t h t h e v i s u a l and i n f r a - r e d spectrum. A
r e p o r t was made t o M r . Luskin on May 15 on t h e e a r t h r e s o u r c e s e x p e r i ments i n which t h i s Laboratory p r e s e n t e d t h e o r b i t a l a l t i t u d e l i n c l i n a t i o n c o n s i d e r a t i o n s , t h e miss i o n sequence, and some of t h e p o i n t i n g and
c o n t r o l problems. This s t a t u s r e p o r t showed t h a t t h e r e has been major
i n c o m p a t i b i l i t y recognized which would n o t a l l o w any proposed e a r t h
r e s o u r c e s t o f l y ; however, f u r t h e r s t u d i e s were r e q u i r e d . F u r t h e r
e f f o r t i s proceeding under a group formed by t h e Mission Requirements
A r e p o r t w i t h recommendations
Panel and headed by M r . Sims (R-AERO-P).
concerning t h e f e a s i b i l i t y of f l y i n g e a r t h r e s o u r c e s experiments i s t o
be made t o D r . Mueller i n t h e l a t t e r p a r t of June.
2.
S a t u r n V SE&IS C o n t r a c t
The Boeing Company submitted a proposal on MSFC Supplemental
Agreement 262, implementation of launch schedule APD-4H. This proposal
i s being reviewed w i t h i n t h e l a b o r a t o r y t o i n s u r e t h a t t h e S a t u r n V
program o b j e c t i v e s w i l l be accomplished. N e g o t i a t i o n s on t h i s c o n t r a c t
change a r e expected t o b e g i n i n mid-June.
V.
AEROPHYSICS DIVISION
A.
Mechanical Design O f f i c e
1. A new d e s i g n of a f u l l s c a l e High Reynolds Number Equipment
Diaphragm C u t t e r using a four-arm g r i d s u p p o r t has been completed. T e s t s
i n d i c a t e d t h a t a four-arm g r i d g i v e s b e t t e r diaphragm p e t a l ing than t h e
8-arm g r i d p r e v i o u s l y used.
2. A r e q u e s t has been made by R-AERO-AD f o r s i x S a t u r n V f o r c e
models f o r t e s t i n g i n MSFC 14" wind t u n n e l . Four of t h e models w i l l have
"bent" c e n t e r l i n e s i n o r d e r t o determine t h e e f f e c t of v e h i c l e bending on
s t a t i c aerodynamics of t h e S a t u r n V. ME Laboratory has been r e q u e s t e d t o
make s t u d i e s t o determine t h e most economical method of f a b r i c a t i n g t h e
"bent" models. Design w i l l begin when t h e s e s t u d i e s a r e completed.
�3 . The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and
t l ~ c i rc u r r e n t s t a t u s
.
Redesign of F l a t P l a t e Protuberance Heat T r a n s f e r
Model, L. R . C . , 4' WT (AT)
Design
Heated Plenum Chamber, L. D. WT (AE)
Design
C a l i b r a t i o n Equipment f o r High Reynolds
Number T e s t Equipment (AE)
Design
Sapphire Windows, S. T. S . , 14" WT, X-Beam (AE)
Design
5 Component Micro Force Balance, L. D. C.
Drafting
4" O.D.
P r e s s u r e Model, L. T. V . ,
(AE)
WT (AD)
Drafting
Pneumatic Work Bench (NSC) (A)
Drafting
Nozzle and Plenum, Laser Beam (A)
Drafting
Redesigned Survey Probe, 14" WT (AE)
Fabrication
Low Volume Diaphragm C u t t e r , IBFF (AE)
Fabrication
V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n
Fabrication
18.75% P i l o t Model, High Reynolds T e s t Equipment (AE)
V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n High
Reynolds T e s t Equipment (AE)
Fabrication
Strap-On Force Model, 14" WT (AD)
Fabrication
T r a c e r M a t e r i a l I n j e c t o r , X-Beam,
S.T.S., 14" WT (A)
Fabrication
Major Components, High Reynolds Number T e s t
Equipment
Fabrication
( P a r t i a l Delivery)
P r e s s u r e Models, X-Beam, SST, 14" WT (AF)
Delivered
S l o s h Force Measuring System (DD)
n e l ivered
5" O . D . ,
S a t . V. Base Flow Model, X-Beam 14" WT (A)
Force Models, Experimental, L. D. C .
(AE)
Delivered
Delivered
�B.
Design Branch
1.
O r b i t a l Workshop Aerodynamics
The S a t u r n I B o r b i t a l workshop v e h i c l e e x t e r n a l c o n f i g u r a t i o n has been changed s e v e r a l times a n d , a t p r e s e n t , a frustum a n g l e
i n c r e a s e from B058' i s being c o n s i d e r e d . S i n c e aerodynamic d a t a a r e
r e q u i r e d f o r s t r u c t u r a l t r a j e c t o r y and c o n t r o l a n a l y s i s , t h e aerodynamic
c h a r a c t e r i s t i c s were d e f i n e d f o r the c u r r e n t c o n f i g u r a t i o n . S t a b i l i t y
d a t a were based on small model wind t u n n e l t e s t conducted i n t h e MSFC
14" t r i s o n i c wind t u n n e l . Local normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s
were defined based on e x p e r i m e n t a 1 , a n a l y t i c a l and e m p i r i c a l d a t a . Data
a r e p r e s e n t e d f o r a n g l e s of a t t a c k of 0 t o 10 degrees f o r Mach numbers
01 0.8 t o 2.0.
These d a t a a r e published i n o f f i c e memorandum R-AEROAD-68-24.
2.
S o l a r Panel Shroud and APS F a i r i n g s f o r S-IB/AAP-11
By t h e end of February 1968, i t became e v i d e n t t h a t R-P&VE
was n e a r i n g completion of t h e s t r u c t u r a l d e s i g n of t h e s o l a r panel
U n t i l t h i s time, no
shroud and APS f a i r i n g s f o r t h e S a t u r n IB/AAP-11.
experimental d a t a had been obtained t o v e r i f y e s t i m a t e d load d i s t r i b u t i o n s .
To i n c o r p o r a t e a p o s s i b l e weight s a v i n g s i n t h e d e s i g n of t h e s e u n i t s ,
R-P&VE needed t h e s e d a t a by a b o u t t h e second week of A p r i l 1968.
T e s t s were conducted i n t h e MSFC t r i s o n i c wind t u n n e l d u r ing t h e second week of A p r i l 1968. P r e s s u r e d i s t r i b u t i o n s were obtained
a t Mach numbers from 0.8 t o 1.96 f o r a n g l e s of a t t a c k up t o 8 d e g r e e s .
These d a t a were f u r n i s h e d t o R-P&VE approximately one week l a t e r than
promised because of l a c k of t i m e l y s u p p o r t i n model d e s i g n and f a b r i c a t i o n .
3
S a t u r n S-IVB APS R1E Engine Plume D e f i n i t i o n f o r Plume
Impingement Analyses
Plume c h a r a c t e r i s t i c s (Mach number, p r e s s u r e , t e m p e r a t u r e ,
d e n s i t y , and chemistry p r o f i l e s ) f o r t h e R1E engine of t h e S-IVB APS
u n i t s have been developed. These d a t a , which a r e a p p l i c a b l e f o r p e r f orrning plume impingement and contamination a n a l y s e s over a f f e c t e d
a r e a s of t h e S-IVB workshop v e h i c l e , a r e p r e s e n t e d i n o f f i c e memorandum
R-AERO-AD-68-34, May 1 7 , 1968.
4.
S a t u r n V High A l t i t u d e Flow S e p a r a t i o n E f f e c t s on Vehicle
Stability
An a n a l y s i s i s being made t o determine t h e e f f e c t s of flow
The flow s e p a r a s e p a r a t i o n on S a t u r n V s t a t i c s t a b i l i t y aerodynamics.
t i o n , caused by t h e expanding exhaust plume, has been observed b o t h on
t h e ground and from a i r c r a f t . From t h e s e o b s e r v a t i o n s , t h e p o i n t of
flow s e p a r a t i o n has been d e f i n e d a s a f u n c t i o n of a l t i t u d e .
�A l l changes i n t h e aerodynamics due t o flow s e p a r a t i o n
w i l l occur a f t e r Mach 3.0.
Vellicle c o n t r o l w i l l n o t be g r e a t l y a f f e c t e d
hccilr~sc of the low dynamic p r e s s u r e .
R e s u l t s of t h i s a n a l y s i s w i l l be
pub1 ished i n t h e near f u t u r e .
5.
AS-205/CSM Axial Force C h a r a c t e r i s t i c s
Power-on a x i a l f o r c e c o e f f i c i e n t s were r e v i s e d f o r the
AS-ZO~/CSMv e h i c l e based on t h e AS-203 and AS-204 f l i g h t d a t a . These
v e h i c l e s had t h e c o r r e c t base c o n f i g u r a t i o n w i t h t h e engine shrouds
removed and t u r b i n e exhaust d u c t s r e r o u t e d . F l i g h t d a t a r e f l e c t a
d e c r e a s e i n t o t a l a x i a l f o r c e c o e f f i c i e n t . The l i f t - o f f term which
has been included i n t h e a x i a l f o r c e c o e f f i c i e n t i s now d e l e t e d based
on f l i g h t r e s u l t s . These d a t a a r e published i n o f f i c e memorandum
K-AERO-AD-68-25.
6.
S a t u r n V Power-On Aerodynamic Drag
An improved method of p r e s e n t i n g v e h i c l e a x i a l f o r c e has
been developed t o more a c c u r a t e l y d e f i n e b a s e d r a g e f f e c t s d u r i n g f i r s t
stage flight.
The new approach d e f i n e s a forebody a x i a l f o r c e coeff i c i e n t a s a f u n c t i o n of Mach number and a curve o f ' a v e r a g e b a s e p r e s s u r e (Pb - P,) v e r s u s a l t i t u d e .
T o t a l v e h i c l e d r a g i s computed by
summing t h e above curves f o r a g i v e n Mach number, a l t i t u d e , and dynamic
p r e s s u r e . P r e l i m i n a r y a n a l y s i s of AS-502 f l i g h t d a t a i n d i c a t e s a 25 p e r c e n t d e c r e a s e i n a x i a l f o r c e from t h e d e s i g n d a t a i n NASA TM X-53517.
About 15 p e r c e n t of t h i s d e c r e a s e i s due t o scoop removal. The remainder
of t h e d i f f e r e n c e i s caused by t h e d i f f e r e n c e between f l i g h t d a t a and
wind t u n n e l t e s t s . F i n a l d a t a w i l l be published t o update d e s i g n a x i a l
force
.
7.
Q-Ball Angle of A t t a c k Sensor
S i n c e MSC i s c o n s i d e r i n g removing t h e q - b a l l cover p o s s i b l y
t h i r t y minutes b e f o r e v e h i c l e launch, A s t r i o n i c s Laboratory i s concerned
a b o u t t h e e f f e c t s of r a i n on t h e q - b a l l d u r i n g t h i s time p e r i o d .
A s t r i o n i c s has a l s o reopened t h e q u e s t i o n of f l y i n g through r a i n and
c l o u d s . No complete environmental t e s t i n g has e v e r been accomplished on
t h e q - b a l l because, i n t h e p a s t , R&D v e h i c l e s were n o t flown i n r a i n .
But, w i t h t h e moon s h o t launch windows being l i m i t e d , S a t u r n V v e h i c l e s
may b e f i r e d r e g a r d l e s s of t h e weather. A s t r i o n i c s has asked R-AERO-AD
t o h e l p i n planning and running n e c e s s a r y t e s t s t o determine t h e e f f e c t s
of r a i n on t h e q - b a l l .
�8.
Orif i c e Flow C o e f f i c i e n t I n v e s t i g a t i o n
The t e s t d a t a from Ames, which i s being p l o t t e d on t h e
7090 Computer a t t h e Computation Laboratory, a r e almost complete; NSL
w i l l publish a f i s a l data report.
Because of t h e unavoidable d e l a y s encountered d u r i n g t h i s
program which d e p l e t e d t h e c o n t r a c t f u n d s , t h e a d d i t i o n a l t e s t s scheduled
f o r t h e MSFC 14-inch TWT and t h e IBFF have been postponed i n d e f i n i t e l y .
NSL has r e c e i v e d a four-month no-cost c o n t r a c t e x t e n s i o n t o a l l o w them
t o f i n i s h t h e r e p o r t work.
The major d e l a y s which occurred a t Ames were due t o (1)
l a s t-minute s c h e d u l e changes and instrument m a l f u n c t i o n s , (2) t h e i r
d e l a y i n sending MSFC f i n a l d a t a , and ( 3 ) Computation L a b o r a t o r y ' s
d e l a y i n m a n i p u l a t i n g and p l o t t i n g t h e d a t a .
9.
Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n
P r e s s u r e t e s t s of t h e v i s c o u s c r o s s - f l o w models a r e underway i n t h e MSFC 14-inch TWT. The f o u r models c o n s i s t of two c o n f i g u r a Each
t i o n s : a n o g i v e - c y l i n d e r and a n o g i v e - c y l i n d e r - f r u s t u m - c y l i n d e r .
c o n f i g u r a t i o n has two model s i z e s : a 1 . 0 - i n c h diameter and a n 0.5-inch
d i a m e t e r . The Mach number range i s 0.40 through 1.96, and t h e a n g l e of
a t t a c k range i s 0, 5 , 10, 15, 20 and 25 d e g r e e s . Model i n s t a l l a t i o n
and d a t a a c c u r a c y problems may cause a two- t o three-week d e l a y i n comp l e t i n g t h e program.
C.
Experimental Aerophysics Branch
1.
Low
ens i t y
Chamber
The i n v e s t i g a t i o n of t h e use of t h e Low Density Chamber
a s t h e a l t i t u d e s i m u l a t o r f o r performing t h e j e t plume impingement t e s t
a n d l o r determining t h e a p p r o p r i a t e n e s s of C02 gas a s t h e t e s t medium
h a s continued. To determine i f C02 i s s a t i s f a c t o r y a s a t e s t medium,
t h e following experiments were designed and a r e being prepared:
(a)
Determination of t h e o n s e t a n d / o r presence of condens a t i o n i n t h e C02 plume by impact p r e s s u r e measurement
techniques and l i g h t s c a t t e r i n g t e c h n i q u e s .
(b)
Impact p r e s s u r e survey of C02 plume'for comparison t o
a t h e o r e t i c a l plume.
(c)
Measurement of f o r c e s and moments produced by a C02
j e t exhausting p a r a l l e l t o a f l a t p l a t e i n a vacuum
( f o r comparison t o pub1 ished d a t a ) .
�A l l ol: tllc. cxpcrimcntal hardware has been ordered and i s on hand ( i n c l u d ing a 2-component b a l a n c e f o r experiment c ) w i t h t h e e x c e p t i o n of model
n o z z l c s . Altllough t h e c l o s e t o l e r a n c e s on t h e s e n o z z l e s p r e s e n t a
problem i n manufacturing, a t t e m p t s a r e s t i l l being made t o f a b r i c a t e
them.
Some t e s t s have a l r e a d y been r u n t o observe t h e presence
of C 0 2 condensation i n t h e plume, u s i n g t h e l i g h t - s c a t t e r i n g technique.
A 1 though no q u a n t i t a t i v e r e s u l t s were o b t a i n e d , flow v i s u a l i z a t i o n of
t h e condensation i n t h e plume was f u r n i s h e d . F u r t h e r t r i a l s a r e being
made t o r e f i n e t h e photographs f o r documentation.
2.
IBFF
The Impulse Base Flow F a c i l i t y has completed t h e Mach 2
s t a r t i n g load phase of the p i l o t model High Reynolds Number program.
The d a t a , which i n c l u d e a n a n g l e of a t t a c k range from 0 t o 18 degrees
w i t h charge p r e s s u r e s from 65 t o 715 p s i a , a r e being a n a l y z e d . Subs o n i c and t r a n s o n i c f o r c e d a t a phases a r e scheduled t o b e g i n t h e week
01 May 27. Following t h e f o r c e t e s t s , blockage t e s t s a r e scheduled.
Some problems have been encountered w i t h t h e s t r a i n gauge
b a l a n c e system used t o measure model s t a r t i n g load. High p r e s s u r e
(715 p s i a ) environments w i t h a r a p i d decompression seem t o a f f e c t t h e
s t r a i n gauge bond. A f t e r s e v e r a l load a p p l i c a t i o n s , l a r g e z e r o s h i f t s
o c c u r r e d . I n s p e c t i o n r e v e a l e d numerous bubbles under t h e gauges,
n e c e s s i t a t i n g regaging
.
Plans a r e being made f o r the f l a t - p l z t e s i n g l e - n o z z l e phase
of t h e p a r a m e t r i c program t o f o l l o w t h e p i l o t model HRE program. Run
sclledules have been r e c e i v e d , and d e s i g n i s under way f o r p l a t e mounting.
A c o n i c a l n o z z l e and a contoured n o z z l e (5-2), which have been r e c e i v e d ,
a r e ready f o r i n s t a l l a t i o n . This i n v e s t i g a t i o n must be scheduled i n
l i g h t of o t h e r p r o j e c t s and a v a i l a b i l i t y of manpower.
The High Reynolds Number T e s t Equipment program has made
c o n s i d e r a b l e p r o g r e s s d u r i n g t h e p a s t two months. Concrete work f o r t h e
s u p p l y tube s u p p o r t s and 1,000,000 l b s t h r u s t anchor has been completed.
Welding of t h e s u p p l y tube and a i r reducing s t a t i o n i s scheduled t o
b e g i n i n e a r l y June.
The f o l l o w i n g i s a l i s t of hardware items and t h e i r confirmed d e l i v e r y d a t e s :
(a)
(b)
D i f f u s e r and s p o o l s
Tension rods
June 3
J u l y 18
�(c)
(d)
(e)
Bridge f o r crane
Model s u p p o r t
Supersonic t e s t s e c t i o n
June 15
July 8
J u l y 22.
C a l i b r a t i o n model requirements have been forwarded t o t h e
Mechanical Design O f f i c e . Model p r e s s u r e s w i l l be measured w i t h t h e
trapped volume technique. I n s t r u m e n t a t i o n r e q u i r e d f o r t h i s technique
has been o r d e r e d .
A group from AEDC s p e n t a day a t t h e Wind Tunnel looking
a t t e s t d a t a and q u e s t i o n i n g personnel a b o u t our High Reynolds T e s t
Equipment. AEDC t e n t a t i v e l y plans t o b u i l d a tube wind t u n n e l w i t h a
1 2 - f o o t diameter t e s t s e c t i o n , a 1000 long supply t u b e , 500 p s i a s t a g n a t i o n p r e s s u r e , configured much l i k e t h e MSFC equipment. Two groups from
Boeing have a l s o v i s i t e d r e c e n t l y f o r d i s c u s s ions concerning t h e i r pos
s i b l e development of a tube wind t u n n e l .
-
4.
Thermal-Acous t i c J e t F a c i l i t y (TAJF)
Tes t s a r e c o n t i n u i n g by R-AERO-AF personne 1 us ing t h e c r o s s
beam system. T o t a l runs t o d a t e : 269. Power and h i g h p r e s s u r e gas
connections t o t h e helium h e a t e r have s t i l l n o t been made. The c o n t r a c t
l ~ a sn o t y e t been awarded, b u t i s expected any day, Since t h e c o n t r a c t
c a l l s f o r completion w i t h i n 60 d a y s , hookup might be made b e f o r e t h e end
of J u l y .
5.
1.4 x 14-Inch T r i s o n i c Wind Tunnel
The f o l l o w i n g t e s t s were r u n d u r i n g A p r i l and May 1968:
( a ) An i n v e s t i g a t i o n f o r R-AERO-AF i n t o t h e flow and
a c o u s t i c c h a r a c t e r i s t i c s of t h e 14" T r i s o n i c wind t u n n e l s p e c i a l t e s t
s e c t i o n . The work was i n p r e p a r a t i o n f o r f u t u r e t e s t s using t h e c r o s s beam c o r r e l a t i o n equipment. P r e s s u r e and a c o u s t i c surveys were made
a l o n g the high speed S c h l i e r e n movies f o r shock f l u c t u a t i o n . T o t a l
runs: 64.
(b) An i n v e s t i g a t i o n f o r R-AERO-AD t o o b t a i n p r e s s u r e d a t a
t o v e r i f y e s t i m a t e d load d i s t r i b u t i o n s on t h e s o l a r panel shrouds and APS
u n i t s of t h e S a t u r n 113/AAP-I1 v e h i c l e . T o t a l r u n s : 38.
( c ) An i n v e s t i g a t i o n t o determine t h e reduced a x i a l f o r c e
due t o removing t h e base flow d e f l e c t o r s from t h e Apollo-Saturn V launch
v e h i c l e . The i n v e s t i g a t i o n compared d a t a t o t h a t o b t a i n e d from c o r n e l l ' s
8 - f o o t Transonic Tunnel. T o t a l r u n s : 4 4 .
�( d ) A p r e l i m i n a r y e n t r y f o r R-AERO-AD on t h e v i s c o u s
c r o s s - 1 l ow inves t i g a t i o n . P r e s s u r e and f o r c e d a t a were obtained on
[our models. These d a t a w i l l b e compared w i t h f u t u r e t e s t s . T o t a l
r u n s : 55.
( e ) A c o n t i n u a t i o n of t h e i n v e s t i g a t i o n of v i s c o u s c r o s s flow. This p r e s s u r e phase, being conducted by ~ h r y s l e rs' Space D i v i s i o n
f o r R-AERO-AD, i s c u r r e n t l y i n p r o g r e s s . To i n c r e a s e t h e t u n n e l r u n
r a t e , R-TEST aFr and compressed a i r from t h e t u n n e l compressors a r e
being used s imul taneous l y
.
6.
7 x 7-Inch B i s o n i c Tunnel
The BWT was r e c a l i b r a t e d d u r i n g t h e r e p o r t i n g period t o
cover c e n t e r l i n e a s w e l l a s o f f - c e n t e r 1 i n e Mach number d i s t r i b u t i o n s .
The complete s u b s o n i c and s u p e r s o n i c range was covered. T o t a l r u n s :
110.
7.
I n s trumenta t i o n
The protuberance model was r e c e i v e d May 3 --form
--. t h e AEDC
shops f o r t h e i n s t r u m e n t a t i o n of t h e 122 a c o u s t i c channels and 400
s t a t i c p r e s s u r e s . Assembly time f o r t h e i n s t r u m e n t a t i o n was reduced
by t h r e e man months of e f f o r t s i n c e i t was p o s s i b l e t o use t h e w i r i n g
a s s e m b l i e s removed from t h e 4 p e r c e n t S a t u r n V a c o u s t i c s model which
was t e s t e d a t AEDC a b o u t one y e a r ago.
A -
The model was shipped t o AEDC May 14, and t e s t i n g began
May 20. The f i r s t n i g h t of t e s t i n g was i n v a l i d a t e d because of a t u n n e l
water l e a k . Water c o n c e n t r a t i o n s were s o heavy t h a t t h e model had t o
be t a k e n a p a r t t h e n e x t day, each s t a t i c p r e s s u r e l i n e blown d r y , and
t h e S c a n i v a l v e s disassembled, c l e a n e d , and d r i e d . P a r t s of t h e model
r e q u i r e d b a i l i n g o u t of t h e w a t e r . T e s t i n g i s expected t o c o n t i n u e
through June 5 .
8.
Data Reduction
Besides t h e normal t e s t d a t a , approximately 800 d a t a c a s e s
were processed f o r t h e shadow s c a n n e r . Most of t h i s work is done on
t h e CDC 3200 l o c a t e d i n B u i l d i n g 4200.
D.
Thermal Environment Branch
1. The s p e c t r o r a d i o m e t e r i n s t r u m e n t a t i o n system developed by
Rocketdyne under C o n t r a c t NAS8-21144 has been i n s t a l l e d and checked o u t
i n t h e B-3 t e s t c e l l a t t h e Rocketdyne Nevada F i e l d Laboratory (NFL).
T e s t s on FLOX/CH4 p r o p e l l a n t combination, c u r r e n t l y underway, a r e being
�monitored. I n a d d i t i o n t o our use of t h e d a t a from t h e s e t e s t s , t h e
r e s u l t s w i l l b e used by Langley Research Center and Rocketdyne a s a
d e s i g n a i d i n t h e development of a h i g h performance i n j e c t o r .
2. The hardware and t e s t s e t - u p f o r t h e experimental composite
engine s t u d y (NAS7-521) being done by Rocketdyne has been completed.
Because of a n e x p l o s i o n i n t h e a d j a c e n t t e s t c e l l , t h e i n s t r u m e n t a t i o n
system was damaged, b u t t h i s has been r e p a i r e d and f u l l s c a l e t e s t i n g i s
t o begin i n J u l y .
3 . Two c o n t r a c t s w i t h t h e General Applied Science L a b o r a t o r i e s ,
Both of
I n c . have r e c e n t l y been i n i t i a t e d : NAS8-21264 and NAS8-21387.
t h e s e c o n t r a c t s a r e f o r a n a l y t i c a l s t u d i e s of r e a c t i n g gas flows and
t h e i r e f f e c t on p r o p u l s i o n systems. Progress on t h e s e e f f o r t s w i l l be
r e p o r t e d i n more d e t a i l l a t e r .
4 . High a n g l e of a t t a c k h e a t i n g t e s t s : A t r i p was made t o
Langley Research Center d u r i n g t h e week of May 12 t o d i s c u s s h i g h a n g l e o f - a t t a c k h e a t i n g t e s t s t o b e r u n a t LRC.
It was l e a r n e d t h a t t h e U n i t a r y
P l a n Tunnel w i l l be down on t h e o r i g i n a l l y planned d a t e t o e n t e r t h e
t u n n e l (mid-July).
Consequently, t h e t e s t d a t e has been changed t o t h e
f i r s t of J u l y . The p r e s e n t model s t i n g e r , intended f o r AEDC, i s n o t
a d a p t a b l e f o r e i t h e r U n i t y P l a n o r 20-inch t u n n e l s of LRC. Drawings
llave been made f o r new s t i n g e r s , and t h e machining should commence
d u r i n g t h e l a s t week of May.
5. R a d i a t i o n and low d e n s i t y drag c o e f f i c i e n t view f a c t o r
program:
Checking o u t t h e r a d i a t i o n view f a c t o r computer program and
documentation of t h e Modified F r e e Molecular Drag Program continued.
Documentation of t h e R a d i a t i o n View F a c t o r Program was s t a r t e d d u r i n g
t h i s p e r i o d . A d d i t i o n a l funds t o c o n t i n u e work on t h i s s t u d y i n t h e
a r e a s of s p e c t r a l r a d i a t i o n , r e f l e c t e d r a d i a t i o n , and t h e use of t h e
contour i n t e g r a l method have been r e q u e s t e d .
6. O r b i t a l Workshop S o l a r Array: A thermal a n a l y s i s of t h e
S-IVB O r b i t a l Workshop s o l a r a r r a y has been i n i t i a t e d . This s t u d y
should be completed by t h e week of May 26.
E.
Unsteady Aerodynamics Branch
1.
S a t u r n I B Ground Winds
S t u d i e s f o r modifying a p r e v i o u s l y c o n s t r u c t e d S a t u r n I B
a e r o e l a s t i c wind t u n n e l model t o s i m u l a t e t h e AAP-2 and AAP-4 c o n f i g u r a t i o n s a r e b e i n g continued.
�P r e d i c t i o n s of ground-wind-induced l o a d s f o r S a t u r n I B ,
AS-205 v e h i c l e s i n t h e completely f u e l e d and empty weight c o n d i t i o n s
have been completed. These d a t a were published A p r i l 24, 1968.
A l l a v a i l a b l e S a t u r n I B wind t u n n e l t e s t d a t a were examined
I o r e s t a b l i s h i n g c r i t i c a l wind v e l o c i t i e s f o r t h e S a t u r n I B AS-205 i n
t h e i n t e r m e d i a t e weight c o n d i t i o n s . Recommendations f o r e s t a b 1 i s h i n g
t h e s e c r i t i c a l wind v e l o c i t i e s were published May 23, 1968.
2.
S a t u r n V Ground Winds
An o n - s i t e i n s p e c t i o n was made of t h e p r o g r e s s i n f a b r i c a t i o n of a n Uprated S a t u r n V ground winds model by Atkins and M e r r i l l ,
I n c . An e x t e n s i o n has been i n i t i a t e d t o t h e c o n t r a c t f o r t h e model
completion. The c o n t r a c t should be completed by mid-July.
A s t u d y f o r determining t h e second mode e f f e c t s on ground
wind l o a d i n g s of the S a t u r n V f u e l e d weight c o n d i t i o n i s i n p r o g r e s s .
P r e d i c t i o n of s t a t i c wind loads f o r t h e S a t u r n V v e h i c l e
w i t h t h e LUT and MSS c o n f i g u r a t i o n i s completed. These r e s u l t s should
be published s h o r t l y .
3.
I n f 1i g h t Acoustics
a . Systematic phase and amplitude d i s t o r t i o n s t h a t occurred
i n d a t a a c q u i s i t i o n and r e d u c t i o n systems used i n t h e f o u r - p e r c e n t AEDC
experiment have been determined e x p e r i m e n t a l l y by Baganoff and A s s o c i a t e s .
The r e s u l t s show t h a t we may c r o s s - c o r r e l a t e any two d a t a channels w i t h i n
a t a p e r e c o r d e r head and produce o n l y 0.2 db amplitude and 2.0 degree
phase d i s t o r t i o n s , and a c r o s s r e c o r d e r heads i t i s p o s s i b l e t o produce
f i n a l r e s u l t s w i t h a s c a t t e r band of 0.5 db amplitude and 5.0-degree
phase. These d a t a were p r e s e n t e d f o r t h e f u l l frequency r a n g e of 10
t o 20 k i l o h e r t z .
b . A d d i t i o n a l f l u c t u a t i n g p r e s s u r e d a t a r e c e i v e d from
Baganoff and A s s o c i a t e s w i l l be forwarded t o R-P&VE-S.
The v e r y l a r g e
volume of cross-power s p e c t r a l d e n s i t y i n f o r m a t i o n t o b e forwarded
r e p r e s e n t s f a i r l y comprehensive p r e l i m i n a r y r e s u l t s f o r t h e z e r o a n g l e
of a t t a c k c o n d i t i o n .
c . A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l
I n - f l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s "
i s being i n i t i a t e d .
Data from Ames f o u r p e r c e n t S a t u r n V , PSTL-1 and PSTL-2 wind t u n n e l
c o n d i t i o n s , and f l i g h t w i l l be used a s w e l l a s o t h e r d a t a a v a i l a b l e i n
t h e 1i t e r a t u r e .
�(1.
Kequcs ts f o r e s t i m a t e s of i n f l i g h t environments f o r
Lot~rspc.c i f i c , mod i f ied l a u n c l ~c o n f i g u r a t i o n s have been r e c e i v e d . These
conLi.gtlrations involve the use of t h e S a t u r n V b o o s t e r (a I B b o o s t e r w i t h
a C c ~ ~ t i l uupper
r
s t a g e ) . The environmental e s t i m a t e s f o r t h e s e conf i g u r a t i o n s w i l l be published a s soon a s p o s s i b l e .
e . The FEWG i n p u t f o r unsteady aerodynamic ( a c o u s t i c ,
f l u t t e r , e t c . ) i s i n t r a n s i t i o n and w i l l be t h e f u l l r e s p o n s i b i l i t y of
R-AERO-AU.
There a r e c o n s t r a i n t s f o r providing FEWG i n p u t d a t a which
w i l l c r e a t e i n c r e a s e d manpower e f f o r t f o r a p e r i o d of time b e f o r e and
a f t c r a f l i g h t . The a c o u s t i c problems i n meeting t h e AS-502 r e q u i r e ments of t h e FEWG a r e due mainly t o computer problems a t Comp. Lab.
Thcsc problems should be solved b e f o r e t h e n e x t f l i g h t ; o t h e r w i s e , t h e
n e x t FEWG r e p o r t may be delayed. The a d d i t i o n a l i n c r e a s e i n manpower
c f l o r t n e c e s s a r y f o r providing d a t a and a t t e n d i n g meetings f o r FEWG
i n p u t w i l l d e l a y t h e d e t a i l e d a n a l y s e s of t h e inhouse t e c h n i c a l evaluat i o n and a p p l i c a t i o n s of p a s t , c u r r e n t , and f u t u r e f l i g h t d a t a . Howe v e r , because of t h e AS-502 problems, t h e s e d a t a a r e b e i n g analyzed
inhouse a s f a s t a s they become a v a i l a b l e .
Also f i l m s have been r e q u e s t e d f o r a n a n a l y s i s of t h e
flame f r o n t s t a b i l i t y o r plume motion i n t h e f i v e h e r t z o s c i l l a t i o n s
observed on AS-502.
Houston has s e v e r a l of t h e f i l m s and a p p a r e n t l y
a r e r e l u c t a n t t o r e t u r n them. A n a l y s i s w i l l proceed when f i l m s become
available.
4.
Launch S i t e Acoustics
a . The conference on n o i s e a l l e v i a t i o n f o r s u b s o n i c a i r c r a f t , t o be h e l d a t Langley Research Center i n October 1968, w i l l be
t h e s u b j e c t of a planning meeting a t Headquarters on June 11. The
a b s t r a c t s f o r a l l t h e c e n t e r s ' p r e s e n t a t i o n s have been provided f o r t h e
MSFC p e r s o n n e l involved i n t h i s program. Three t e n t a t i v e papers a r e
planned from MSFC:
(1) a paper on t h e crossed-beam system of D r . Krause,
a paper on a c o u s t i c f o c u s i n g by 0 . E. Smith, and a t o p i c on p r o p a g a t i o n
ane excess ground a t t e n u a t i o n e f f e c t s by S. Guest.
b.
The v e h i c l e a c o u s t i c f l i g h t d a t a r e p o r t s f o r AS-501 and
502 a r e being prepared. Because of some d a t a s h o r t a g e s caused by computer
problems a t t h e Comp. Lab., d a t a s u b s t i t u t i o n s have been made which a r e
The a c o u s t i c a n a l y z e r
n o t meeting t h e o r i g i n a l requirements of R-AERO-AU.
system has been r e t u r n e d t o t h e manufacturer f o r r e p a i r s .
c . A program f o r t h e d e t e r m i n a t i o n of excess ground a t t e n u a t i o n i n t h e p r o p a g a t i o n of a c o u s t i c energy has been developed and i s working a t Lockheed f o r some 60 t e s t s of l a r g e b o o s t e r s o r r o c k e t engines a t
MSFC from 1965 t o 1967. The m e t e o r o l o g i c a l d a t a a r e t o be used i n t h i s
�program t o bcs t e v a l u a t e the d a t a a c q u i s i t i o n c o n d i t i o n s and t o look f o r
the POSS i b l e i n £ luence of s e a s o n a l v a r i a t i o n s on t h e ground impedance
f o r t l i i s s t u d y . Some 100,000 d a t a p o i n t s w i l l p e r m i t some s t a t i s t i c a l
e v a l u a t i o n of t h e r e s u l t s f o r f i e l d use under g i v e n c o n d i t i o n s .
d . The A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t T e s t Lab,
has been e f f e c t i v e l y s h u t down because of a n a p p a r e n t s h o r t a g e of manpower f o r o p e r a t i o n a l use. The S a t u r n V model p r e s s u r e amplitude and
phase i n f o r m a t i o n has thus been delayed and i s n o t of s u f f i c i e n t p r i o r i t y
i n T e s t Lab. t o a l l o w t e s t i n g i n t h e immediate f u t u r e . Other s i m i l a r
programs have l i k e w i s e ceased.
e . The R-AERO-AU i n p u t t o " P r e d i c t i o n s of B l a s t and Acoustic
Environments of Large Space Boosters," a j o i n t NASA/AF hazards manual,
has been completed. P r e l i m i n a r y d r a f t s of t h e hazards manual a r e
a n t i c i p a t e d t h i s summer.
f . P r e d i c t i o n of t h e A c o u s t i c Environment f o r t h e Nuclear
Ground T e s t Module i s approximately 80 p e r c e n t complete. These environmental e s t i m a t e s w i l l be r e l e a s e d i n a memorandum when completed.
5.
Panel F l u t t e r
Dynamic s t r a i n d a t a from t h e AS-~O~/S-IVBforward s k i r t
show evidence of panel f l u t t e r e x i s t i n g d u r i n g t h e s u p e r s o n i c f 1i ~ " '
regime. A f u l l r e p o r t i s being prepared.
6.
Quasi-Steady A n a l y s i s
T e s t d a t a from r e c e n t t e s t s on c o n v e c t i v e wake and f r e e
o s c i l l a t i o n models a r e p r e s e n t l y being reduced and a n a l y z e d . Flow
v i s u a l i z a t i o n t e s t s a r e planned i n June 1968, on a cone-cylinder-£ l a r e
body. Also, b a l l i s t i c range t e s t s a t BRL on Apollo forebody c o n f i g u r a t i o n s a r e now scheduled i n June 1968. F a b r i c a t i o n of t h e shock-induced
s e p a r a t i o n model (planned f o r f u t u r e t e s t i n g ) has been i n i t i a t e d .
VI.
DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Multi-Projects
1.
Mission P r o j e c t s
R e s t r i c t e d 3-Body Problems (New):
I n order t o l a y a base
f o r i n v e s t i g a t i o n i n t o f u t u r e m i s s i o n s t o t h e earth-moon 1i b r a t i o n p o i n t ,
t h e following s t u d y i s b e i n g performed. P e r i o d i c a s y m p t o t i c o r b i t s have
been t r a c e d s u c c e s s f u l l y from e q u a l mass r a t i o s , y = 0 , t o a mass r a t i o ,
y = 0.9.
The mass r a t i o y i s d e f i n e d :
�where M1 and M2 a r e t h e masses of t h e p r i m a r i e s . It i s hoped t h a t t h e
t r a c e can be s u c c e s s f u l l y c a r r i e d p a s t t h e c r i t i c a l mass r a t i o , y = 0.9229
..., t o t h e mass r a t i o of t h e earth-moon system, y = 0.9757
The
c r i t i c a l mass r a t i o is t h e mass r a t i o where t h e c h a r a c t e r i s t i c exponents
of t h e s o l u t i o n s t o t h e l i n e a r i z e d e q u a t i o n s i n t h e neighborhood of t h e
t r i a n g u l a r l i b r a t i o n p o i n t s change from complex t o pure imaginary. The
complex c h a r a c t e r i s t i c exponents g i v e r i s e t o s p i r a l i n g motion i n t o o r
o u t from t h e l i b r a t i o n p o i n t s , depending on whether t h e r e a l p a r t of t h e
complex number i s n e g a t i v e o r p o s i t i v e . The pure imaginary exponent
g i v e s r i s e t o p u r e l y p e r i o d i c motion s o t h a t when t h e c r i t i c a l mass
r a t i o i s passed the o r b i t s change t h e i r b a s i c n a t u r e from s p i r a l i n g
o r b i t s ( c a l l e d p e r i o d i c - a s y m p t o t i c ) t o p e r i o d i c o r b i t s i n t h e neighborhood of t h e t r i a h g u l a r l i b r a t i o n .
(DAO)
... .
2.
Guidance
a.
S-IVB S o f t Lunar Landing Study (Ref:
1968, p. 36)
February-March
A p r e s e n t a t i o n on t h e S-IVB s o f t l u n a r l a n d i n g s t u d y
s t a t u s was g i v e n t o t h e R-AERO-D s t a f f d u r i n g A p r i l . The s t a t u s review
covered t h e f o l l o w i n g t o p i c s :
(1)
(2)
Basic mission p r o f i l e .
An a n a l y t i c a l i n v e s t i g a t i o n of t h e changes i n
t h e i t e r a t i v e guidance e q u a t i o n s t o perform
3-dimens i o n a l r e t r o - b u r n s
.
(3)
Implementations and v e r i f i c a t i o n of t h e s e
changes.
(4)
A n a l y t i c development of a n i g n i t i o n c r i t e r i o n
f o r t h e l u n a r deboost and l u n a r l a n d i n g burns.
(5)
A p r e l i m i n a r y performance a n a l y s i s t o check t h e
o p t i m a l i t y and a c c u r a c y of t h e guidance scheme.
It was recommended t h a t performance improvement s t u d i e s b e i n i t i a t e d by
R-AERO-DA.
A t t h e p r e s e n t l e v e l of e f f o r t (112 man), t h e n e x t major
s t a t u s review w i l l be i n approximately one y e a r . The f o l l o w i n g items
w i l l be analyzed and r e p o r t e d on a t t h a t time:
�(I)
I n v e s t i g a t i o n of s i m p l i f i e d n a v i g a t i o n a l a i d s
(beacon, e t c . ) t o provide information f o r i n p u t
i n t o guidance scheme
.
b.
(2)
How t h i s i n f o r m a t i o n could be o b t a i n e d using curr e n t l y a v a i l a b l e hardware.
(3)
A d d i t i o n a l hardware, i f r e q u i r e d .
(4)
Boil-of f i n f o r m a t i o n from s t a g e c o n t r a c t o r s .
(5)
Optimum m i s s i o n p r o f i l e w i t h and w i t h o u t a b o i l off constraint.
(6)
Landing a t t i t u d e recommendations
(DGINorthrop)
mode.
-
u s i n g a hover
S-11, 2 Engines Out (New)
S - I 1 2-engines-out l o g i c was published i n a memorandum
a s a n a c t i o n item from a meeting between ASTR and AERO l a b s . This l o g i c
r e q u i r e s engine-out d i s c r e t e s i g n a l s . As f a r a s known, t h e d e c i s i o n t o
implement f o r two engines has n o t been made. Even w i t h t h i s l o g i c , t h e
S - I 1 s t a g e i s s t i l l n o t a d e q u a t e l y d e f i n e d a s f a r a s guidance i s concerned,
A memorandum d e f i n i n g t h e S - I 1 s t a g e by o t h e r than p r e - s e t burn times i s
b e i n g prepared.
This d e f i n i t i o n w i l l remove t h e requirement f o r engineso u t d i s c r e t e s i g n a l s . (DGA)
c.
LLM Midcourse C o r r e c t i o n (New)
A q u i c k a n a l y s i s of a n LLM midcourse c o r r e c t i o n , AV
budget has i n d i c a t e d t h a t t h e AV r e q u i r e d w i l l i n c r e a s e by a b o u t 20 p e r (DGA)
c e n t when t h e MCC i s delayed from 4 hours t o 10 hours a f t e r TLI.
3.
Dynamics and Control
a.
S t a g e S e p a r a t i o n Computer Program (New)
A two-part computer program t o s i m u l a t e s t a g e s e p a r a t i o n has been w r i t t e n and checked o u t i n F o r t r a n I1 f o r t h e SDS 930 comp u t e r . The f i r s t p a r t of t h e program s i m u l a t e s t h e r o t a t i o n a l motion of
a s i n g l e body i n a n i n e r t i a l c o o r d i n a t e system u n t i l changing f o r c e s
( i . e . , t h r u s t t a i l - o f f f o r c e s and r e t r o - f o r c e s ) s e p a r a t e t h e two b o d i e s .
Thcn t h e second p a r t of t h e program s i m u l a t e s t h e motion of t h e two
bodies i n s i x degrees of freedom and c a l c u l a t e s t h e r e l a t i v e p o s i t i o n
v c c t o r between a r b i t r a r y p o i n t s ( s p e c i f i e d i n t h e program i n p u f ) expressed
i n a c o o r d i n a t e system f i x e d i n one of t h e b o d i e s . The program i s g e n e r a l
i n t h e s e n s e t h a t i t can be used w i t h v a r i o u s c o n f i g u r a t i o n s . Use of t h e
930 computer e l i m i n a t e s much turn-around time.
(DC)
�b.
Local Angle-of-Attack
Response (New)
E f f e c t s on Vehicle Dynamic
The downwash normal f o r c e d i s t r i b u t i o n of a d e f l e c t e d
v e h i c l e i s being computed. An aerodynamic t r a n s f o r m a t i o n was d e r i v e d
t h a t c a r r i e s t h e p a r t i a l d i f f e r e n t i a l e q u a t i o n from C a r t e s i a n c o o r d i n a t e s
i n t o t h e c o o r d i n a t e s of a d e f l e c t e d body. A method of e v a l u a t i n g g e n e r a l ized bending f o r c e s , a s w e l l a s a e r o e l a s t i c e f f e c t s , is being developed.
(DD/~hrysler)
c.
S t r u c t u r a l Damping Research (New)
Two c o n t r a c t s a r e being awarded t o Lockheed f o r s t u d i e s
of s t r u c t u r a l damping. The f i r s t w i l l a t t e m p t t o c o r r e l a t e t h e damping
of t h e 115 s c a l e model of t h e S a t u r n I v e h i c l e w i t h t h e damping of i t s
components and t h e a n a l y t i c a l energy d i s t r i b u t i o n . Work under t h e second
c o n t r a c t w i l l a t t e m p t t o s i m i l a r l y p r e d i c t t h e s t r u c t u r a l damping of t h e
AAP C l u s t e r . Some t e s t i n g w i l l b e done t o provide b a s e l i n e and v e r i f i c a (D~SI~ockheed)
tion data.
d.
Damping of Liquid O s c i l l a t i o n s by Wall Roughness (New)
The e f f e c t s of w a l l roughness on t h e damping of l i q u i d
o s c i l l a t i o n s i n a r e c t a n g u l a r b a s i n a r e being i n v e s t i g a t e d . The b a s i n
i s made of g l a s s (20" x 10" x 10") and t h e t e s t l i q u i d i s w a t e r p l u s two
p a r t s p e r thousand Aerosol MA. The f i r s t s l o s h made i s e x c i t e d by a p p l y ing a p e r i o d i c f o r c e t o t h e b a s i c p a r a l l e l t o t h e 20-inch dimension. Some
of t h e r e s u l t s a r e a s f o l l o w s :
(1) With a 9-inch d e p t h , t h e presence of 3-inch by
10-inch s t r i p s of !/lo g r i t (approximately 1110-inch diameter p a r t i c l e s )
on t h e 10-inch wide tank ends w i t h t h e lower edge of t h e s t r i p s 7 inches
from t h e tank bottom caused a 65 p e r c e n t i n c r e a s e i n t h e l o g decrement
of t h e f r e e decay compared t o t h e smooth w a l l v a l v e .
2) The presence of i/30 g r i t (approximately 03-inch
d i a m e t e r ) i n s t r i p s \ caused a 23 p e r c e n t i n c r e a s e i n damping over t h e
smooth-wall v a l v e .
( 3 ) A s expected from r i n g b a f f l e s t u d i e s , roughness
near t h e tank bottom i s much l e s s e f f e c t i v e i n i n c r e a s i n g t h e damping
than roughness i n c o n t a c t w i t h t h e l i q u i d s u r f a c e .
(One-inch roughness
s t r i p s a t t h e s u r f a c e were o n l y s l i g h t l y l e s s e f f e c t i v e t h a n t e n - i n c h
s t r i p s covering t h e e n t i r e end w a l l s .) (DDS)
�1.
Dynamics and Control
a.
S a t u r n V Launcher
Ana 1y s i s (New)
-
Umbilical Tower V i b r a t i o n
Methods a r e being developed f o r e v a l u a t i n g t h e v i b r a t i o n a l c h a r a c t e r i s t i c s of t h e S a t u r n V l a u n c h e r - u m b i l i c a l tower combina-
t i o n . A method of a n a l y s i s and d i g i t a l computer programs a r e a l s o being
developed f o r determining t h e modes and f r e q u e n c i e s of l a r g e s p a c e frames.
The program f o r a n a l y z i n g s p a c e frames, which uses a
r e p e t i t i v e s o l u t i o n technique, has been checked o u t w i t h a r e l a t i v e l y
(DDS/Lockheed)
s m a l l plane frame problem.
b.
S a t u r n V, S-IVB Coast S t a b i l i t y (New)
A s e r i e s of s i m u l a t i o n runs has been made t o s t u d y
t h e dynamics of t h e S-IVB s t a g e a f t e r second burn. The mass of propell a n t l e f t on board was v a r i e d , and t h e v e h i c l e s continuous v e n t system
was turned o f f , This would permit t h e p r o p e l l a n t t o s e a t i n t h e upper
domes of b o t h t a n k s under t h e i n f l u e n c e of aerodynamic d r a g . R e s u l t s
of t h e s e runs show t h a t t h e v e h i c l e can be c o n t r o l l e d by t h e APS system.
A d d i t i o n a l r u n s w i l l b e made t o confirm t h i s f o r v e r y low f l u i d l e v e l s .
Tllc o b j e c t i v e of t h e s t u d y w i l l be t o d e f i n e t h e l i m i t s on t h e amount
of t h e p r o p e l l a n t l e f t on board f o r which t h e v e h i c l e i s s t a b l e , w i t h o u t
t h e continuous v e n t system.
(DDS)
c.
S a t u r n V T h e o r e t i c a l T r a n s f e r Function Study (New)
The f l i g h t mechanic yaw e q u a t i o n s of motion and cont r o l have been formulated f o r S a t u r n V. These e q u a t i o n s i n c l u d e f o u r
bending modes and t h e f i r s t s l o s h mode f o r each p r o p e l l a n t tank. S l o s h
n o n l i n e a r i t i e s i n damping c o e f f i c i e n t s a r e b e i n g i n c l u d e d . The e f f e c t
of wind p e n e t r a t i o n i s a l s o b e i n g e v a l u a t e d . T h e o r e t i c a l t r a n s f e r funct i o n f o r t h e S a t u r n V v e h i c l e w i l l be determined f o r t h e b o o s t phase.
Comparisons w i t h f l i g h t d a t a w i l l be made f o r model v e r i f i c a t i o n .
dynamic S c i e n c e )
d.
L o n g i t u d i n a l I n s t a b i l i t y of t h e S a t u r n V Vehicle
(Pogo) (New)
A r e p r e s e n t a t i v e mathematical model of t h e v e h i c l e
l o n g i t u d i n a l s t r u c t u r a l modes, p r o p e l l a n t t a n k s , p r o p e l l a n t s u c t i o n
l i n e s , pumps, and engine t h r u s t c h a r a c t e r i s t i c s a r e being formulated
Tor t h e S a t u r n V t o s t u d y t h e i r coupled i n t e r a c t i o n (Pogo) e f f e c t a s
w i t n e s s e d from t h e f l i g h t t e s t r e s u l t s of S a t u r n 502. This system
�w i l l kc analyzed i n the l o n g i t u d i n a l mode by determining Nyquist s t a b i l i t y p l oLs ([sing a d i g i t a l s o l u t i o n .
Concurrently, t h i s l o n g i t u d i n a l
ins ~ ; t ib1 i t y w i l l a l s o be simulated on t h e hybrid 650 analog computer.
' r l ~ c , ~ ~ n a l oco~nputcr
g
o f f e r s wide range i n n o t o n l y s i m u l a t i n g t h e l o n g i t u d i n a l i n s t a b i l i t y b u t i n r a p i d l y e v a l u a t i n g p o t e n t i a l " f i x e s " by means
oP parameter v a r i a t i o n s . A coupled l o n g i t u d i n a l - l a t e r a l a n a l y s i s w i l l
a l s o be s t u d i e d on analog equipment.
(Dc/DD/~orthrop)
e.
Second F l i g h t S t a g e , Dual Engine Out Control
Anal ys i s (New)
The a n a l y s i s of d u a l engine f a i l u r e i n t h e second f l i g h t
s t a g e of t h e S a t u r n V has been i n i t i a t e d . A s t a b i l i t y a n a l y s i s has been
performed on a system model which included p i t c h - r o l l coupling. Prel i m i n a r y r e s u l t s i n d i c a t e a low c o n t r o l system frequency and a damping
r a t i o l e s s than 20 p e r c e n t d u r i n g second s t a g e f l i g h t f o r c o n d i t i o n s of
two c o n t r o l engines o u t . The response a n a l y s i s of t h i s system has been
i n i t i a t e d . The model i n c l u d e s t h e a p p r o p r i a t e guidance maneuver r e s u l t ing from two engines o u t , a l t h o u g h t h e guidance and c o n t r o l a r e uncoupled
(DC)
i n the present simulation.
f.
S-111s-IVB S e p a r a t i o n
w i t h No T i l t A r r e s t (New)
The e f f e c t of c o n t i n u i n g t h e guidance cormnands u n t i l
engine c u t o f f on t h e S-111s-IVB s e p a r a t i o n of t h e AS-503 " B o i l e r p l a t e "
conf i g u r a t i o n i s being s t u d i e d . According t o p r e l i m i n a r y r e s u l t s , t h e
separation clearance i s r e l a t i v e l y i n s e n s i t i v e t o the turning r a t e a t the
beginning of s e p a r a t i o n , and i f a l l retro-motors o p e r a t e , c o n t i n u a t i o n
of t h e guidance commands w i l l n o t j e o p a r d i z e s e p a r a t i o n c l e a r a n c e , I f
one r e t r o - m o t o r f a i l s , t h e r e s u l t i n g plume impingement f o r c e on t h e i n t e r
s t a g e a d a p t e r reduces t h e c l e a r a n c e between t h e S-IVB s t a g e engine b e l l
and t h e top of t h e i n t e r s t a g e a d a p t e r by 85 p e r c e n t of t h e a v a i l a b l e
c l e a r a n c e . I f r e t r o - m o t o r misalignment t o l e r a n c e s ( l o ) -- e . g . , o f f s e t
t o l e r a n c e (6" l o n g i t u d i n a l and 2" l a t e r a l )
and r o t a t i o n r a t e v a r i a t i o n ( . 5 " / s e c ) a r e imposed on t h e r e t r o - o u t c o n d i t i o n , t h e r e s u l t i n g 3 0
v a r i a t i o n t a k e s a n o t h e r 1 4 t o 15 p e r c e n t of t h e a v a i l a b l e c l e a r a n c e ,
depending on t h e t u r n i n g r a t e a t t h e beginning of s e p a r a t i o n (guidancecommand i n f l u e n c e d ) and which r e t r o - m o t o r f a i l s . I f t h e i n i t i a l t u r n i n g
r a t e i s one d e g / s e c nose-down, t h e 3 0 envelope c l e a r s f o r any retro-motoi
o u t . I f i t i s one d e g l s e c nose-up, t h e 30 envelope c l e a r s f o r a lower
r c t r o - m o t o r o u t ( f i n p o s i t i o n A o r D), and t h e p r o b a b i l i t y of c l e a r i n g
i s b e t t e r than 99 p e r c e n t f o r a n upper retro-motor o u t .
(DC)
--
�3.
I'rojcct
a.
Information A p p l i c a b l e t o I n d i v i d u a l Vchicles
AS-503 Dynamic Data f o r A l t e r n a t e Miss i o n A f t e r
Payload S e p a r a t i o n (New)
A document c o n t a i n i n g t h e c u r r e n t bending and t o r s i o n
d a t a f o r t h e AS-503 a l t e r n a t e m i s s i o n a f t e r payload s e p a r a t i o n has been
completed. The a n a l y s i s was made using t h e assumption t h a t t h e SLA
panels a r e j e t t i s o n e d f o r t h e m i s s i o n . This document i s t o be d i s t r i buted under cover memorandum R-AERO-DD-107-68.
An e a r l i e r a n a l y s i s was
conducted w i t h t h e SLA panels i n t a c t and deployed 45"; t h e r e s u l t s of
tlla t a n a l y s i s were published under memorandum R-AERO-DD-102-68.
It i s
c u r r e n t l y planned t h a t t h e SLA panels w i l l be j e t t i s o n e d .
(~~S/~oeing)
b.
AS-503 Dynamics Data (Ref:
Dec. 1967-Jan. 1968)
A complete r e v i s i o n of dynamic d a t a f o r AS-503 was
made t o update t h e t h i r d f l i g h t c o n f i g u r a t i o n l a t e r a l dynamic charact e r i s t i c s t o i n c l u d e t h e e f f e c t s of c u r r e n t mass d a t a and a more d e t a i l e d
mathematical model and t o i n c l u d e yaw modes. There a r e a l s o c o r r e c t e d
t o r s i o n a l dynamic c h a r a c t e r i s t i c s f o r t h e S-IVB b o o s t p o r t i o n of t h e
f l i g h t . A f t e r review, t h i s document w i l l be d i s t r i b u t e d under cover
memorandum R-AERO-DD-108-68.
(~~Sf~oeing)
c.
AAP
1.
Cluster
a.
Miss i o n P r o f i l e
(1)
Vis i b i l i t y of t h e Ear th-Moon L i b r a t i o n
P o i n t s from ATM (New)
A new a c t i o n has been i n i t i a t e d t o s u p p o r t t h e ATM
m i s s i o n a t t h e r e q u e s t of Space Sciences Laboratory. One of t h e e x p e r i ments on board (HAO) i s a s o l a r coronagraph w i t h a 3" f i e l d of view. During experiment o p e r a t i o n , i t i s always c e n t e r e d on t h e sun. It has been
proposed t o use t h i s i n s t r u m e n t t o view t h e t r i a n g u l a r l i b r a t i o n p o i n t s
L4 and L5 of t h e earth-moon system whenever t h e s e p o i n t s pass w i t h i n
t h e 3O f i e l d of view of t h i s i n s t r u m e n t . The a c t i o n taken h e r e has been
t o determine when t h e s e l i b r a t i o n p o i n t s w i l l pass w i t h i n the 3 " f i e l d
o i view of t h i s instrument. A s e t of e q u a t i o n s t o determine t h e a n g u l a r
displacement of L4 and 25 from t h e l i n e of s i g h t between t h e ATM and t h e
sun have been d e r i v e d and s e n t t o t h e Computation L a b o r a t o r y t o b e
included i n t h e N-body deck. Checkout of t h e s e e q u a t i o n s i s expected
t o b c g i n w i t h i n a b o u t two weeks. Some p r e l i m i n a r y c a l c u l a t i o n s have
i n d i c a t e d t h a t t h e r e a r e two 35-day p e r i o d s d u r i n g each y e a r , each period
�s e p a r a t e d by s i x months, d u r i n g which t h i s experiment i s p o s s i b l e ( t h i s
i s clue t o t h e s m a l l f i e l d of view of t h e instrument and t h e f a c t t h a t i t
i s always c e n t e r e d on t h e s u n ) . These two times of y e a r correspond t o
t h e two i n t e r s e c t i o n s of t h e moon's o r b i t plane w i t h t h e e c l i p t i c plane.
The times of t h e s e two i n t e r s e c t i o n s change g r a d u a l l y from y e a r t o y e a r
and thus have t o be determined f o r any s p e c i f i e d y e a r . For t h e y e a r s
1970-71 t h e i n t e r s e c t i o n s occur on October 25, 1970 and A p r i l 25, 1971.
T h i r t y - f i v e - d a y p e r i o d s c e n t e r e d on t h e s e two d a t e s g i v e t h e times during which t h i s experiment i s p o s s i b l e .
(DAO)
(2)
E a r t h Resources Experiment Impact on C l u s t e r I
Miss i o n (New)
A q u i c k r e s p o n s e s t u d y was i n i t i a t e d t o provide
t h e m i s s i o n impact of adding e a r t h r e s o u r c e s experiments t o t h e p r e s e n t
c l u s t e r . This s t u d y was undertaken i n s u p p o r t of t h e Luskin Committee
r e p o r t on May 15. Because of t h e e a r t h r e s o u r c e s experiment r e q u i r e ments f o r d a t a a t l a t i t u d e s h i g h e r t h a n 29", a t r a d e o f f of m i s s i o n
l e n g t h , payload, and a l t i t u d e was made. By lowering d e s i r e d l i f e t i m e t o
270 d a y s , t h e workshop a l t i t u d e could be lowered t o 200 NM. Keeping t h e
same workshop i n j e c t i o n weight a s p r e s e n t l y planned allowed t h e i n c l i n a t i o n t o be i n c r e a s e d t o approximately 35 d e g r e e s . A t t h i s a l t i t u d e and
i n c l i n a t i o n , a s i n g l e U P - 1 launch o p p o r t u n i t y can b e provided every
4 days. By " f i n e tuning" t h e i n c l i n a t i o n t o 34.26 degrees two launch
o p p o r t u n i t i e s p e r day can be provided every f o u r days. The time between
t h e two AAP- 1 launch o p p o r t u n i t i e s i s approximately f i v e h o u r s . Targeting f o r t h e AAP-2 workshop o r b i t and U P - 1 launch o p p o r t u n i t i e s was proThe d e s i r a b i l i t y of
v i d e d t o g e n e r a t e launch v e h i c l e t r a j e c t o r i e s
p r o v i d i n g two launch o p p o r t u n i t i e s per day i s b e i n g d i s c u s s e d w i t h i n
NASA. Items t o be considered i n c l u d e launch a b o r t r e c o v e r y l i g h t i n g ,
rendezvous l i g h t i n g , e a r t h r e s o u r c e s experiment 1i g h t i n g , and e a r l i e s t
r e c o v e r y l i g h t i n g . Also t o be considered a r e range s a f e t y c o r r i d o r s and
placement of r e c o v e r y f o r c e s . Work c o n t i n u e s t o s u p p o r t more d e t a i l e d
p r e s e n t a t i o n s t o NASA h e a d q u a r t e r s i n June 1968.
(DAO)
.
(3)
E a r t h Resources Experiment Impact on MP-112
(New)
A s t u d y has been undertaken t o determine t h e comp a t i b i l i t y of seven e a r t h r e s o u r c e s experiments w i t h t h e AAP-L/Z m i s s i o n .
The a r e a of prime i n t e r e s t of t h e s e experiments is t h e USA w i t h some
experiments cons t r a i n e d t o d a y l i g h t viewing.
The t o t a l time over t h e USA d u r i n g
s i o n was determined f o r b o t h 29" and 35" i n c l i n e d o r b i t s
a l t i t u d e . Four o r f i v e o p p o r t u n i t i e s p e r day occur w i t h
t h e USA b e i n g a n average of 10 minutes i n l e n g h t . These
were t h e n i n t e g r a t e d w i t h t h e b a s i c crew c y c l e and t h e A
t h e 28-day misa t a 220 n.mi.
t h e passes over
opportunities
A P - ~ biomedical
/~
�experiments, r e s u l t i n g i n 48 USA passes o r approximately 9 hours of
over-USA time a v a i l a b l e f o r a s t r o n a u t monitoring of t h e e a r t h r e s o u r c e s
expcr iments
.
L i g h t i n g over t h e USA i s a f u n c t i o n of launch time.
A l a t e morning launch a f f o r d s f a v o r a b l e USA l i g h t i n g e a r l y i n t h e 28-day
m i s s i o n , a n evening launch t h e mid-mission days, and a n i g h t launch t h e
l a t t e r miss i o n days.
(DAM)
(4)
J - 2 s D i r e c t Rendezvous (New)
An i n v e s t i g a t i o n of t h e use of t h e J - 2 s engine t o
provide f o r d i r e c t rendezvous c a p a b i l i t y has begun. The p r o f i l e cons i s t s of S-IB and S-IVB h i g h t h r u s t phases w i t h u s e of t h e J-2s engine
i d l e mode (5000 l b . t h r u s t ) f o r t h e t e r m i n a l rendezvous p o s i t i o n and
v e l o c i t y c o n t r o l . By v a r y i n g t h e l e n g t h of i d l e mode burn, a launch
window can be provided. When a p p l i e d t o t h e AAP-4 unmanned rendezvous
problem, a 30-second launch window can be provided by v a r y i n g t h e l e n g t h
of t h e i d l e mode from approximately 900 t o 600 seconds. The payload t r a d e o f f f o r t h i s window i s approximately 1000 l b s . ; however, t h e payload
i n c r e a s e due t o J-2S engine t h r u s t and s p e c i f i c impulse improvement i s
a b o u t 2500 pounds.
The n e t i n c r e a s e over t h e p r e s e n t AAP-4 v e h i c l e
c a p a b i l i t y i n t o a 220 NM o r b i t would be i n t h e o r d e r of 1500 pounds.
The S-IVB t h r u s t s t r u c t u r e would n o t r e q u i r e beef-up because t h e J-2s
t h r u s t was h e l d t o t h e p r e s e n t t h r u s t s t r u c t u r e c a p a b i l i t y (240,000 I b
thrust).
Cost and s c h e d u l e c o n s i d e r a t i o n s would probably r u l e o u t t h e
a p p l i c a t i o n of t h e J-2S engine f o r t h e AAP-4 unmanned rendezvous v e h i c l e ;
however, i t s f u t u r e use f o r a n unmanned l o g i s t i c s c a r r i e r and a s a r e s c u e
v e h i c l e s h o u l d b e noted.
( ~ ~ 0 1 ~ p p lA
i enda l y s i s )
(5)
-
Unmanned Rendezvous
Using S-IVB Stage (Ref:
February-March 1968, p. 4 4 ) .
The S-IVB unmanned rendezvous s t u d y i s c o n t i n u i n g
i n o r d e r t o r e f i n e m i s s i o n p r o f i l e s e l e c t i o n and t o provide a b a s i s upon
which t h e p r o f i l e can be implemented. P r e s e n t a t i o n s on t h e s t u d y were
n u d e t o t h e MSC AAP program o f f i c e on A p r i l 4 , 1968 and t o D r . von Braun
on May 1, 1968. A review of t h e s t u d y was a l s o made t o t h e Miss i o n
Rcquiremcnts Panel on May 22, 1968.
An a n a l y s i s of t h e guidance and n a v i g a t i o n
a c c u r a c i e s a t t h e second S-IVB c u t o f f r e s u l t e d i n t h e n e c e s s i t y of
p r o v i d i n g a c o n s t a n t d e l t a h e i g h t burn a s soon a s p o s s i b l e a f t e r t h e
S-IVB second burn. The maximum s i z e of t h i s burn i s 10.8 m e t e r s p e r
second. An a l t e r n a t e mode would b e t o burn i n t o a n e l l i p t i c a l o r b i t
w i t h t h e proper energy d i f f e r e n t i a l .
�The plane change burn r e q u i r e s yawing t o a n a l t i tr~tlc apl'roximna t e l y pcrpcnd i c u l a r t o t h e o r b i t a l plane.
Because of t h e
ST- 1 24 M p l a t f o r m i n n c r gimbal (yaw) 1i m i t of 45 d e g r e e s , p r e l i m i n a r y
d i s cuss ions w i t h As t r i o n i c s people have been h e l d . These d i s c u s s ions
have pointed o u t t h a t k i t s t o modify t h e ST-124 M p l a t f o r m t o a 4-gimbal
c o n f i g u r a t i o n have been purchased f o r t h e S a t u r n program. The impact
of t h i s m o d i f i c a t i o n i s being considered a t A s t r i o n i c s
.
I n designing the t r a j e c t o r i e s f o r the terminal
rendezvous phase of a m i s s i o n , t h e r e a r i s e s a need f o r a r a p i d method
of i n v e s t i g a t i n g t h e c h a r a c t e r i s t i c s of a g r e a t number of p r o f i l e s .
These c h a r a c t e r i s t i c s i n c l u d e p r o p e l l a n t r e q u i r e m e n t s , t i m i n g , l i g h t i n g , t e r m i n a l approach a n g l e s , sens i t i v i t y t o e r r o r s i n measuring t h e
r e l a t i v e p o s i t i o n s and v e l o c i t i e s , and e r r o r s i n making t h e p r o p u l s i v e
maneuvers. During t h i s p e r i o d , s e v e r a l monograms were developed which
a i d i n t h e i n v e s t i g a t i o n of t h e s e p r o f i l e s
These monograms g i v e t h e
r e l a t i v e v e l o c i t y v e c t o r s a t t h e i n i t i a t i o n and f i n a l i z a t i o n of t h e
t e r m i n a l phase a s a f u n c t i o n of t h e r e l a t i v e p o s i t i o n v e c t o r and t h e
time t o be s p e n t i n performing the t e r m i n a l phase.
.
The use of t h e LM rendezvous r a d a r f o r t h e v e r n i e r
burns has been s t u d i e d i n terms of range, range r a t e , and antenna e l e v a t i o n a n g l e e r r o r s . Based upon t h e 3 0 random and b i a s e r r o r s provided by
MSC, t h e e r r o r i n TPF p o s i t i o n was found t o be approximately 5 k i l o m e t e r s i f t h e r a d a r ' d a t a were used t o compute t h e TPI burn. T h e r e f o r e ,
a midcourse c o r r e c t i o n w a s added t o t h e t e r m i n a l phase p r o f i l e .
Weight and performance c o n s i d e r a t i o n s due t o
adding r e s t a r t c a p a b i l i t y t o t h e p r e s e n t S-IVB s t a g e a r e b e i n g s t u d i e d
by P&VE L a b o r a t o r y and Douglas. The I U system problems involved i n
i n t e r f a c i n g w i t h t h e LM rendezvous r a d a r a r e b e i n g pursued by
( D A O / N tOh~r o p )
As tr i o n i c s Lab.
(6)
AAP-4 LM/ATM Unmanned Rendezvous (Ref:
February-March 1968, p. 45)
-
F u r t h e r a n a l y s i s of t h e S-IVB
LM/ATM unmanned
rendezvous w i l l c o n t i n u e . A d e t a i l e d performance d i s p e r s i o n a n a l y s i s
and n a v i g a t i o n a l a n a l y s i s w i l l be performed s o that a more e x a c t APS
p r o p e l l a n t budget can be d e t i n e d . The guidance requirements f o r t h e
low /\V t r a n s f e r maneuvers a r e a l s o b e i n g a n a l y z e d , a s w e l l as navigat i o n u p d a t e s , u s i n g r a d a r i n f o r m a t i o n s o t h a t launch v e h i c l e d i g i t a l
computer s t o r a g e requirements can b e determined.
A q u i c k look a t t h e u s e of IGM t r a j e c t o r y shaping
i n S - I B s t a g e a f t e r max q i n d i c a t e s t h a t approximately 900 l b s of payload a t o r b i t a l i n s e r t i o n can b e achieved w i t h a 1 0 p e r c e n t i n c r e a s e i n
s t r u c t u r a l l o a d s . This may be needed a t a l a t e r d a t e i f payload problems
occur w i t h t h e 2nd S-IVB s t a g e i g n i t i o n made i n a c h i e v i n g rendezvous.
(DG)
�(7)
AAP-3A Launch Opportunity and Rendezvous
A n a l y s i s (Ref: February-March 1968, p. 40)
AAP-3A l i f t - o f f i s scheduled (ML-13) t o occur
a f t e r day 119 ( r e f e r e n c e d t o AAP-2 l a u n c h ) . This a l l o w s 28 days f o r
t h e AAP-1 m i s s i o n and 90 days f o r s t o r a g e b e f o r e AAP-3A miss i o n i s
s t a r t e d . Two n e a r i n - p l a n e inphase launch o p p o r t u n i t i e s occur on day
129 a f t e r AAP-2 launch. The p r e v i o u s l y c a l c u l a t e d AAP-1 and a n g l e d i d
n o t s a t i s f y t h e l i g h t i n g c o n s t r a i n t s . That i s , nominal t e r m i n a l phase
i n i t i a t i o n (TPI) occurs i n darkness s o t h a t t h e t a r g e t can be o p t i c a l l y
t r a c k e d a g a i n s t a s t e l l a r background. A l s o , t h e t e r m i n a l phase f i n a l i z a t i o n (TPF) maneuver occurs a t a t i m e e q u i v a l e n t t o 140° of t a r g e t
t r a v e l l a t e r and i s planned t o occur a t s u n r i s e t o o b t a i n t h e d e s i r e d ,
v i s i b i l i t y d u r i n g t h e docking maneuvers. The time from p u r s u i t launch
t o rendezvous was optimized t o s a t i s f y t h e AAP-3A rendezvous l i g h t i n g
c o n s t r a i n t s . The r e s u l t i n g t a r g e t l e a d a n g l e a t AAP-3A launch was found
t o be 4.704 d e g r e e s . The time from UP-3A launch t o rendezvous i s
5 hours 21 minutes 52.7 seconds, and t h e t o t a l AV r e q u i r e d i s 136 m/s.
This s t u d y i s now being documented.
(DAO)
(8)
Data Bank (New)
The f i r s t monthly s t a t u s r e p o r t of t h e M a r t i n
~ a r i e ~ ts a Data
'
Bank (R-AERO-DAM-27-68) i s being d i s t r i b u t e d . The d a t a
bank i s a computerized d a t a s t o r a g e and r e t r i e v a l system f o r c o l l e c t i n g ,
m a i n t a i n i n g , r e t r i e v i n g and r e p o r t i n g d a t a concerning d e s c r i p t i o n s of
The s t a t u s r e p o r t provides a c u r r e n t and conplanned AAP experiments,
s o l i d a t e d r e f e r e n c e t o t h e AAP experiment i n f o r m a t i o n c o n t a i n e d i n t h e
d a t a bank. Capsule i n f o r m a t i o n such a s experiment number, t i t l e , ob ject i v e , crew time, experiment time r e q u i r e m e n t s , w e i g h t , volume, peak
power, e t c . , a r e g i v e n f o r each experiment. Most of t h e c a n d i d a t e
AAP-112 experiments a r e contained i n t h e d a t a bank. However, t h e bank
i s c o n t i n u o u s l y being updated and does n o t y e t c o n t a i n G A A P c a n d i d a t e
experiments.
A s t a t u s r e p o r t of t h e d a t a bank w i l l be published
monthly. This f i r s t r e p o r t had a l i m i t e d d i s t r i b u t i o n . D i s t r i b u t i o n of
(DAMIMartin)
Later r e p o r t s w i l l be i n c r e a s e d i f necessary.
(9)
*
Des i g n Reference Miss i o n Document
(DRMD) (Ref: February-March 1968, p. 39)
The AAP-112 Design Reference Mission Document has
been r e c e i v e d from M a r t i n M a r i e t t a and d i s t r i b u t i o n f o r comments has been
made under cover memorandum R-AERO-DAM-28-68.
The DRMD i s a comprehensive
survey of t h e AAP-1/2 m i s s i o n from launch of AAP-2 t o t h e r e c o v e r y of
CM-1 and c o n s i s t s of s i x volumes a s follows:
�Volume I
Volume I1
Volume I11
VolumeIV
Volume V
Volume V I
b.
-
Miss i o n Des c r i p t i o n
- Detailed Orbit Trajectory
- Design Engineering I n t e g r a t e d
Miss i o n Time1 i n e
-AttitudeMissionTimeline
I n t e g r a t e d Miss i o n Sys tems
D e s c r i p t i o n s and Requirements
A l t e r n a t e Mission and Contingency
Plans.
-
-
Guidance
(1)
AAP-3 Guidance C o m p a t i b i l i t y A n a l y s i s (New)
A meeting was h e l d on A p r i l 14, 1968, between t h e
guidance people of MSFC and MSC t o d i s c u s s t h e p o s s i b l e causes of a c t i o n
t o be taken concerning t h e AAP-3 launch v e h i c l e guidance c o m p a t i b i l i t y
f o r a n a s c e n t t o a n 81 x 120 n.mi. e l l i p s e u s i n g t h e S-IB, S-IVB, and
CSM s t a g e s t o a c h i e v e a p e r i g e e i n s e r t i o n , There a r e s e v e r a l p o s s i b i l i t i e s a v a i l a b l e f o r t h e AAP-3 m i s s i o n . The t r u e s t a g e IGM e q u a t i o n s
could be used t o s t e e r t h e S-IVB s t a g e s t o a n a i r p o i n t , s l i g h t l y beyond
S-Ill3 f u e l d e p l e t i o n , t h a t has been s e l e c t e d from a n optimized t r a j e c t o r y
t o o r b i t a l i n s e r t i o n . Our a n a l y s i s showed t h a t compatible take-over
c o n d i t i o n s r e s u l t e d f o r e i t h e r t h e CSM u s i n g c r o s s -product s t e e r i n g o r
one-stage IGM e q u a t i o n s . The CSM n a v i g a t i o n system, because of t h e gyro
compassing t e c h n i q u e of l a y i n g t h e launch azimuth, makes i t d e s i r a b l e
t o e n f o r c e t h e d e s i r e d o r b i t a l p l a n e a t S-IVB f u e l d e p l e t i o n s o t h a t
o n l y p i t c h s t e e r i n g w i l l be r e q u i r e d of t h e CSM t o a c h i e v e o r b i t a l
i n s e r t i o n . The guidance people of MSC i n d i c a t e d t h a t t h e most d e s i r a b l e
system from a complete c o m p a t i b i l i t y s t a n d p o i n t would be f o r t h e S-IVB
s t a g e t o use two-stage yaw s t e e r i n g and t h r e e - s t a g e p i t c h s t e e r i n g and
use t h e one-stage IGM e q u a t i o n s i n t h e CSM. They a l s o i n d i c a t e d t h a t
i t would be d i f f i c u l t t o s e l l t h e change i n guidance e q u a t i o n s t o t h e i r
management s i n c e t h e c r o s s - p r o d u c t s t e e r i n g would do t h e t a s k f o r t h e
AAP-3 m i s s i o n . The b a s i c rendezvous phasing c a p a b i l i t y of t h e G
IM system
LN/ATM
was p o i n t e d o u t , and some bakcground m a t e r i a l from t h e S-IVB
unmanned rendezvous s t u d y w a s p r e s e n t e d i n t h e hope t h a t i t would
s t r e n g t h e n t h e i r argument f o r a more compatible system w i t h MSC management. The f i n a l d e c i s i o n was delayed u n t i l a l a t e r d a t e s o t h a t MSC
could be s u r e t h a t any d e c i s i o n made would n o t j e o p a r d i z e f l e x i b i l i t y
f o r l a t e r missions.
(DG)
-
�c.
Dynamics and Control
(1)
CMG Maximum Volume C o n t r o l Law (New)
For t h e CMG c o n t r o l l a w c u r r e n t l y proposed, t h e
momentum v e c t o r s of t h e i n d i v i d u a l CMG' s a r e o r i e n t e d i n a n i s o g o n a l
d i s t r i b u t ion t o eliminate the " a n t i - p a r a l l e l " condition.
The i s o g o n a l
d i s t r i b u t i o n has been i n v e s t i g a t e d and found t o p o s s e s s a n extreme
p r o p e r t y ; t h a t i s , t h e volume formed by t h e t h r e e gyromomentum v e c t o r s
i s a maximum. This i n v e s t i g a t i o n was c a r r i e d o u t i n o r d e r t o p u t t h e
d i s t r i b u t i o n on a f i n n mathematical b a s i s , and w i t h t h e hope that t h e
i n v e s t i g a t i o n would y i e l d a more s u i t a b l e c o n t r o l l a w .
A new c o n t r o l l a w has been f o m u l a t e d i n which
one law r e p l a c e s t h e two laws t h a t were r e q u i r e d p r e v i o u s l y . The new
c o n t r o l law i s s t i l l i n a p r e l i m i n a r y s t a g e . Because of t h e complexity
of t h e mathematics, most of t h e a n a l y s i s and t e s t i n g i s being done on
t h e d i g i t a l computer. Once t h e programs a r e running, a more a c c u r a t e
(DDD)
s t a t e m e n t may be made on t h e u s e f u l n e s s of t h e l a w .
(2)
AAP C l u s t e r S t r u c t u r a l Dynamics (New)
P r e l i m i n a r y bending v i b r a t i o n c h a r a c t e r i s t i c s
f o r s e v e r a l c o n f i g u r a t i o n s of t h e AAP C l u s t e r have been computed, and t h e
r e s u l t s f o r t h e complete c l u s t e r documented i n memorandum R-AERO-DD-9968. The dynamic d a t a f o r t h e CSM docked t o t h e LM/ATM were g i v e n i n
~ . r e s u l t s of a n a l y s e s of s e v e r a l o t h e r
memorandum R - A E R O - D D - ~ ~ - ~ The
c o n f i g u r a t i o n s a r e being reviewed.
(DDS)
d.
P r o j e c t Information Applicable t o Individual
Vehicles
(1)
Response A n a l y s i s of AAP-2 F i r s t F l i g h t
Stage (New)
The response a n a l y s i s of t h e AAP-2 m i s s i o n i s
being documented. The v e h i c l e c o n f i g u r a t i o n included exterior-mounted
s o l a r p a n e l s , AAP b a s e l i n e APS u n i t s , and SLA/NC j e t t i s o n r o c k e t . Aerodynamic moment c h a r a c t e r i s t i c s f o r t h i s con£ i g u r a t i o n were s u f f i c i e n t l y
high s o t h a t t h e c o n t r o l a n g l e r e q u i r e d i n t h e presence of t h e 95 p e r c e n t
winds was 8.0 degrees a t max q f o r t h e RSS bending moment c o n d i t i o n s .
Tlle c o n t r o l l a b i l i t y margin i s s a t i s f a c t o r y f o r a non-malfunction £1 i g h t ;
llowever, h i g h bending moments a r e i n c u r r e d . A t 1 0 km, 68 s e c from
1 i f t o f f , t h e bending moment ( i n c l u d i n g margin f o r f l e x i b l e body dynamics)
i s 62.5 m i l l i o n i n l b s ; a t max q , 7 3 s e c , t h e bending moment i s 61.3
m i l l i o n i n l b s . (DC)
�ATM S o l a r Panel F l e x i b i l i t y (New)
a.
A d e t a i l e d a n a l y s i s has been made of t h e f l e x i b i l i t y
of t h e ATM s o l a r p a n e l s . The e f f e c t s of frame bending, panel s h e a r ,
p i n deformation and s o l i d l u b r i c a n t deformation have been included i n
t h e a n a l y s i s . These d a t a w i l l b e i n c o r p o r a t e d i n t o t h e AAP C l u s t e r
dynamic a n a l y s i s and should be u s e f u l i n f u t u r e damping p r e d i c t i o n s .
(~D~l~ockheed)
b.
A'IM P o i n t i n g (New)
Response s t u d i e s a r e determining t h e e r r o r o b t a i n e d f o r
t h e ATM f o r v a r i o u s d i s t u r b a n c e s . A t o t a l s i m u l a t i o n of t h e CMG e l a s t i c
body c l u s t e r i s b e i n g used f o r t h e s t u d y . Two bending modes a r e
included. S i n c e r e s u l t s a r e j u s t beginning t o come i n from Computation
L a b o r a t o r y , we cannot y e t draw any c o n c l u s i o n s as t o e r r o r expected.
(DD/NO
t h~r o p )
3.
OWS
a.
P a s s i v e A t t i t u d e Control (Ref:
P- 43)
February
- March
1968,
A memo has been w r i t t e n summarizing t h e r e s u l t s of a
s o l a r panel misalignment s t u d y of t h e OWS i n t h e s t o r a g e mode. The
s t u d y i n d i c a t e s t h a t a n i n c r e a s e of t h e aerodynamic c o e f f i c i e n t s by
30 p e r c e n t can cause a maximum a n g u l a r d e v i a t i o n of a b o u t 20" from t h e
nominal p i t c h and yaw a t t i t u d e a f t e r t e n o r b i t s ; t h i s a t t i t u d e behavior
might r e q u i r e a corresponding a t t i t u d e c o r r e c t i o n by r e a c t i o n j e t s . A t
t h a t time, t h e v e h i c l e begins t o s p i n up a l o n g i t s l o n g i t u d i n a l a x i s t o
a f i n a l r a t e of approximately 0.5 d e g l s e c o r more.
The r e p o r t on t h e comparison of t h r e e s t e e r i n g laws
f o r t h e ATM SIXPAC CMG c o n t r o l system has been p u b l i s h e d . The r e p o r t
is t i t l e d " E v a l u a t i o n of S t a b i l i t y f o r Three C o n t r o l C o n f i g u r a t i o n s of
t h e ATM SIXPAC Control System," Report 'I'M-54130-185, LMSCIHREC A781369,
d a t e d A p r i l 1968. The r e s u l t s i n d i c a t e i n s t a b i l i t y of t h e Langley cont r o l law f o r some gimbal p o s i t i o n s , b u t s t a b i l i t y i s i n d i c a t e d f o r a l l
(DCAILockheed)
c a s e s f o r t h e cross-product and H-vector c o n t r o l law.
b
.
OWS O r i e n t a t i o n S t u d i e s (Ref:
February-March 1968)
Aerodynamic t o r q u e s f o r t h e X-POP o r i e n t a t i o n of t h e
OWS have been added t o t h e computer s i m u l a t i o n of t h e r o t a t i o n a l dynamics
and c o n t r o l system of t h e workshop. This was done by expanding t h e a e r o dynamic c o e f f i c i e n t s a s a t r u n c a t e d F o u r i e r s e r i e s . The s i m u l a t i o n has
a l s o been modified t o i n c l u d e t h e e f f e c t s of v e n t i n g t o r q u e s .
�S t u d i e s have been completed on deadbands, e . g . , s h i f t ,
e r r a t i c engine t h r u s t , a e r o and v e n t i n g t o r q u e s . S t u d i e s t o determine
t h e e I f e c t of launch d a t e , s u n s p o t number, and a l t i t u d e s on impulse
regiments a r e now b e i n g run.
(DD)
VII.
FLIGHT TEST ANALYSIS DIVISION
A.
Special Projects Office
1.
Saturn V
a.
F l i g h t E v a l u a t i o n Working Group (FEWG)
The launch v e h i c l e f l i g h t e v a l u a t i o n of AS-502 i s n e a r ing completion. Work on t h e 60-day e v a l u a t i o n r e p o r t has been rescheduled
t o provide f o r completion i n 74 t o 78 days. This r e v i s e d s c h e d u l e i s a
r e s u l t of t h e unusual m a l f u n c t i o n s experienced and a n e x p e d i t e d i n i t i a l
e v a l u a t i o n o r i e n t e d toward r a p i d i d e n t i f i c a t i o n of anomalies r a t h e r than
f i n a l reporting.
To d a t e , t h e F l i g h t E v a l u a t i o n Working Group has comp l e t e d t h e f o l l o w i n g AS-502 f l i g h t r e s u l t s documentation:
3-day TWX Report t o NASA Headquarters
10-day TWX Report t o NASA Headquarters
F l i g h t E v a l u a t i o n B u l l e t i n s No. 1, 2 and 3
Completed minutes of two FEWG E v a l u a t i o n meetings.
D i r e c t s u p p o r t has been provided f o r a p r e s e n t a t i o n of
AS-502 r e s u l t s t o General P h i l l i p s , t h e AS-503 Design C e r t i f i c a t i o n
Review, and on a continuous b a s i s t o t h e S a t u r n F l i g h t E v a l u a t i o n Panel
i n t h e j o i n t MSC~MSFC i n v e s t i g a t i o n of t h e AS-502 133-Second T r a n s i e n t .
b.
F l i g h t E v a l u a t i o n Panel (FEP)
O n - s i t e s u p p o r t and c o o r d i n a t i o n w a s provided under t h e
a u s p i c e s of t h e F l i g h t E v a l u a t i o n Panel (FEP) f o r t h e i n v e s t i g a t i o n of
May 26, 1968.
t h e AS-502 f l i g h t anaomaly a t 133 seconds from A p r i l 20
S t r u c t u r a l and i n s t r u m e n t a t i o n d e s i g n e n g i n e e r s from b o t h IBM ( f o r t h e
IU) and McDonnell-Douglas ( f o r t h e S-IVB) were working a t E l l i n g t o n AFB,
Texas, t h e s i t e of t h e anomaly t a s k team, d u r i n g t h a t p e r i o d . P&VE gave
i n t e r m i t t e n t o n - s i t e s u p p o r t t o t h e a n a l y s i s e f f o r t through M r . E. E. Beam
of i t s Dynamics and Loads ranch. The MSFC o n - s i t e e f f o r t was managed
-
�a n d coordinated by t h e FEP (Messrs. Graham, Lindberg and Nathan). The
MSFC t a s k was supported a t H u n t s v i l l e by v a r i o u s R-AERO, R-ASTR, R-COMP,
It-l'&VIC, I<-QUAT, and prime c o n t r a c t o r elements. A r e p o r t summarizing t h e
i-nvtst i g a t i o n w i l l be d i s t r i b u t e d i n e a r l y June 1968.
c.
Current P r o p u l s i o n Simulation Module S t a t u s
The S a t u r n Performance E v a l u a t i o n Deck w i t h the Propuls i o n S i m u l a t i o n Module (SPED-PSM) i s o p e r a t i o n a l through f i r s t S-IVB
burn o n l y . The module has been i n s t a l l e d i n the second S-IVB burn port i o n of t h e program, b u t i s n o t y e t o p e r a t i o n a l .
The SPED-PSM program has t h e following closed-loop
p r o p u l s i o n performance g e n e r a t i n g c a p a b i l i t y .
(1)
D i s p e r s i o n s i n t h r u s t and f l o w r a t e r e s u l t i n g from
d i s p e r s ions i n t h e independent p r o p u l s i o n s y s tem
parameter can be simulated
.
(2)
Engine-out and o t h e r p r o p u l s i o n system m a l f u n c t i o n s
a n d / o r f a i l u r e s can be c o n s i d e r e d .
(3)
S - I 1 and S-IVB PU system o p e r a t i o n a n d / o r malfunct i o n a r e simulated.
( 4 ) Center of g r a v i t y and moment of i n e r t i a a r e computed f o r any of t h e d i s p e r s i o n o r m a l f u n c t i o n
cases
.
S e v e r a l r e f i n e m e n t s t o SPED-PSM which i n c r e a s e t h e
a c c u r a c y of t h e s i m u l a t i o n have been made s i n c e January of t h i s y e a r .
(5)
A complete c o n t r o l f i l t e r s i m u l a t i o n has been
i n s t a l l e d i n t h e program, b u t v i r t u a l l y no
machine c o r e s t o r a g e space remains.
(6)
The c a p a b i l i t y t o c o r r e c t l y c o n s i d e r d i s c r e t e mass
l o s s e s i n t h e mass c e n t e r of g r a v i t y and moment of
i n e r t i a r o u t i n e s has been added.
(7)
I n p u t t a b l e s can be p u t i n a s a f u n c t i o n of e i t h e r
f l i g h t time o r mass l o s s , thus p r o v i d i n g a b e t t e r
s i m u l a t i o n f o r d i s p e r s i o n a n a l y s e s and m a l f u n c t i o n s .
S e v e r a l o t h e r r e f i n e m e n t s t o t h e SPED-PSM program a r e
c u r r e n t l y underway which w i l l f u r t h e r i n c r e a s e t h e accuracy of t h e simul a t i o n i n some a r e a s and w i l l a l s o d e c r e a s e t h e turn-around time f o r
both a complete p o w e r f l i g h t s i m u l a t i o n and d i s p e r s i o n a n a l y s i s .
�(8)
An improved S-IVB PU model has become a v a i l a b l e ,
This improved model w i l l be programmed and
checked o u t w i t h i n t h e n e x t few weeks.
(9)
I n i t i a l i z a t i o n l o g i c f o r performing p e r t u r b a t i o n s
i n one s t a g e w i t h o u t r e r u n n i n g t h e nominal c a s e s
f o r a l l previous s t a g e s has been developed f o r
t h e S a t u r n V t r a j e c t o r y g e n e r a t o r . This same
scheme w i l l be adapted t o t h e SPED-PSM program.
(10)
Logic f o r running t h e i n t o - o r b i t , c o a s t , and o u t o f - o r b i t v e r s i o n s of SPED-PSM back-to-back w i t h o u t
having t o come o f f t h e computer w i l l be i n s t a l l e d .
The SPED-PSM v e r s i o n completed i n January used SA-501
v e h i c l e i n f o r m a t i o n a s i n p u t d a t a . The o u t p u t from t h i s was compared
w i t h t h a t g i v e n i n t h e p r e f l i g h t p r o p u l s i o n performance p r e d i c t i o n tapes
and t h e o p e r a t i o n a l t r a j e c t o r y . The average d e v i a t i o n i n t h r u s t and
f l o w r a t e f o r each s t a g e and t h e d e v i a t i o n i n v e l o c i t y a t t h e c u t o f f of
each s t a g e were:
s - IC"'
S-I1
S-IVB
Thrus t , %
-0.76
+O. 62
-0.57
Flowrate, %
+O. 29
-0.11
+4.6
parame t e r / ~ t a g e
Velocity M / S ~ C
-15.9
-131.3
+9.6
The propuls i o n parameter comparisons a r e q u i t e good f o r
the S-IC and S - I 1 s t a g e s , b u t e n t i r e l y unacceptable f o r t h e S-IVB s t a g e .
Although t h i s problem i s n o t y e t r e s o l v e d , t h e i n s t a l l a t i o n of the
improved S-IVB PU model i s expected t o make a s i g n i f i c a n t improvement
i n t h i s comparison.
The v e l o c i t y d e v i a t i o n s n o t o n l y r e f l e c t t h e d e v i a t i o n s
i n t h e p r o p u l s i o n parameters b u t a l s o o t h e r inadequacies of t h e s i m u l a t i o n
scheme, e . g . , t h e S-IC v e l o c i t y d e v i a t i o n s (about -12.8 m/sec), inadequate
r e p r e s e n t a t i o n of c e n t e r engine decay (about -3.0 m/sec) and t h e l a c k of
c o n t r o l f i l t e r s i m u l a t i o n . The S - I 1 v e l o c i t y d e v i a t i o n s a r e c o n s i d e r a b l y
more complex b u t a r e a t t r i b u t e d t o p r o p u l s i o n parameter d e v i a t i o n s (about
+21.0 m / s e c ) , l a c k of c o n s i d e r a t i o n of t h e S-IC/S-I1 i n t e r s t a g e and launch
escape tower j e t t i s o n i n g i n t h e mass l o s s r o u t i n e (about -131.3 m/sec) and
;7'
S-IC Outboard engine c u t o f f .
48
�l s o i n t l ~ c . c c n t t r of g r a v i t y and moment of i n e r t i a r o u t i n e s (no d a t a
v a i l a b l v Tor t h e s e c f f c c t s ) and t h e l a c k of c o n t r o l f i l t e r s i m u l a t i o n .
h e S-IVB s t a g e should c u t o f f when a p r e s e t v e l o c i t y i s reached.
An
cror which allowed two d i f f e r e n t v e l o c i t y p r e s e t t i n g s t o be used f o r
le two s i m u l a t i o n s i s r e s p o n s i b l e f o r t h e e n t i r e S-IVB c u t o f f v e l o c i t y
r v i a t i o n . Another comparison w i l l be made a s soon a s t h e r e f i n e m e n t s
j r e s e n t l y underway a r e completed.
I
An RFQ has been i s s u e d . t o perform a s t u d y t o determine
t h e a c c u r a c y and adequacy of t h e SPED-PSM. Three items a r e t o be
accomplished under t h i s t a s k .
(1) E x e r c i s e t h e v a r i o u s o p t i o n s t o determine i f they
a r e working p r o p e r l y under a v a r i e t y of c o n d i t i o n s .
(2) Compare t h e e q u a t i o n s f o r t h e v a r i o u s p r o p u l s i o n
parameters w i t h t h o s e from t h e MARK s e r i e s of programs ( i f documentation
is a v a i l a b l e ) .
This w i l l g i v e a n i n d i c a t i o n of t h e adequacy of t h e
s imula t i o n .
( 3 ) Compare t h e SPED-PSM o u t p u t w i t h t h e corresponding o u t p u t from t h e p r e f l i g h t p r o p u l s i o n p r e d i c t i o n t a p e s and t h e
o p e r a t i o n a l t r a j e c t o r y from t h e s e t a p e s . This w i l l be used t o d e t e r mine t h e a c c u r a c y of t h e s i m u l a t i o n .
This s t u d y w i l l l a s t a b o u t s i x months and r e q u i r e
a b o u t 1,000 manhours of c o n t r a c t s u p p o r t .
B.
F l i g h t Mechanics Branch
1.
Saturn I B
a.
AS-2051 CSM-101 Rendezvous Miss i o n
The A S - ~ O ~ I C S M -Launch
~ O ~ Vehicle D i s p e r s i o n Analysis
Data Report has been completed. This a n a l y s i s shows the 30 F l i g h t
Performance Reserve t o be 1249 pounds. Fixed-time p a r t i a l s ( a t 7000
seconds) now being g e n e r a t e d a r e t o be completed t h e e a r l y p a r t of
June.
The Launch Vehicle O p e r a t i o n a l T r a j e c t o r y Data Report
i s a l s o complete. This document i n c l u d e s d e t a i l e d t r a j e c t o r y d a t a from
guidance r e f e r e n c e r e l e a s e t o t h e l o s s of S-IVB/IU l i f e t i m e . Under
nominal c o n d i t i o n s , t h e S-IVBIIUISC w i l l a t t a i n t h e d e s i r e d o r b i t w i t h
1874 pounds of u s a b l e p r o p e l l a n t . This i s approximately 600 pounds i n
excess of t h e FPR r e q u i r e m e n t s . These d a t a were g e n e r a t e d using a spacec r a f t weight of 36,300 pounds.
�The o r b i t a l t r a j e c t o r i e s using t h e nominal and +3a
impulses from t h e o r b i t a l s a f i n g e x e r c i s e have been generated and s u p p l i e d
t o MSC.
The Launch Vehicle Abort and A l t e r n a t e Mission document
i s s t i l l i n p r o g r e s s . A d d i t i o n a l PU f a i l u r e c a s e s , e t c . , have been
generated a s p a r t of t h i s a n a l y s i s .
The Launch Vehicle Range S a f e t y A n a l y s i s i s approximately
7 5 p e r c e n t complete. This document w i l l b e p u b l i s h e d , a l o n g w i t h t h e
a s s o c i a t e d "Cape Tape , I 1 t h e f i r s t h a l f of June.
MSFC i n p u t s i n t o t h e J o i n t O p e r a t i o n a l T r a j e c t o r y Document and a J o i n t O p e r a t i o n a l T r a j e c t o r y T a r g e t i n g Document have been
generated.
These documents w i l l be published a s soon a s MSC completes
t h e i r input.
A memorandum concerning the f eas i b i l i t y of c o n t r o l 1 ing
r e - e n t r y of t h e S-IVB s t a g e was prepared i n response t o a n a c t i o n item
a s s i g n e d a t t h e Apollo Design C e r t i f i c a t i o n Review Board Meeting.
b.
2061207 Dual Launch
The S-IB s t a g e t i l t polynomials and S-IVB s t a g e guidance
p r e s e t t i n g s have been g e n e r a t e d f o r t h i s m i s s i o n . These d a t a , documented
i n CCSD r e p o r t numbers TN-AP-68-322 and TN-AP-68-324, a r e being reviewed
and should be d i s t r i b u t e d by mid-June.
initiated.
2.
The d i s p e r s i o n a n a l y s e s f o r t h e s e v e h i c l e s have been
They a r e t o be d e l i v e r e d t o MSFC around August 1.
Saturn V
S e v e r a l computer r u n s s i m u l a t i n g two engines o u t i n t h e
S - I 1 s t a g e were made i n s u p p o r t of t h e AS-502 f l i g h t e v a l u a t i o n and
s p e c i a l i n v e s t i g a t i o n of t h e 502 anomalies.
which v e r i f i e d £1 i g h t d a t a .
These r e s u l t e d i n overspeeds
The " f i n a l " o p e r a t i o n a l t r a j e c t o r y f o r t h e BP-30 miss i o n
i s being g e n e r a t e d by in-house personnel r a t h e r than the Boeing Company.
The primary r e a s o n f o r t h i s i s t h e extremely high c o s t e s t i m a t e s s u p p l i e d
by TBC f o r t h i s e f f o r t . This approach i s a l s o being used i n t h e f i n a l
d i s p e r s i o n a n a l y s i s . The r e l e a s e of t h e t r a j e c t o r y a n a l y s i s and t h e d i s p e r s i o n a n a l y s i s i s scheduled f o r June 15 and J u l y 15, r e s p e c t i v e l y .
�c.
AS-503-D Mission
Boeing t r a n s m i t t e d a p r e l i m i n a r y o p e r a t i o n a l t r a j e c t o r y
on May 2 7 , 1968. This c o o r d i n a t i o n s h e e t w i l l be r e l e a s e d on o r about
Junc 10. The p r e l i m i n a r y document c o n t a i n s m i s s i o n o b j e c t i v e s , cons t r a i n t s , shaping g u i d e l i n e s , guidance p r e s e t t i n g s ( i n c l u d e s a "no wind"
b i a s t i l t program), t r a j e c t o r y d e s c r i p t i o n s , t r a j e c t o r y and o r b i t
summary, c r i t i c a l e v e n t sequence, a mass c h a r a c t e r i s t i c s summary, a
v e h i c l e p r o p u l s i o n c h a r a c t e r i s t i c s summary, and a t r a j e c t o r y l i s t i n g .
d.
AS-504-E Mission
P r e s e n t planning c a l l s f o r a r e l e a s e of t h e i n i t i a l
o p e r a t i o n a l t r a j e c t o r y around t h e f i r s t week i n September, w i t h t h e
f i n a l o p e r a t i o n a l t r a j e c t o r y around December 1. The d i s p e r s i o n a n a l y s i s
should be a v a i l a b l e i n e a r l y October, and t h e range s a f e t y d a t a s e n t t o
KSC around t h e end of October o r e a r l y November.
e.
O r b i t a l Debris
The S u r v i v a l and Risk Hazard Reports f o r t h e AS-503 v e h i c l e
a r e b e i n g documented and w i l l be d e l i v e r e d t o R-AERO-FM t h e f i r s t week i n
June. These r e p o r t s w i l l be reviewed b e f o r e t h e y a r e d i s t r i b u t e d t o t h e
necessary centers.
f
.
Lunar Landing Miss i o n (LLM)
A l a r g e summer e x e r c i s e of t h e q u i c k r e t a r g e t i n g mode
of o p e r a t i o n i s t e n t a t i v e l y scheduled t o b e g i n J u l y 15. A l l i n t r a c e n t e r
l i n k s between AERO, ASTR, P&VE, COMP, and I 0 ( i n c l u d i n g I-MO) a r e hoped
t o be c l o s e d . Also a d d i t i o n a l i n t e r c e n t e r l i n k s on communication v e r i f i c a t i o n wind cause check, e t c . , w i l l be e x e r c i s e d a s much a s p o s s i b l e .
Some o t h e r primary o b j e c t i v e s a r e t o i n c l u d e t h r e e launch months (probably
~ u l y ,August, and September 1969) a t l e a s t one four-day launch month, and
a look a t A t l a n t i c i n j e c t i o n s . A v e r y thorough s c a n of p o s s i b l e launch
d a t e i s planned, t h e primary i n t e n t being t o add t o our l u n a r m i s s i o n
knowledge.
g.
Current S t a t u s of S t a t i s t i c a l Analysis f o r
T r a j e c t o r y S i m u l a t i o n of S a t u r n V Vehicles
P r o g r e s s by Lockheed M i s s i l e and Space Company has been
g e n e r a l l y good on t h i s c o n t r a c t , which cons i s t s b a s i c a l l y of two modificat i o n s of t h e "SPED" deck:
(1) a s t a t i s t i c a l sampling program which i s
being d e s i g n e d , coded, and i n s t a l l e d i n t h e "SPED" deck; and (2) a
s t a t i s t i c a l computations program which i s being d e s i g n e d , coded, and
i n s t a l l e d i n t h e "SPED~!deck. The s t a t i s t i c a l sampling program i s being
�dcsigncd t o provide a random s e l e c t i o n of i n p u t parameters and t h e
s t a t i s t i c a l computations program w i l l compute mean v a l u e s , covariance
ma t r i c c s , s tandard d e v i a t i o n s , c o r r e l a t i o n c o e f f i c i e n t s , cumulative
d is t r i b u t i o n f u n c t i o n s ( p l o t s ) , median v a l u e s , and a type of con£ idence
i n ~ c r v a lf o r a l a r g e number of o u t p u t parameters. Sample runs by
Loclclieed w i t h r e s p e c t t o t h e above m o d i f i c a t i o n s a r e now being made.
C.
Tracking and O r b i t a l Analysis Branch
1.
Saturn I B
(1) P r e l i m i n a r y a c q u i s i t i o n and l o s s times were t r a n s m i t t e d t o M r . T. E . Buckley a t GSFC. M r . Buckley i s a Bendix F i e l d
Engineer s u p p o r t i n g GSFC i n Network Operations ( L e t t e r May 2, 1968).
( 2 ) Analysis has been performed and documented by
memorandum R-AERO-FT-18-68 on t h e p r e d i c t e d AS-205 S-IVB o r b i t a l decay
and 1i f e t i m e . This a n a l y s i s i n c l u d e s d i s p e r s i o n due t o k3a off-nominal
s t a g e p a s s i v a t i o n s a s w e l l a s t h e d i s p e r s i o n s due t o atmospheric
uncertainties.
(3) The t r a c k i n g and communications a n a l y s i s on t h e
A S - ~ O ~ / C S M 101 O p e r a t i o n a l T r a j e c t o r y has been completed and i s docuThis a n a l y s i s was performed
mented i n memorandum R-AERO-FT-20-68.
in-house and a l o n g w i t h t h e look a n g l e i n f o r m a t i o n g e n e r a t e d , s i g n i f i e s
an updating of p r e s e n t c a p a b i l i t i e s
.
(4) A p r e l i m i n a r y copy of t h e AS-205 look a n g l e d a t a
was s e n t t o M r . John Gurley, MSC, on a magnetic t a p e . A t t h e time t h e s e
d a t a were completed, t h e p o l a r i z a t i o n a n g l e d a t a were i n c o r r e c t . The
f i n a l look a n g l e i n f o r m a t i o n c o n t a i n s t h e c o r r e c t e d p o l a r i z a t i o n a n g l e
data.
The t r a c k i n g and communications network t o be used on
the AS-207/206 Rendezvous Mission has been s e n t t o CCSD ( L e t t e r A p r i l 5 ) .
2.
Saturn V
(1) A c q u i s i t i o n and l o s s times f o r Corona, C a l i f o r n i a ,
were t r a n s m i t t e d by TWX t o M r . Kimball of t h e Naval Weapons C e n t e r .
These d a t a were r e q u e s t e d by t h e Weapons Center t o a i d i n t e s t s of new
r a d a r equipment.
�(2) Look a n g l e time h i s t o r i e s f o r the launch phase of
AS-501 and AS-502 were r e q u e s t e d by M r . Frank S h e l t o n , GSFC. The
information was t r a n s m i t t e d by l e t t e r dated A p r i l 22, 1968.
( 3 ) Information r e g a r d i n g t h e AS-502 S-IVB s p e n t s t a g e
l u n a r - s o l a r e f f e c t s and p e r t u r b a t i o n s , a l o n g w i t h r e l a t e d r e f e r e n c e s ,
was . s e n t t o D r . Knothe, KSC, by l e t t e r dated A p r i l 19, 1968. D r . Knothe
has expressed a s t r o n g i n t e r e s t i n t h e s e 502 a n a l y s e s .
The l a t e s t TBC v e r s i o n of t h e AS-503 "D" miss i o n
t r a j e c t o r y has seemingly s a t i s f i e d t h e v a r i o u s people who r e c e i v e VHF
t e l e m e t r y d a t a . I n a d d i t i o n t o having coverage f o r t h e b u r n s , t h e f u e l
dump i s now o b s e r v a b l e b e f o r e t h e s l a n t range exceeds 4500 km.
This
range has been e s t a b l i s h e d a s t h e maximum range f o r which VHF t e l e m e t r y
d a t a can be r e c e i v e d and s t i l l be of good q u a l i t y .
3.
Apollo A p p l i c a t i o n s
a.
S a t u r n IB Workshop
(1) Decay and l i f e t i m e i n f o r m a t i o n on t h e c l u s t e r m i s s i o n was prepared f o r p r e s e n t a t i o n t o D r . von Braun on May 3rd and t o
M r . Luskin on May 1 5 t h . These d a t a were included i n M r . Deaton's
p r e s e n t a t ion.
(2) Decay and l i f e t i m e i n f o r m a t i o n on t h e c l u s t e r
m i s s i o n was p r e s e n t e d a t t h e Miss i o n Requirements Panel meeting h e l d
a t MSPC on May 22nd. We a r e now documenting t h i s l a t e s t i n f o r m a t i o n i n
a memor and um
.
(3) The use of t h e c o n s t r a i n t Generator Program was
s u p p l ied t o R-AERO-DA f o r t h e i r t imel i n e a n a l y s i s on t h e AAP-1/ 2 miss ion.
This program has demonstrated i t s v a l u e by p r o v i d i n g a n e x c e l l e n t b a s e
t o s t a r t experiment s c h e d u l i n g . The program, however, r e q u i r e s e x c e s s i v e
IBM 7094 computer time f o r long d u r a t i o n m i s s i o n s . We a r e reviewing t h e
program, and w i l l a t t e m p t t o g e t i t running on t h e 1108 system. This
should r e l i e v e some of t h e computer time problem.
(4) We a r e a t t e m p t i n g t o g e n e r a t e r e p r e s e n t a t i v e look
a n g l e s f o r As t r i o n i c s Lab f o r t h e antenna p a t t e r n s t u d i e s . We have
r e c e i v e d a p o s t - p a s s i v a t i o n v e c t o r f o r a 230 n.m. c i r c u l a r , 28.9 degree
i n c l i n a t t o n o r b i t . The f i r s t s t e p was t o determine t h e yaw and r o l l
maneuvers n e c e s s a r y f o r t h e s o l a r a r r a y s t o a c q u i r e t h e sun. This has
been done f o r t h i s p a r t i c u l a r v e c t o r . This i n f o r m a t i o n w i l l then be
i n p u t t o ~ o c k h e e d ' s look a n g l e deck.
�Wc b e l i e v e t h a t a s t u d y t o a s c e r t a i n g e n e r a l yaw
ai~tlrot l mancttvrrs a s a f u n c t i o n of time and i n c l i n a t i o n would be of
intc>rc1st. T l l i s i s now being done in-house.
b.
S a t u r n V Workshop
S u r v e i l l a n c e coverage on t h e S a t u r n V Workshop from
launch t o i n s e r t i o n (270 n.m. o r b i t ) and a 24-hour o r b i t a l p e r i o d has
been completed and i s documented i n memorandum R-AERO-FT-14-68.
These
a n a l y s e s w i l l be included i n t h e phase A documentation.
4.
General
a.
Lifetime
(1) M r . A 1 Baker of Bellcomm met w i t h M r . Paul Revels
its
and M r . Russ Pimm (LMSC) t o d i s c u s s t h e o r b i t a l l i f e t i m e program
o p t ions and capab il i t i e s
He s p e n t approximately s i x hours d i s c u s s i n g
t h e program and seemed t o be q u i t e pleased w i t h i t s o v e r a l l f e a t u r e s .
It a p p e a r s t h a t Bellcomm i s planning t o use i t much more e x t e n s i v e l y i n
miss i o n planning.
-
.
(2) I n c o n n e c t i o n w i t h our l i f e t i m e s t u d i e s , LMSC
m i s s i o n s u p p o r t has analyzed t h e decay of Echo I. Because of t h e l a c k
t h e b a l l o o n supposedly has
of knowledge of p o s s i b l e changing of C+/M
been punctured by meteors and p o s s i b l y d e f l a t e s a t lower a l t i t u d e s and
expands a t t h e h i g h e r a l t i t u d e s , a f f e c t i n g b o t h t h e drag p e r t u r b a t i o n s ,
t h e e x a c t p o s i t i o n s and v e l o c i t i e s
a s well a s the s o l a r pressure f o r c e
a r e very d i f f i c u l t t o predict.
--
--
11
I n o r d e r t o e s t i m a t e t h e l i f e t i m e of Echo I ( h e r e
e s t i m a t e " must be emphasized due t o t h e inadequate knowledge of AIM),
t h r e e runs were made. The f i r s t r u n used t r a c k i n g d a t a from SAO on
November 8 , 1967, w i t h CDA/M = 16.643 m2/kg and A/M times s o l a r p r e s s u r e
( P r ) = 0.000045 kg a s i n i t i a l c o n d i t i o n s , and i n t e g r a t e d w i t h H. W.
Small d e n s i t y model. The r e s u l t i n g impact d a t e was May 8 , 1968. The
second r u n began w i t h t r a c k i n g d a t a on May 1 0 , 1967, b u t w i t h a change i n
t h c a r e a p r e s e n t e d t o t h e s o l a r p r e s s u r e (AIM = Pr = 0.000040 ~ ~ l k g ) The
.
r e s u l t i n g impact d a t e was June 5 , 1968. The t h i r d r u n used t h e same t r a c k ~ used a
ing d a t a a s t h e second, b u t changed Pr AIM t o 0.000045 N T / ~and
c ~ A / M= 12.482 m2/kg. The r e s u l t i n g impact d a t e was June 9 , 1968.
It should be emphasized t h a t t h e s e d a t a a r e very
u n c e r t a i n because of t h e nebulous c h a r a c t e r of t h e p h y s i c a l parameters
of t h e b a l l o o n . However, based on t h e November 8 , 1967 elements, t h e
e r r o r i n our two p r e d i c t i o n s was 3 p e r c e n t and 4 p e r c e n t f o r t h e June
5 t h and June 9 t h p r e d i c t e d decay d a t e s , r e s p e c t i v e l y . These r e s u l t s
a r e v e r y encouraging.
�(3)
NORAD P r e s e n t a t i o n on T I P
The NORAD p r e s e n t a t i o n on t h e i r Tracking and Impact
P r c d i c t i o n Program g i v e n i n Washington on May 2 1 s t was q u i t e i n t e r e s t i n g .
NOKAD i s p r e s e n t l y keeping up w i t h over 1 , 3 0 0 s a t e l l i t e s i n o r b i t . Their
m i s s i o n i s t e r m i n a l decay p r e d i c t i o n , weapons s u p p o r t , s e n s o r c a l i b r a t i o n , and e a r t h model d e t e r m i n a t i o n . The p r e s e n t a t i o n c o n s i s t e d of t h e
t e r m i n a l decay p r e d i c t i o n s and how t h e y a r e performed. Two programs
a r e p r i m a r i l y involved; one i s King-Hele Decay Program which g i v e s them
e s t i m a t e d decay p r e d i c t i o n s f o r 1,300 s a t e l l i t e s i n a b o u t one minute of
computer time. This program, a n a l y t i c i n n a t u r e , uses mean o r b i t a l
elements and t h e r a t e of change of p e r i o d t o p r e d i c t decay. The program i s e s t i m a t e d t o have an accuracy of from 10-25 p e r c e n t (one sigma).
The second program, which c o n s i s t s of a s p i r a l decay technique used
over s h o r t time p e r i o d s (from 7-10 days b e f o r e i m p a c t ) , i s a v a r i a t i o n or-parameters technique and i s used up t o approximately 20 minutes
b e f o r e impact, then a Cowell i n t e g r a t i o n p r e d i c t i o n i s made t o impact.
The second program r e q u i r e s t r a c k i n g i n f o r m a t i o n t o update t h e s a t e l l i t e ' s
o r b i t a l elements; i t was s t a t e d t h a t a c c u r a t e p r e d i c t i o n s (5-10 p e r c e n t /
one sigma) could be made over a c e r t a i n time p e r i o d i f t r a c k i n g i n f o r m a t i o n
of approximately the same p r e d i c t i o n p e r i o d l e n g t h were a v a i l a b l e b e f o r e
the prediction.
I n o t h e r words, i f they had 12 hours of d a t a a r c , they
could a c c u r a t e l y p r e d i c t 12 hours ahead. I f they had 10 days of t r a c k i n g
d a t a , they could a c c u r a t e l y p r e d i c t approximately 10 days ahead. This
does n o t seem t o be a major accomplishment i n comparing t h i s t o our pres e n t c a p a b i l i t i e s . The second program uses t h e SPADATS 1966 e a r t h model
w i t h 9 zonal and 6 t h o r d e r t e s s e r a l harmonics, t h e 1966 ~ a c c h i adynamic
atmosphere mode above 120 km, and t h e 1962 U. S. Standard model below
120 km. Other atmospheric models, which i n c l u d e e f f e c t s due t o s o l a r
a c t i v i t y and geomagnetics, have n o t been e v a l u a t e d .
One of NORAD's prime s o u r c e s of t r a c k i n g informat i o n i s t h e B a l l i s t i c M i s s i l e E a r l y Warning System (BMEWS) . They have
v i r t u a l l y no t r a c k i n g i n f o r m a t i o n from t h e Southern Bemisphere and v e r y
l i t t l e below 35" l a t i t u d e . One of t h e i r prime reasons f o r t h e p r e s e n t a t i o n was t o a t t e m p t t o s o l i c i t e NASA t r a c k i n g s u p p o r t . Their "boxscore"
s i n c e June 1965, o u t of 314 TIP decays, i s a s f o l l o w s :
109 impact p r e d i c t i o n s w i t h i n +5 minutes accuracy
81 impact p r e d i c t i o n s w i t h i n k10 minutes a c c u r a c y
68 impact p r e d i c t i o n s w i t h i n +20 minutes a c c u r a c y
75 impact had v i s u a l c o n f i r m a t i o n
8 impacts have had p i e c e s r e c o v e r e d .
�These a c c u r a c i e s sound v e r y good, b u t i t must be
r cmemb e r e d t h a t they need c o n t i n u i n g t r a c k i n g i n f o r m a t i o n over the l a s t
10 days and w i t h t h i s i n f o r m a t i o n , t h e accuracy i s 5-10 p e r c e n t (one
s igma) . P r e s e n t l y , NORAD uses s e v e r a l a g e n c i e s t o confirm decay:
SAO
12 Baker-Nunn Cameras
122 moonwatch
1127th F i e l d A c t i v i t y Group
67 a i r a t t a c h e s a t embassies
NORAD Reg ions
205 i n d i v i d u a l i n s t a l l a t i o n s
A i r Weather S e r v i c e
300 a i r weather s t a t i o n s
Civilian Airlines
P i l o t s from 65 world a i r l i n e s i n 36 c o u n t r i e s
Ships a t Sea
A l l major f l e e t s and r o u t e s
Other M i l i t a r y and C i v i l i a n Sources.
A 1 though t h e p r e s e n t a t i o n was i n t e r e s t i n g from an
i n f o r m a t i o n v i e w p o i n t , t h e r e seemed t o be l i t t l e which would be of any
g r e a t h e l p t o us. S o l a r a c t i v i t y p r e d i c t i o n s a r e made o n l y 90 days i n
advance; t h u s , no h e l p t h e r e . They d i d make a p o i n t t h a t i f NASA r e q u i r e s
any s u p p o r t on monitoring any s a t e l l i t e , f o r decay purposes o r o t h e r w i s e ,
they were w i l l i n g t o cooperate and, p r e s e n t l y a t l e a s t , w i t h no c o s t t o
NASA.
.
This p r e s e n t a t i o n was coordinated by Col S c h u l h e r r
from NASA Headquarters. Approximately 20 people a t t e n d e d t h e p r e s e n t a t i o n .
Col. Baird and Col. White were t h e A i r Force o f f i c e r s i n charge of t h i s
a s p e c t of NORAD'S work.
(4) We have r e c e n t l y r e c e i v e d from D. G. King-Hele h i s
l a t e s t works i n s a t e l l i t e l i f e t i m e and atmospheric d e n s i t y . To r e c i p r o c a t e t h i s g e s t u r e , we p l a n t o send him M r . ~ l e i s c h m a n ' s and M r . ~ e v e l s '
paper which was p r e s e n t e d a t t h e 3rd N a t i o n a l Conference on Aerospace
Meteorology i n New Orleans on May 7 t h . The paper, e n t i t l e d "The I n f l u e n c ing F a c t o r s i n S a t e l l i t e O r b i t a l Decay and L i f e t i m e A n a l y s i s , " i s publi s h e d i n t h e proceedings of t h e meeting.
�D.
F l i g h t E v a l u a t i o n Branch
1.
Saturn I B
a.
AS-205
(1)
h o - ~ n ~ i n e s - o uControl
t
A s p e c i a l s t u d y of t h e c o n t r o l and m i s s i o n performance c a p a b i l i t i e s of t h e S a t u r n I B v e h i c l e w i t h l o s s of t h r u s t on
two H-1 engines i s underway by CCSD, SSR #114. This w i l l provide
i n l o r m a t i o n r e q u i r e d t o formulate a b o r t c r i t e r i a p e r t i n e n t t o crew
s a f e t y and d e a c t i v a t i o n time f o r two-engine-out a u t o m a t i c a b o r t .
Report r e s u l t s a r e expected on June 28, 1968.
(2)
I n f l i g h t Wind C a p a b i l i t y
The i n f l i g h t wind c a p a b i l i t y of t h e AS-205 v e h i c l e
f o r a non-wind b i a s e d f l i g h t program has been determined.
For a s a f e t y
f a c t o r of 1 . 4 and using a root-sum s q u a r e technique of combining t h e
e f f e c t s of v e h i c l e t o l e r a n c e s , environmental t o l e r a n c e s , wind s h e a r s , and
g u s t s , t h e v e h i c l e i s wind l i m i t e d t o 7 2 , 95 and 7 3 m/sec f o r head, t a i l ,
and c r o s s winds, r e s p e c t i v e l y .
(3)
Emergency D e t e c t i o n System (EDS)
A j o i n t MSC/MSFC document of t h e AS-205 f l i g h t
l i m i t s and a b o r t c r i t e r i a f o r a l l i d e n t i f i a b l e f a i l u r e modes has been
h e l d up pending r e s o l u t i o n by MSC of t h e launch escape v e h i c l e l i m i t s
50 s e c o n d s ) . It now a p p e a r s t h a t MSC
i n t h e e a r l y f l i g h t phase (0
w i l l r e a l i g n t h e launch escape motors t o handle s a t u r a t e d c o n t r o l s i g n a l
f a i l u r e s and withdraw launch escape v e h i c l e l i m i t s t h a t were p r e v i o u s l y
proposed of 3 d e g l s e c r a t e and 5 deg a t t i t u d e e r r o r i n p i t c h o r yaw and
15 deg r o l l a t t i t u d e e r r o r l i m i t . These c o n s t r a i n t s were r e s u l t i n g i n
some unnecessary a b o r t s .
-
2.
Saturn V
(1)
Post F l i g h t Trajectory
The p o s t - f l i g h t t r a j e c t o r i e s on t h e AS-502 launch
v e h i c l e have been e s t a b 1 i s h e d and d i s t r i b u t e d t o t h e v a r i o u s t r a j e c t o r y
u s e r s . The AS-502 t r a j e c t o r y was c l o s e t o nominal u n t i l t h e premature
c u t o f f of t h e two S - I 1 e n g i n e s . A f t e r t h i s anomaly o c c u r r e d , t h e t r a j e c t o r y d e v i a t e d s i g n i f i c a n t l y from nominal. A t S-IVB c u t o f f , t h e spacef i x e d v e l o c i t y was 48.94 m/s g r e a t e r t h a n nominal. T h i s , a l o n g w i t h a
�f l i g h t p a t h a n g l e of 0.378 deg l e s s than nominal, produced a n e l l i p t i c a l
o r b i t w i t h a n e c c e n t r i c i t y 0.0138 g r e a t e r t h a n nominal. The r e s u l t i n g
apogee of the o r b i t was 171.5 km h i g h e r than nominal, and t h e p e r i g e e
was 1 2 . 2 km l e s s than nominal. A ground command t o t h e s p a c e c r a f t t o
s e p a r a t e t h e LV/SC was g i v e n when i t was a s c e r t a i n e d t h a t t h e S-IVB
s tage f a i l e d t o r e i g n i t e .
Considerable time and e f f o r t w e r e s p e n t working w i t h
TBC t o a s s u r e t h a t the p o s t - f l i g h t t r a j e c t o r y d e l i v e r i e s t h e y made were
t e c h n i c a l l y a d e q u a t e f o r d i s t r i b u t i o n t o t h e t r a j e c t o r y u s e r s . AS-502
I t was f e l t t h a t d u p l i c a was t o be a p a r a l l e l t r a i n i n g e x e r c i s e by TBC.
t i o n of e f f o r t would be e l i m i n a t e d i f TBC d e l i v e r i e s were used a s t h e
o f f i c i a l t r a j e c t o r i e s . TBC did a n e x c e l l e n t job and f u r n i s h e d h i g h
quality trajectories.
Tracking d a t a a v a i l a b l e on AS-502 were of good
q u a l i t y . GLOTRAC S t a t i o n I d a t a and C-band r a d a r d a t a from f i v e d i f f e r e n t s i t e s were t h e primary d a t a used i n t h e p o s t - f l i g h t powered
f l i g h t t r a j e c t o r y . ODOP, Camera, and U n i f i e d S-band d a t a were a l s o
used t o judge t h e q u a l i t y of t r a j e c t o r y .
Free f l i g h t t r a j e c t o r i e s of t h e s p e n t s t a g e s were
g e n e r a t e d u s i n g t h e a c t u a l s e p a r a t i o n c o n d i t i o n s and assuming t h e o r e t i c a l
drag c h a r a c t e r i s t i c s .
The S-IC s t a g e was observed breaking up a b o u t 397
seconds range time by photographic coverage from a n a i r c r a f t . The S-IVB
s t a g e remained i n o r b i t and r e - e n t e r e d on A p r i l 26th.
The AS-502 o r b i t a l i n s e r t i o n c o n d i t i o n s and r e s u l t i n g
ephemeris up t o S-IVBISC s e p a r a t i o n were determined. Good agreement w i t h
t h e MSC-determined ephemeris and s e p a r a t i o n c o n d i t i o n s was o b t a i n e d . The
MSFC ephemeris was determined by n u m e r i c a l l y i n t e g r a t i n g t h e " b e s t e s t i mate" i n s e r t i o n c o n d i t i o n s forward t o s e p a r a t i o n (11667.8 s e c R.T.).
These i n s e r t i o n c o n d i t i o n s were based on a l e a s t s q u a r e s f i t of t r a c k i n g
d a t a (C-band) s p r e a d over t h e e n t i r e time of f l i g h t from i n s e r t i o n t o
s e p a r a t i o n . The t e l e m e t e r e d guidance v e l o c i t y d a t a were used t o develop
polynomial curve f i t s t o provide a v e n t i n g model. This model was s a t i s f a c t o r y and the b i a s e s solved f o r were i n r e a s o n a b l e agreement w i t h
l a b o r a t o r y measurements.
One i n t e r e s t i n g f a c t of t h e o r b i t a l determinat i o n was t h e u s e , f o r t h e f i r s t time, of C-band t r a c k i n g from a s h i p
(REDSTONE). The d a t a were s u r p r i s i n g l y good and provided a more r e l i a b l e
e s t i m a t e of t h e i n s e r t i o n parameters t h a n would have been p o s s i b l e o t h e r w i s e . Data d e l i v e r y was good w i t h a l l C-band t r a c k i n g r e c e i v e d by MSFC
30 hours. Low speed u n i f i e d S-band d a t a were r e c e i v e d over
within L
15 days. Analysis of t h e s e d a t a i s c o n t i n u i n g .
t e l e t y p e by L
+
+
�(2)
Pos t - F l i g h t P r o p u l s i o n Simulation
I n p r e p a r a t i o n f o r the AS-502 f l i g h t , t h e s t a g e cont r a c t o r s matched t h e p r e d i c t e d o p e r a t i o n a l t r a j e c t o r y (O.T.) on t h e i r
r e s p e c t i v e s t a g e s w i t h t h e i r p r o p u l s i o n s i m u l a t i o n programs.
A f t e r AS-502 f l i g h t , t h e urgency of s p e c i a l s t u d i e s
being performed t o v e r i f y t h e unusual performance of t h e f l i g h t delayed
t h e d e l i v e r y of p r o p u l s i o n r e c o n s t r u c t i o n t a p e s and a s s o c i a t e d w e i g h t s .
However, t h e s e a r e now i n hand. P r e l i m i n a r y a n a l y s e s on a l l s t a g e s have
been performed. The r e s u l t s of t h e s e a n a l y s e s were p r e s e n t e d t o t h e
F l i g h t E v a l u a t i o n Working Group meeting and have been submitted f o r
t h e FEWG r e p o r t .
S-IC s t a g e a n a l y s i s from t h e s i m u l a t i o n procedure
i n d i c a t e s t h a t t h e average s e a l e v e l t h r u s t was v e r y c l o s e t o p r e d i c t e d .
The a v e r a g e p r o p e l l a n t flow r a t e was almost 0.7 p e r c e n t l e s s than p r e d i c t e d and t h e s p e c i f i c impulse was almost 0.7 p e r c e n t h i g h e r t h a n p r e d i c t e d . Because of t h e a i r scoops having been removed from AS-502, a
d i f f e r e n t drag c o e f f i c i e n t was expected. A lower t o t a l drag c o e f f i c i e n t
w a s observed on AS-502.
S e v e r a l f l i g h t s w i t h t h i s same c o n f i g u r a t i o n w i l l
be r e q u i r e d t o a c c u r a t e l y determine t h e new drag c o e f f i c i e n t .
The S - I 1 s t a g e a n a l y s i s was complicated by t h e twoengine shutdown. As a r e s u l t , t h e t o t a l f l i g h t a v e r a g e s f o r l o n g i t u d i n a l
t h r u s t , v e h i c l e mass l o s s r a t e , and s p e c i f i c impulse was q u i t e d i f f e r e n t
from p r e d i c t e d . Stage performance b e f o r e t h e m a l f u n c t i o n (170 s e c ) was
v e r y c l o s e t o p r e d i c t e d . T h r u s t , p r o p e l l a n t flow r a t e and m i x t u r e r a t i o
were .43 p e r c e n t , .52 p e r c e n t and .73 p e r c e n t , r e s p e c t i v e l y , below p r e d i c t e d v a l u e s w h i l e s p e c i f i c impulse exceeded p r e d i c t i o n by 0.09 p e r c e n t .
The S-IVB s t a g e a n a l y s i s showed a n i n c r e a s e of 0.58 perc e n t and 0.34 p e r c e n t compared t o p r e d i c t e d i n t h e t o t a l a v e r a g e t h r u s t
and flow r a t e , r e s p e c t i v e l y . S p e c i f i c impulse decreased by 0.2 p e r c e n t .
The S-IVB burn time was 29.2 seconds l o n g e r t h a n p r e d i c t e d .
This deviat i o n was e x p l a i n e d by d e v i a t i o n i n i n i t i a l mass, flow r a t e , t h r u s t and
p r e c o n d i t i o n s of f l i g h t ( v e l o c i t y magnitude, e l e v a t i o n of f l i g h t , p a t h
a n g l e , and a l t i t u d e ) .
(3)
AS-502 Guidance
The major loop guidance (LVDC) t e l e m e t r y was reduced
and e d i t e d w i t h o n l y minor problems. The e d i t procedure a d e q u a t e l y
handled t h e few d a t a dropouts t h a t occurred. Hornever, time and d a t a
a t a few p o i n t s were n o t compatible. These occurred near s t a g i n g where
t h e e d i t c o n s t r a i n t s a r e r e l a x e d . Data p l o t s v e r s u s time i n d i c a t e d
erroneous t i m e s , and the processed d a t a were ad jus t e d a c c o r d i n g l y . Such
e r r o r s a r e t o be expected.
�The minor loop t e l e m e t r y (LVDA) was more d i f f i c u l t
e d i t t h a n expected. There were more than u s u a l time e r r o r s because o:
overflow of word b i t s and major loop t e l e m e t r y o v e r r i d i n g t h e LVDA out
p u t s . This i s u s u a l l y handled by e l i m i n a t i n g time p o i n t s o u t of seque
when e d i t i n g t h e d a t a . S i n c e t h e LVDA d a t a a r e sampled approximately
25 times p e r second, t h e r e i s a redundancy of d a t a . However, t h e time
e r r o r s noted on AS-502 caused t h e e l i m i n a t i o n of d a t a where r e c y c l i n g
of t h e accumulators o r c u r r e d . These problems a r e d i f f i c u l t t o a u t o m a t i c a l l y c o r r e c t . C o r r e c t i o n s were made by hand and i n p u t by c a r d s
f o r corrections t o the tape outputs.
A f t e r t h e guidance t e l e m e t r y were reduced, e d i t e d , and
d a t a d i s t r i b u t e d t o v a r i o u s c o n t r a c t o r s and MSC, a timing e r r o r was d i s covered i n t h e LVDA d a t a by comparing similar measurements w i t h t h e
d i g i t a l guidance o u t p u t s . IBM people were r e q u e s t e d t o check t h e d a t a
r e d u c t i o n procedures; t h e y were found t o b e c o r r e c t . However, a f t e r
checking t h e d a t a r e d u c t i o n program, i t was found t h a t t h e updating of
time r e f e r e n c e f o r LVDA d a t a w i t h i n a major computer c y c l e was done at:
t h e end of t h e c y c l e i n s t e a d of t h e beginning. This r e s u l t e d i n a time
b i a s approximately e q u a l t o a major computer c y c l e and v a r y i n g d u r i n g
powered f l i g h t a c c o r d i n g t o t h e n e c e s s a r y computations t o b e made. This
has been c o r r e c t e d and a n a d j u s t e d d a t a t a p e s e n t t o MSC. Some roughness
i n v e l o c i t i e s caused by i n t e r p o l a t i o n d u r i n g s t a g i n g i s b e i n g smoothed.
This c o r r e c t i o n w i l l be made i n a d d i t i o n t o t h e LVDA c o r r e c t i o n s , and
d i s t r i b u t i o n of c o r r e c t e d d a t a w i l l b e made a c c o r d i n g t o t h e PDRD
r e q u e s t s f o r t h e f i n a l s e l e c t e d guidance d a t a .
(4)
AS-502 Control
APS engine chamber p r e s s u r e d a t a i n d i c a t e s t h a t f u e l
d e p l e t e d i n module I a.t: 21,953 s e c R.T. A t 22,030 seconds, t h e yaw
a t t i t u d e e r r o r d a t a show t h a t t h e nominal +1 deg APS deadband has been
exceeded and t h a t yaw a t t i t u d e r a t e s were i n c r e a s i n g due t o l o s s of
t h r u s t i n t h i s module and LOX v e n t i n g . Fuel d e p l e t i o n occurred i n
module I11 a t 22,602 seconds. Angular r a t e s continued t o i n c r e a s e and
were approximately 7 d e g / s e c and 2.5 d e g / s e c i n yaw and p i t c h r e s p e c t i v e l y ,
by 22,800 seconds. A f t e r t h i s time, tumble r a t e s were reduced from r a d a r
and o p t i c a l t r a c k i n g d a t a which a r e a v a i l a b l e u n t i l launch +10 days.
Tumble r a t e s continued t o i n c r e a s e due t o LOX v e n t i n g u n t i l a r a t e of
180 d e g / s e c was recorded on t h e 9 t h day f o l l o w i n g launch.
b.
AS-503 (Mission D) Abort and A l t e r n a t e Mission A n a l y s i s
The AS-503 A&AM document d e l i v e r y d a t e has been changed from
June 15 t o August 1 f o r t h e . 'following r e a s o n s :
�(1) The f i r s t s e t of p r o p u l s i o n s y s t e m m a l f u n c t i o n d a t a
f u r n i s h e d by R-P&VE c o n s i s t e d of ( a ) s i n g l e S-IC and S - I 1 s t a g e engine
f a i l u r e s , and (b) S-IVB extended burns. These c a s e s were generated from
a p r e d i c t e d nominal which has s i n c e been updated.
(2) The f i r s t s e t of d a t a d i d n o t c o n t a i n dual-enginef a i l u r e c a s e s f o r S-IC and S-11 s t a g e s , S - I 1 and S-IVB PU v a l v e f a i l u r e ,
o r f a i l u r e t o LET and i n t e r s t a g e t o j e t t i s o n .
A complete s e t of new AS-503 p r o p u l s i o n system m a l f u n c t i o n
c a s e s were r e q u e s t e d from R-P&VE-P. The new d a t a , which w i l l c o n t a i n
c a s e s mentioned i n (1) and ( 2 ) , w i l l b e compatible w i t h t h e p r o p u l s i o n
system performance p r e d i c t i o n s being used i n t h e c u r r e n t AS-503 operat i o n a l t r a j e c t o r y . I n t h e i r r e p l y t o t h e r e q u e s t , R-P&VE-P s t a t e d t h a t
t h e d a t a would be a v a i l a b l e a b o u t June 1, 1968.
3.
General
a.
AZUS~/GLOTRAC
Tracking Requirements
Because of budgetary c o n s i d e r a t i o n s , t h e q u e s t i o n a r o s e
whether Azusa/GLOTRAC s u p p o r t was r e q u i r e d on f u t u r e S a t u r n v e h i c l e s .
O r i g i n a l l y i t was agreed t h a t t h i s s u p p o r t was r e q u i r e d f o r a l l R&D
S a t u r n v e h i c l e s . The R&D phase of t h e S a t u r n IB program has been comp l e t e d . Although t h e S a t u r n V E D program is n o t completed, i t is
f e l t t h a t a l l of t h e R&D o b j e c t i v e s t h a t r e q u i r e Azus~/GLoTRAc s u p p o r t
on t h e S a t u r n V have been achieved. T h e r e f o r e , a p p r o p r i a t e a c t i o n has
been i n i t i a t e d t o d e l e t e any f u t u r e MSFC requirements f o r AZUS~/GLOTRAC
support.
b.
S t a t e Vector "Update" Analysis
An agreement was made a t t h e l a s t G&P meeting t h a t t h e
f o l l o w i n g would b e done.
(1) An o u t l i n e of t h e 'Is t a t e v e c t o r " update a n a l y s i s
proposed would be s e n t through t h e Co-Chairman of t h e G&P Subpanel t o
a p p r o p r i a t e o r g a n i z a t i o n s of MSC.
(2) A r e q u e s t would b e made t o MSC f o r t h e (1) a c c u r a c i e s
a s s o c i a t e d w i t h t h e r e a l - t i m e determined s t a t e v e c t o r , and (2) t h e
a c c u r a c i e s a s s o c i a t e d w i t h t h e e x t r a p o l a t i o n of t h e r e a l - t i m e determined
s t a t e v e c t o r t o t h e p o i n t of implementation.
This procedure w i l l a i d i n making s u r e t h a t a n a l y s i s
w i l l b e made u s i n g r e a l i s t i c assumptions and o u t p u t t h e i n f o r m a t i o n
r e q u i r e d by b o t h MSFC and MSC.
�The a n a l y s i s proposal has been w r i t t e n and copies
l a v e been d i s t r i b u t e d t o v a r i o u s MSFC o r g a n i z a t i o n s f o r concurrence
b e f o r e sending i t t o MSC.
MSC w i l l probably d e s i r e s e v e r a l of t h e magnetic t a p e s
coming from t h e planned s i m u l a t i o n s t o a i d them i n t h e i r s t u d i e s .
c.
S a t u r n V 6-D T r a j e c t o r y Simulator
The e s t a b l i s h e d o b j e c t i v e of t h i s program is t o
develop a S a t u r n V t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom that
r u n s from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t phases
and t h e parking o r b i t phase t o t h e p o i n t of i n j e c t i o n i n t o a l u n a r
t r a j e c t o r y . This program i s intended t o f u l f i l l t h e R-AERO-FF 6-D
requirements f o r p r e f l i g h t and p o s t - f l i g h t s t u d i e s . The r e q u i r e d
c a p a b i l i t y i s a complete six-degrees-of-freedom t r a j e c t o r y , a closedloop guidance system, a closed-loop p r o p e l l a n t u t i l i z a t i o n system,
a closed-loop p r o p u l s i o n system, and closed-loop c o n t r o l f i l t e r s .
The s t a t u s of t h e s e c a p a b i l i t i e s i n t h e program i s as follows:
A complete
(1) Complete 6-degrees-of-freedom:
6-degrees-of-freedom t r a j e c t o r y g e n e r a t e d from guidance r e f e r e n c e
r e l e a s e through a l l powered f l i g h t and o r b i t a l f l i g h t has been s u c c e s s f u l l y implemented i n t h e SAAM-V deck. The second burn of t h e S-IVB
s t a g e and o r b i t a l f l i g h t were r u n i n t h e open-loop guidance mode w i t h
a t t i t u d e commands i n p u t .
(2) Closed-loop c o n t r o l f i l t e r s : The complete closedloop c o n t r o l f i l t e r system of t h e S a t u r n V v e h i c l e has been i n c o r p o r a t e d
i n t o t h e S a t u r n V 6-D program.
( 3 ) Closed-loop guidance: The i t e r a t i v e guidance
scheme a s implemented i n t h e onboard S a t u r n V guidance computer has
been i n c o r p o r a t e d i n t o t h e SAAM-V program i n closed loop from guidance
r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which
s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , second powered
f l i g h t , and w a i t i n g o r b i t have been prepared. The c a p a b i l i t y t o s i m u l a t e
a c c e l e r o m e t e r f a i l u r e c a s e s and t o perform v e c t o r updates t o t h e o r b i t a l
n a v i g a t i o n system has been i n c l u d e d . The programming and implementation
of t h e s e e q u a t i o n s i n t h e deck a r e i n p r o g r e s s .
( 4 ) Closed-loop p r o p u l s i o n s i m u l a t i o n system and
closed-loop p r o p e l l a n t u t i l i z a t i o n system: The closed-loop p r o p u l s i o n
s i m u l a t i o n module (PSM) i s being developed i n a p a r a l l e l 6-D program.
When d e c l a r e d o p e r a t i o n a l , t h e PSM w i l l be t r a n s f e r r e d t o t h e R-AERO-PF
�6-D program. C o n t r a c t NAS8-21160 completed on January 12, 1968 by
Operations Research, Inc. provided R-AERO-F w i t h t h e p o t e n t i a l a b i l i t y
f o r closed-loop p r o p u l s i o n s i m u l a t i o n . The PSM provided by O R 1 was n o t
considered completely u s a b l e s i n c e s e v e r a l r e f i n e m e n t s were needed.
Since t h e time t h e above d a t a were o b t a i n e d , in-house e f f o r t s t o make
t h e PSM o p e r a t i o n a l have r e s u l t e d i n t h e following:
-
(a)
Control F i l t e r s
The completed c o n t r o l f i l t e r
s i m u l a t i o n needed f o r a S a t u r n V v e h i c l e can
now be used i n c o n j u n c t i o n w i t h t h e PSM.
Machine core s t o r a g e problems i n t h i s a r e a have
been overcome.
(b)
Mass D i s c o n t i n u i t i e s
These a r e now handled by
t h e PSM a c c u r a t e l y . The PSM c o n s i d e r s t h e proper
d i s c o n t i n u i t y i n t h e c e n t e r of g r a v i t y and moment
of i n e r t i a computations.
(c)
For a more r e a l i s t i c simulaP r e s s u r i z a t i o n Tables
t i o n of d i s p e r s i o n c a s e s (engine o u t , e t c . ) , p r e s s u r i z a t i o n t a b l e s a r e now i n p u t a s a f u n c t i o n of
mass l o s s i n s t e a d of s t a g e f l i g h t time.
-
-
Before t h e PSM can be used i n s i m u l a t i o n s , t h e following must be completed:
(a)
The v a l i d i t y of t h e S-IVB p r o p e l l a n t u t i l i z a t i o n
model must b e v e r i f i e d . Some q u e s t i o n s a b o u t t h e
completeness of t h e e q u a t i o n s a r e p r e s e n t l y b e i n g
investigated.
(b)
Demonstrate t h e PSM i n a continuous s i m u l a t e d
f l i g h t from guidance r e f e r e n c e r e l e a s e through
f i n a l S-IVB burn. This i n v o l v e s e s t a b l i s h i n g
a nominal PSM g e n e r a t e d t r a j e c t o r y that w i l l corn
pare very c l o s e l y w i t h a n operational t r a j e c t o r y
(c)
Demonstrate t h e p e r t u r b a t i v e c a p a b i l i t y of t h e PS
These t h r e e items a r e i n p r o g r e s s . It a p p e a r s t h a t O R 1
may be awarded a n a d d i t i o n a l c o n t r a c t t o a s s i s t i n e l e v a t i n g t h e PSM t o
an operational status.
�BIBLIOGRAPHY
1.
G a l l i , D. H., "The Use of S t a t i s t i c s i n Guidance A n a l y s i s ,"
IN-AERO-68-2, U n c l a s s i f i e d , A p r i l 17, 1968.
2.
G i l l i s , W. T. , "Damping of Thermoelas t i c S t r u c t u r e s , I 1 U n c l a s s i f i e d ,
NASA TM X-53722, A p r i l 1 0 , 1968.
3.
E u l e r , H. C., "Solar A c t i v i t y ~ n d i c e ,"
s NASA TM X-53727, May 15, 1968.
4.
Pack, Homer, "A Method of Bending V i b r a t i o n Analysis f o r a Vehicle
w i t h F l e x i b l y Suspended Components," NASA 'IM X-53733, A p r i l 30, 1968.
5.
Harkins, S . , "Compartment Venting and Pipe Flow w i t h Beat Addition,"
NASA TM X-53734, A p r i l 23, 1968.
6.
Redus, J . R., "A D i s c u s s i o n of t h e S t a b i l i t y Requirements f o r a
Launch Vehicle F l i g h t Control System," NASA TM X-53735, May 3 , 1968.
7.
G r e g o r i a , D. G . , "A Generalized S t a t e V a r i a b l e Approach t o t h e
Problem of Absolute S t a b i l i t y , " NASA 'IM X-53736, May 6, 1968.
8.
Smith, R. E . , D. K. Weidner and C. L. H a s s e l t i n e , " O r b i t a l Environment C r i t e r i a and A p p l i c a t i o n s , " NASA TM X-53741, May 29, 1968.
�APPROVAL
ctor , Aero-As t r o d y n a m i c s L a b o r a t o r y
E . D. G e i s s l e r
D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y
DISTRIBUTION
R-AERO-DIR
Dr. G e i s s l e r
M r . Jean
Mr. B u t l e r
R-AERO-R
M r . B e a n (4)
Mrs. Hightower
R-AERO-T
Mr. M u r p h r e e
Mr. C u m i n g s
Dr. Heybey
Mr. J a n d e b e u r
Dr. K r a u s e
Mr. N a t h a n
M r . Few
M r . von P u t t k a m e r
PAO, M r . K u r t z
R-DIR, M r . W e i d n e r
MS-H, Miss J e r r e l l (3)
I-V-P,
Mr. Price
R-AERO-P
R-AERO-D
R-AERO-A
R-AERO-G
R-AERO-Y
R-AERO-F
R-AERO-X
(8)
(16)
(16)
(6)
(8)
(8)
(4)
�
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Saturn V Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000039
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: April - May 1968."
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Includes Advanced Studies Office, Aerospace Environment Division, Astrodynamics and Guidance Theory Division, Projects Office, Aerophysics Division, Dynamics and Flight Mechanics Division, Flight Test Analysis Division.
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George C. Marshall Space Flight Center
Date
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1968-06-01
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1960-1969
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Saturn Project (U.S.)
NASA space programs
Project management
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Progress reports
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Saturn V Collection
Box 27, Folder 1
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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spc_stnv_000027_000050
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http://libarchstor2.uah.edu/digitalcollections/files/original/20/987/spc_stnv_000040.pdf
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PDF Text
Text
AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
February
.March
1968
INDEX
Page
TECHNICAL AND SCIENTIFIC STAFF ...........................
.
..................................
...............................
.............
......
AEROSPACE ENVIRONMENT DIVISION ...........................
A . Atmospheric Dynamics Branch ..........................
B . Space Environment Branch .............................
C . T e r r e s t r i a l Environment Branch ........................
PROJECTS OFFICE ..........................................
ADVANCED STUDIES OFFICE
A
Systems A n a l y s i s Group
B . Mission A n a l y s i s and Astrodynamics Group
C
F l i g h t Mechanics and Performance A n a l y s i s Group
I1
.
.
.
111
.'
v.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ...............
A . Guidance Theory Branch ...............................
IV
.
B
C.
VI
.
...........................
.................................
O p t i m i z a t i o n Theory Branch
Astrodynamics Branch
.....................................
......................
.............................
AEROPHYSICS DIVISION
A
F l u i d Mechanics Research O f f i c e
B
Mechanical Design O f f i c e
C
Aerodynamic Design Branch
D
Experimental Aerophysics Branch
E
Thermal Environment Branch
F . Unsteady Aerodynamics Branch
.
.
.
............................
......................
...........................
.........................
.
.
.
...................
.............................................
.
............................................
...................
..............................................
V I I I . FLIGHT TEST ANALYSIS DIVISION ............................
A . S p e c i a l P r o j e c t s O f f i c e ..............................
B . F l i g h t Mechanics Branch ..............................
C . Tracking and O r b i t a l A n a l y s i s Branch .................
VII
DYNAMICS AND FLIGHT MECHANICS DIVISION
A . Multi-Projects
B . Saturn V
C
Saturn I B
D . S a t u r n Apollo A p p l i c a t i o n s Program
E . General
.......................................
D
.
F l i g h t E v a l u a t i o n Branch
.............................
�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
February
I.
-
March 1968
TECHNICAL AND SCIENTIFIC STAFF
1.
ODYSSEY
Some s u g g e s t i o n s f o r optimizing t h e package of e a r t h o r b i t a l
aeronomy experiments ( p a s s i v e s p h e r e ensemble, paddlewheel s a t e l l i t e ,
d e n s i t o m e t e r , and mass s p e c t r o m e t e r ) t o i n c l u d e i n j e c t i n g i n t o a n o r b i t
of high e c c e n t r i c i t y have been made. Among t h e many advantages of t h e s e
s u g g e s t i o n s would be a b e t t e r d e f i n i t i o n of t h e f r e e molecular and nearf r e e - m o l e c u l a r flow drag c o e f f i c i e n t s . However, some problems a s s o c i a t e d
w i t h implementing t h e experiment package i n t o such a h i g h e c c e n t r i c i t y
o r b i t ( E = . 8 5 , i n i t i a l p e r i g e e 170 km) a r e being c a r e f u l l y s c r u t i n i z e d .
Included i n t h e s e problems a r e t h e paddlewheel and p a s s i v e s p h e r e s a t e l l i t e aerodynamic h e a t i n g environment which c o n t i n u e s t o be d e f i n e d f o r
t h e lower p e r i g e e a l t i t u d e s . For example, a t a g i v e n s e t of i n i t i a l
c o n d i t i o n s , i n c l u d i n g i n i t i a l p o s i t i o n of p e r i g e e a t 170 km, t h e h e i g h t
of p e r i g e e has been c a l c u l a t e d t o d e c r e a s e t o a s low a s 120 km i n s e v e r a l
days by t h e l u n a r and s o l a r p e r t u r b a t i o n s . Some p r e l i m i n a r y s u r f a c e
temperatures r e l a t e d t o the p a s s i v e s p h e r e a r e b e i n g g e n e r a t e d corresponding t o t h e s e e s t i m a t e d p e r i g e e a l t i t u d e s around 120 km.
(Few)
2 . E x t e n s i v e i n v e s t i g a t i o n s were c a r r i e d o u t on t h e proper a r r a n g e ment of ground-fixed d e t e c t o r s and beams t o measure wind v e l o c i t y a t a
predetermined h e i g h t . S p e c i a l c a r e was g i v e n t o t h e e f f e c t of observat i o n a l e r r o r on t h e outcome. The work i s i n t h e f i n a l s t a g e s now; t e n e t s
and r e s u l t s w i l l be r e p o r t e d on i n a TM-X t o be w r i t t e n and published i n
t h e weeks t o come.
A n o t e i s being prepared on two-spot i s o t r o p y and t h e r e l a t i o n s h i p of two-point and two-beam covariances a s developed w i t h t h e a i d of
(Heybey)
F o u r i e r t r a n s forms.
11.
A.
ADVANCED STUDIES OFFICE
Sys terns Analysis Group
J a y H. Laue of R-P&VE-AP made a p r e s e n t a t i o n t o M r . Frank Williams,
R-AS-DIR on t h e p r e s s u r e - f e d launch v e h i c l e (PFLV) in-house s t u d y on
March 2 7 , 1968. A t t h e l a s t AS0 management b r i e f i n g on t h e PFLV (November
1 9 6 7 ) , a b a s e l i n e c o n f i g u r a t i o n was s e l e c t e d f o r in-depth a n a l y s i s d u r i n g
�Phase I of the s t u d y . The r e s u l t s of t h e Phase I s t u d y were t h e s u b s t a n c e
of t h e March 27 p r e s e n t a t i o n . Phase I r e s u l t s showed t h e b a s e l i n e conf i g u r a t i o n p r o p e l l a n t tanks t o be e x c e s s i v e l y t h i c k , t h a t geometric
s c a l i n g of s t a g e s i s n o t d e s i r a b l e , and t h e v e h i c l e was expensive.
M r . Laue then p r e s e n t e d a c a n d i d a t e f o r t h e Phase I1 c o n f i g u r a t i o n , t h e
main f e a t u r e s of which a r e c l u s t e r e d p r o p e l l a n t tanks w i t h s m a l l e r w a l l
t h i c k n e s s and commonality of hardware between s t a g e s r a t h e r than emphasis
on s c a l i n g . The proposed c o n f i g u r a t i o n has more hardware i n common
between s t a g e s than do t h e p r e s e n t T i t a n c o n f i g u r a t i o n s .
The C h r y s l e r Corporation Space D i v i s i o n (CCSD) "National Space
Booster Studytt w i l l be funded and work i s expected t o be under c o n t r a c t
w i t h i n a few days. The s t u d y i s expected t o c o n s i s t of t h e f o l l o w i n g
g e n e r a t i o n of a launch v e h i c l e spectrum t o g i v e a n i n t e g r a t e d i n c r e mental c a p a b i l i t y t o match t h e missions provided by MSFC; i n v e s t i g a t i o n
of s p e c i f i c a t i o n s f o r launch v e h i c l e d e s i g n , development and o p e r a t i o n s
t o determine what s p e c i f i c a t i o n s r a i s e c o s t s ; recommendation of s p e c i f i c a t i o n changes on p r e s e n t launch v e h i c l e s t o reduce c o s t s of p r e s e n t
systems; and a p r e s s u r e - f e d launch v e h i c l e s t u d y ( i n c l u d i n g e n g i n e s ) .
B.
Miss i o n Analys i s and As trodynamics Group
1.
S a t u r n V Workshop
A s e c t i o n e n t i t l e d " O r b i t a l Analysis" has been completed f o r
i n c o r p o r a t i o n i n t o t h e MSFC's S a t u r n V Workshop r e p o r t . The c o n t e n t of
t h i s s e c t i o n i n c l u d e s i n f o r m a t i o n p e r t i n e n t t o o r b i t a l l i f e t i m e , rendezvous -compatible o r b i t s , ground launch window, t h e sun' s i l l u m i n a t i o n
a n g l e r e l a t i v e t o t h e workshop o r b i t p l a n e , sun-synchronous o r b i t s ,
v e h i c l e a t t i t u d e , and gimbal a n g l e h i s t o r i e s .
2.
Synchronous O r b i t S t u d i e s
I n s u p p o r t of t h e AS0 "Synchronous O r b i t Study ," p r e l i m i n a r y
S a t u r n V payload c a p a b i l i t i e s t o 80, 90, 100, 110, and 120 degrees
west l o n g i t u d e hover p o i n t s and zero-degree synchronous o r b i t i n c l i n a t i o n s have been c a l c u l a t e d and t r a n s m i t t e d t o M r . Paul Thomas, R-AS.
I n r e s p o n s e t o a r e q u e s t by M r . Tidd, R-AS-OM, a spectrum of
launch v e h i c l e payloads t o a 90° West hover p o i n t f o r z e r o and 28.5"
i n c l i n a t i o n synchronous o r b i t s has been o b t a i n e d . The v e h i c l e s conT i t a n I I I C , T i t a n 1 1 I ~ / ~ g e n aA
, t l a s SLA-3A/
s i d e r e d were S a t u r n IB/SM,
Agena, A t l a s sLV- 3C/ Centaur, and TAT/DELTA/FW~.
�3.
AIAA Technology f o r Manned P l a n e t a r y Mission Meeting
M r . Bobby E l l i s o n from t h i s o f f i c e a t t e n d e d t h i s meeting on
March 4-6, 1968, i n New Orleans. A copy of t h e papers presented a r e
a v a i l a b l e i n t h i s o f f i c e f o r information and review.
4.
Unmanned P l a n e t a r y Study
A s t u d y i s underway by R-AERO-XF on t h e performance of t h e
T i t a n family of launch v e h i c l e s . The c o n f i g u r a t i o n and weight summaries have been received from R-P&VE-A on the T i t a n 111~/Centaur,
T i t a n I I ~ F I T r a n s t a g e , T i t a n I I I F / S t r e t c h e d Transtage, T i t a n IIIF/
Centaur, T i t a n IIIM, and T i t a n I I I C . These T i t a n c o n f i g u r a t i o n s and
aur
t h e spectrum
t h e Saturn V, Saturn IB/SM, and Saturn ~ ~ / ~ e n t comprise
of launch v e h i c l e s t o be used i n Unmanned P l a n e t a r y Study.
A d a t a package was prepared f o r M r . Frank Williams, R-AS-DIR,
f o r use a t t h e OSSA "Planetary Working Group" on A p r i l 3 , 1968. The
P l a n e t a r y Working Group i s headed by M r . Don Hearth of OSSA. This
package c o n s i s t e d of background and c u r r e n t m a t e r i a l being generated
i n t h e AS0 Unmanned P l a n e t a r y Study.
5.
In-House Study "Application of Voyager S p a c e c r a f t t o Venus
and J u p i t e r M i s s ions"
Although the e s s e n t i a l s p a c e c r a f t and a s t r i o n i c s d a t a have
n o t y e t been received from R-P&VE-A and R-ASTR-A, documentation of t h e
s tudy has begun.
C.
F l i g h t Mechanics and Performance Analys is Group
The major a c t i v i t y of t h i s group has been t o support t h e f i n a l
a n a l y s i s of t h e Phase A s t u d y of t h e Saturn V Workshop. Documentatic
of t h i s work should soon be completed. Data have been generated f o r
t h e two-s tage S a t u r n V, including performance, instantaneous impact
p o i n t s , impact zones, and t r a j e c t o r y shaping t o modify t h e S-IC impa
zone. Data of t h i s same type have a l s o been generated f o r t h e l o g i s
v e h i c l e s including both t h e T i t a n 111 and t h e S-IB.
A program i s being modified f o r t h e CDC 3200 computer t o enabl
t h i s group t o respond more q u i c k l y t o r e q u e s t s f o r raw f l i g h t mecha
data.
On February 1, t h e Mission Analysis Task Group met a t NASA He;
q u a r t e r s . M r . Goldsby from t h i s o f f i c e provided information on pe
formance, range s a f e t y and a b o r t problems of t h e Saturn V Workshop
�On February 15, M r . Goldsby presented t h e continued work of t h i s
o f f i c e on t h e range s a f e t y and a b o r t problem a t a meeting of t h e OWS
Task Group a t MSC.
M r . Madewell and M r . Becker of R-AS0 made a p r e s e n t a t i o n t o
M r . Matthews, NASA Headquarters, on March 7 and 8, and t o t h e Thompson
Committee on March 12 on t h e S a t u r n V Workshop. On March 1 3 , M r . Becker
and M r . Madewel 1 reviewed t h e r e s u l t s of t h e i r p r e s e n t a t i o n s f o r members
of t h e MSFC t a s k group. They r e p o r t e d that t h e i r p r e s e n t a t i o n s t o
M r . Matthews and t o t h e Thompson Committee r e s u l t e d i n no major d e c i s i o n s and t h a t p o s i t i v e d i r e c t i o n s f o r c o n t i n u i n g t h e e f f o r t were n o t
provided. They a l s o s t a t e d t h a t M r . Matthews d i d n o t f e e l t h a t a l l
p o s s i b l e a l t e r n a t i v e s l e a d i n g t o a "C" type of c o n f i g u r a t i o n have been
d e r i v e d and t h a t he does n o t want t o c o n s t r a i n any o p t i o n s a t t h i s time.
M r . Becker and M r . Madewell r e p o r t e d t h a t M r . Matthews d i s c u s s e d a
s p e c i f i c concept t h a t tends t o be more advanced t h a n "B", b u t l e s s
The comments a t t h e MSFC meeting on t h e 1 3 t h
advanced than "C".
'revealed t h a t no major d e c i s i o n s can be expected on t h e S a t u r n V Workshop (1) u n t i l t h e Thompson Committee has f i n a l i z e d t h e i r r e p o r t , (2)
u n t i l t h e consequences of t h e p r e s e n t budgetary e x e r c i s e s a r e r e a l i z e d ,
and ( 3 ) u n t i l t h e Hideaway meeting i s h e l d . A subsequent meeting on
March 29 w i t h R-ASA personnel r e s u l t e d i n n o t h i n g of consequence.
111, AEROSPACE ENVIRONMENT DIVISION
A.
Atmospheric Dynamics Branch
1.
CPS-9 Radar/Thunderstorm Study a t MSFC During 1968
The CPS-9 weather r a d a r l o c a t e d a t t h e Atmospheric Research
F a c i l i t y (Bldg. 4614) w i l l b e used by R-AERO-Y t o s t u d y l o c a l thunderstorm development, motion, and a s s o c i a t e d s u r f a c e wind c o n d i t i o n s i n
t h e s p r i n g and summer of 1968. Data and i n s t r u m e n t a t i o n requirements
f o r t h i s s t u d y have been s p e c i f i e d i n memorandum R-AERO-YE-129-68, "CPS-9
~ a d a r / T h u n d e r s t o r m Study a t MSFC During 1968." The p r e p a r a t o r y work
n e c e s s a r y f o r i n i t i a l d a t a a c q u i s i t i o n f o r S a t u r n V ground wind problems
has begun, and t h e p r o j e c t is expected t o be i n o p e r a t i o n as planned.
2.
Environmental T e s t s of Jimsphere and Rose Type Balloons
M r . John W. Kaufman and M r . Dennis W. Camp v i s i t e d t h e D-4 s i t e
of E g l i n A i r Force Base, F l o r i d a , t o p a r t i c i p a t e i n f i e l d t e s t s of t h e
Jimsphere and v a r i o u s Rose-type b a l l o o n s used t o a c q u i r e upper atmosp h e r i c wind p r o f i l e d a t a . These t e s t s were performed d u r i n g March 1968.
M r . John Wright of AFCRL, t h e t e s t d i r e c t o r , i s r e s p o n s i b l e f o r e v a l u a t i n g t h e r e s u l t s of t h e s e f i e l d t e s t s . The f o l l o w i n g types of b a l l o o n s
were used:
�- AFCRL'S s t a n d a r d 40-inch d i a m e t e r , 8-gore
B - a 40-inch d i a m e t e r , 4-gore (shaped), Rose
Type A
Type
Rose.
without
the b u i l t - i n corner r e f l e c t o r .
Type C
-a
Type D
- MSFC'S
40-inch d i a m e t e r , 4-gore (shaped), Rose cont a i n i n g a corner r e f l e c t o r .
2-meter ~ i m s p h e r e .
These t e s t s were conducted f o r t h e f o l l o w i n g r e a s o n s :
a.
To determine f u r t h e r t h e e r r o r s i n f i n e - s c a l e winds by
o b t a i n i n g more d u a l - t r a c k d a t a i n h i g h wind f i e l d s .
b.
To determine if advance Rose d e s i g n s can be t r a c k e d t o
g r e a t e r d i s t a n c e s and lower a n g l e s t h a n t h e s t a n d a r d Rose.
c.
To check t h e newer r a p i d - i n f l a t i o n v a l v e and i t s e f f e c t on
Rose performance .
d.
To compare some Jimspheres w i t h t h e Rose.
M r . Moses Sharenow of t h e F o r t Monmouth S i g n a l Corp L a b o r a t o r i e s
(Code: AM SEL-BL-TE) w a s a t t h e D-4 s i t e d u r i n g t h e week of March 1 0 t h
t o w i t n e s s t h e f i e l d t e s t s . M r . Sharenow, who is r e s p o n s i b l e f o r s t a n d a r d i z i n g t h e Jimsphere as r e q u e s t e d by R-AERO-Y, p l a n s t o review t h e
r e s u l t s of t h e s e t e s t s . The s t a n d a r d i z i n g of t h e Jimsphere w i l l depend
l a r g e l y on M r . sharenow's o p i n i o n of t h e s e t e s t s and t h e t e s t r e s u l t s .
M r . Sharenow expressed d i s p l e a s u r e i n t h e way t h e t e s t s were b e i n g
conducted. The primary r e a s o n f o r t h i s d i s p l e a s u r e was t h a t M r . Sharenow
d i d n o t b e l i e v e t h e AFCRL people were i n t e r e s t e d i n p r o v i d i n g him w i t h
i n f o r m a t i o n he needed t o perform h i s r e s p o n s i b i l i t y of s t a n d a r d i z i n g t h e
Jimsphere.
For t h e same r e a s o n , M r . Kaufman and M r . Camp were n o t comp l e t e l y pleased w i t h the t e s t s .
M r . Kaufman and M r . Camp a l s o v i s i t e d KSC t o d i s c u s s v a r i o u s
problems r e l a t e d t o t h e a c q u i s i t i o n of lower and upper atmospheric d a t a
i n regard t o r o u t i n e d a t a a c q u i s i t i o n , s p e c i a l research t a s k s , the
launch of S a t u r n v e h i c l e s , e t c .
3.
F a s t Response Anemometer
Twenty-five p r o p o s a l s were r e c e i v e d i n r e p l y t o a n RFP f o r
t h e development of a f a s t response anemometer. This anemometer w i l l be
used t o o b t a i n d a t a f o r f r e q u e n c i e s > 1 cps t o be used i n s e l e c t e d
s t r u c t u r a l r e s p o n s e s t u d i e s and aerodynamic s c a l i n g a n a l y s i s . The
proposals have been e v a l u a t e d and a c o n t r a c t o r t e n t a t i v e l y s e l e c t e d .
�N e g o t i a t i o n w i t h t h e p r o s p e c t i v e c o n t r a c t o r should t a k e p l a c e soon. I f
t h e p r o s p e c t i v e c o n t r a c t o r a g r e e s t o meet c e r t a i n c o n d i t i o n s added t o
t h e proposed development, work should begin on t h e anemometer w i t h i n a
few weeks
.
4.
A n a l y s i s of Atmospheric Turbulence from FPS-16 ~ a d a r l ~ i m s p h e r e
Data (NASA C o n t r a c t NAS8-21331)
The purpose of t h i s c o n t r a c t w i t h Meteorology Research, I n c . ,
i n i t i a t e d i n February 1968, i s t o determine t h e c a p a b i l i t y of t h e FPS-16
r a d a r l ~ i m s p h e r esystem t o d e t e c t c l e a r a i r t u r b u l e n c e (CAT). The cont r a c t o r has r e c e i v e d a i r c r a f t and Jimsphere d a t a f o r e l e v e n c a s e s of
CAT observed over Wallops I s l a n d d u r i n g December 1967. I n a d d i t i o n , we
w i l l r e c e i v e seven c a s e s of t u r b u l e n c e f o r t h e month of February 1968
when t h e d a t a become a v a i l a b l e . I f i t is demonstrated t h a t t h e FPS-16
r a d a r l ~ i m s p h e r ewind s e n s i n g system i s capable of d e t e c t i n g CAT, t h e n
i t w i l l b e p o s s i b l e t o develop a g l o b a l CAT climatology.
This informat i o n i s u r g e n t l y needed by v a r i o u s government a g e n c i e s , t h e armed f o r c e s ,
and commercial a i r l i n e s . A t t h e p r e s e n t time, CAT d a t a a r e o b t a i n e d by
instrumented a i r c r a f t , which a r e expensive t o o p e r a t e and m a i n t a i n and
a r e s u b j e c t t o o p e r a t i o n a l c o n s t r a i n t s . These f a c t o r s a c c o r d i n g l y l i m i t
t h e q u a n t i t y of d a t a a v a i l a b l e t o perform s t a t i s t i c a l a n a l y s e s . On t h e
o t h e r hand, t h e Jimsphere wind d e t e c t o r is r e l a t i v e l y cheap, and t h e r e
a r e v i r t u a l l y no o p e r a t i o n a l c o n s t r a i n t s . This means t h a t a l a r g e
q u a n t i t y of d a t a can be o b t a i n e d i n a s h o r t p e r i o d of time and t h a t a
CAT c l i m a t o l o g y could be developed w i t h i n t h e n e x t f i v e y e a r s i f t h e
c u r r e n t s t u d i e s show t h a t adequate e n g i n e e r i n g d a t a may be d e r i v e d from
t h e system.
5.
Real Time Anemometer Data t o HOSC
Real-time wind v e l o c i t y p r o f i l e d a t a w i l l be t r a n s m i t t e d t o
HOSC f o r a l l f u t u r e S a t u r n launches. This i n c l u d e s d a t a from t h e two
r e f e r e n c e h e i g h t anemometers a t t h e 60-foot (18.3m) l e v e l and winds
from a t o p t h e LUTS o r s e r v i c e s t r u c t u r e , depending on t h e launch pad
b e i n g used. Such d a t a w i l l b e r e c e i v e d from LC37B, 39A, and 39B, b u t
n o t from LC34 u n l e s s i t i s decided t h a t LC34 w i l l be used t o launch
f u t u r e Saturn vehicles.
6.
F i n a l Report on C o n t r a c t NAS8-21138 w i t h NAR
The f i n a l r e p o r t , "Wind F i e l d A n a l y s i s f o r C a n t i l e v e r Loads,"
has been r e c e i v e d from North American Rockwell C o r p o r a t i o n , Downey,
C a l i f o r n i a ; Ben U j i h a r a was t h e p r i n c i p a l i n v e s t i g a t o r . The r e p o r t
Wind d a t a
w i l l be published a s a NASA CR and d i s t r i b u t e d by R-AERO-Y.
from t h e 500F t e s t s were used t o i l l u s t r a t e pad wind-flow c o n d i t i o n s
and flow a b o u t t h e ~ ~ T I V e h i c l e .
�7.
Reduction of Meteorological Tower Data by NWRC
M r . John Kaufman (R-AERO-YE/MSFC/NASA),
M r . Paul Harness
(R-COMP-RRP/MSFc/NASA), and M r . L e s t e r Keene (IN-DAT-P/KSC/NASA) v i s i t e d
t h e N a t i o n a l Weather Records Center (NWRC) of ESSA a t A s h e v i l l e , North
C a r o l i n a , on February 8 , 1968, t o d i s c u s s d a t a r e d u c t i o n techniques and
problems r e l a t e d t o reducing NASA's 150-meter m e t e o r o l o g i c a l tower d a t a .
NWRC is r e s p o n s i b l e f o r reducing t h e d a t a t h a t are recorded on paper
s t r i p c h a r t s , a c c o r d i n g t o t h e scope of work under Government Order No.
H-13207A. S i x t e e n months (December 1965 through March 1967) of t h e s e
m e t e o r o l o g i c a l tower d a t a have been reduced and made a v a i l a b l e t o
R-AERO-Y f o r formal a n a l y s e s . Although t h e d a t a - r e c o r d i n g t e c h n i q u e s
a t t h e tower f a c i l i t y have g r e a t l y improved s i n c e t h e f i r s t few weeks
of i t s o p e r a t i o n , v a r i o u s d a t a - r e c o r d i n g problems s t i l l e x i s t . With
t h e c o o p e r a t i o n of KSC (Mr. Keene), R-AERO-Y/MSFC,and NWRC p e r s o n n e l ,
t h e s e problems should be e l i m i n a t e d .
8.
Recent Reports on NASA's 150 m M e t e o r o l o g i c a l Tower F a c i l i t y
Two r e p o r t s have r e c e n t l y been made a v a i l a b l e on NASA'S 150 m
M e t e o r o l o g i c a l Tower l o c a t e d a t KSC, F l o r i d a :
(1) GP-465 e n t i t l e d ,
"Meteorological Measuring and Recording Equipment D e s c r i p t i o n , C a l i b r a t i o n and Maintenance Procedures f o r NASA's 150 m M e t e o r o l o g i c a l Tower
F a c i l i t y , Kennedy Space C e n t e r , F l o r i d a , " dated February 1 5 , 1968;
and ( 2 ) NASA TM X-53699 e n t i t l e d , "NASA's 150-Meter M e t e o r o l o g i c a l Tower
Located a t t h e Kennedy Space Center, F l o r i d a , " d a t e d J a n u a r y 1958
(Revised) . I 1 Copies of t h e s e r e p o r t s may b e o b t a i n e d by c o n t a c t i n g
R-AERO-YE, Attn: John W. Kaufman (876-6392).
B.
Space Environment Branch
1. The continued in-depth a n a l y s e s of t h e e i g h t thermosphere probes
launched d u r i n g t h e f i r s t q u a r t e r of 1967 has g e n e r a t e d a d d i t i o n a l
i n f o r m a t i o n a b o u t t h e d i u r n a l v a r i a t i o n of b o t h t h e n e u t r a l and charged
p o r t i o n s of t h e e a r t h ' s upper atmosphere i n t h e "ignorosphere" (90-140 km)
r e g i o n . This i n f o r m a t i o n i s being combined w i t h t h e r e s u l t s of c u r r e n t
s t u d i e s t o deve op improved 10.7 cm s o l a r f l u x and geomagnetic index
(Kp) p r e d i c t i o n s i n t h e development of a r e f i n e d model of t h e upper
atmosphere.
2. I n e s t a b 1 i s h i n g t h e o r b i t a l n a t u r a l environment c r i t e r i a f o r
t h e AAP-1 and -2 m i s s i o n s , i t became e v i d e n t t h a t a d e t a i l e d time prof i l e o f t h e d e n s i t y that could be expected would be of v a l u e i n c u r r e n t
v e h i c l e motion and torque accumulation a n a l y s e s . A time p r o f i l e i s
being developed using ~ a c c h i a ' s " S t a t i c D i f f u s i o n Model" w i t h 10.7 cm
s o l a r f l u x and Kp i n d i c e s that e x i s t e d i n October 1960, a time p e r i o d
�d u r i n g which t h e s o l a r a c t i v i t y was a t t h e same l e v e l as t h a t p r e d i c t e d
f o r t h e AAP-1 and - 2 m i s s i o n s using c u r r e n t p r e d i c t i o n techniques and
C u r r e n t p r e d i c t i o n techniques cannot provide t h e
miss i o n guide1 i n e s
amount of d e t a i l r e q u i r e d t o c o n s t r u c t t h i s p r o f i l e . Work has begun on
a s i m i l a r p r o f i l e f o r t h e 56-day m i s s i o n of AAP-3 and -4.
.
3. A p r e l i m i n a r y d r a f t of t h e " O r b i t a l Environment C r i t e r i a monograph b e i n g produced f o r OART has been completed. The document c o n t a i n s
a b r i e f review of d a t a a c q u i s i t i o n and modeling t e c h n i q u e s , a s w e l l as
a d e t a i l e d d i s c u s s i o n of ~ a c c h i a ' s" S t a t i c D i f f u s i o n Model" and how i t
should be a p p l i e d i n v e h i c l e development programs and a s s o c i a t e d
ana 1ys e s
.
4. P r e d i c t e d v a l u e s of n a t u r a l environmental parameters a t o r b i t a l
a l t i t u d e s f o r t h e 1972-1975 time frame were provided t o t h e Advanced
Systems O f f i c e f o r use i n t h e i r S a t u r n IB and S a t u r n V launched workshop
analyses.
5 . Work was begun on e s t a b l i s h i n g a n o r b i t a l d e t e r m i n a t i o n program
t o b e used i n f u t u r e a n a l y s e s f o r d e r i v i n g atmospheric d e n s i t y v a l u e s
from t h e o r b i t a l decay of s a t e l l i t e s . These v a l u e s w i l l t h e n be used i n
c o n j u n c t i o n w i t h t h e r e s u l t s of our rocket-launched probe measurements
i n c o n s t r u c t i n g a r e f i n e d model of t h e upper atmosphere.
6. A major r e v i s i o n t o TM X-53521, "Space Environment C r i t e r i a
G u i d e l i n e s f o r Use i n Space Vehicle Development, 1967 Revision," i s
This r e v i s i o n w i l l be a j o i n t AERO-SSL e f f o r t w i t h t e c h n i c a l
underway.
i n f o r m a t i o n on e l e c t r o m a g n e t i c r a d i a t i o n , r a d i a t i o n , and meteoroids being
provided by SSL. The r e v i s i o n should be published t h i s summer.
7. The h i s t o r i c a l Geophysical Data Tape has been updated. Master
f i l e No. 2 now c o n t a i n s d a i l y , 27-, 54-, and 81-day running mean, monthly
mean, and 12-monthly mean v a l u e s of b o t h t h e 10.7 cm s o l a r f l u x and t h e
Zurich s u n s p o t numbers, a s w e l l a s t h r e e h o u r l y e q u i v a l e n t p l a n e t a r y
amplitude, a p , v a l u e s converted from published geomagnetic a c t i v i t y , Kp,
v a l u e s . Data on t h i s t a p e a r e l i s t e d by modified J u l i a n days, day of
y e a r , and d a t e .
8. Work i s c o n t i n u i n g on d e f i n i n g a compatible complement of
experiments f o r t h e Odyssey p r o j e c t . S e v e r a l i t e r a t i o n s have developed
a s e t of i n s t r u m e n t a t i o n t h a t w i l l provide measurements of t h e composit i o n and d e n s i t y of t h e n e u t r a l atmosphere, t h e thermal and momentum
accommodation c o e f f i c i e n t s , t h e f r e e - and n e a r - f r e e d r a g c o e f f i c i e n t s ,
and i n f o r m a t i o n concerning t h e shape of t h e e a r t h .
�9. Work i s c o n t i n u i n g on r e f i n i n g models of t h e atmospheres of
Venus, Mars, and Mercury f o r i n c l u s i o n i n t h e f o u r t h coming r e v i s i o n
t o TM X-53521.
A m a j o r i t y of t h e e f f o r t i s on Venus u s i n g t h e new
Mariner and Venera d a t a o b t a i n e d from the open l i t e r a t u r e .
10. S e v e r a l s t a t i c t e s t f i r i n g s have been monitored by t h e ionos p h e r i c phase p a t h sounding network. One problem now r a p i d l y becoming
c r i t i c a l is t h e backlog of unreduced d a t a which a r e accumulating.
Although t h e A i r Force i n Rome, New York, i s reducing t h e d a t a t a p e s
a t no c o s t t o NASA, t h e p r i o r i t y g i v e n t o t h i s d a t a r e d u c t i o n i s s o
low, t h e r e i s seldom s u f f i c i e n t computer time t o reduce t h e d a t a . A
t r i p i s planned t o Rome, New York, and t h e Avco-Boston p l a n t i n t h e
n e a r f u t u r e t o t r y t o d e a l w i t h t h e problem. The MSFC swept frequency
ionos onde i s now o p e r a t i o n a l and is providing ionograms b e f o r e , d u r i n g ,
and a f t e r s t a t i c t e s t f i r i n g s .
11. An u n s o l i c i t e d p r o p o s a l has been r e c e i v e d from D r . J . B.
B l i z a r d of t h e Denver Research I n s t i t u t e t o update and extend h e r 120day s o l a r f l a r e p r e d i c t i o n technique. Funding i s being sought f o r t h i s
work.
C.
~ e r r e tsr i a l Environment Branch
1.
The f o l l o w i n g o f f i c e memos have been i s s u e d :
a . R-AERO-YT-11-68, "A S t a t i s t i c a l Anal ys i s of t h e 'Earth' s
Atmosphere f o r a S e l e c t e d Geographic Area," d a t e d February 9 , 1968.
b . R-AERO-YT-17-68, "Ground Wind Risk Levels f o r Apollo 6
(AS-502) f o r One-Hour Exposure f o r Each Hour During March and A p r i l , "
d a t e d March 6 , 1968.
c . R-AERO-YT-18-68,
d a t e d March 6, 1968.
"Additional Atmospheric Moisture Values , I 1
d . R-AERO-YT-25,68, "Some Peak Ground Wind R i s k Levels f o r
Apollo 6 (AS-502) f o r One-Hour Exposure d u r i n g MSS Removal," dated
March 25, 1968.
e . R-AERO-YT-27-68, "Standard D e v i a t i o n s of P r e s s u r e , Temperat u r e , and Density w i t h Respect t o t h e P a t r i c k Reference Atmosphere 1963,
t o 120 Krn A l t i t u d e , " dated A p r i l 4, 1968.
A c o n t r i b u t i o n t o t h e Research Achievements Review, Volume 11,
Report No. 10, "A S t a t i s t i c a l A n a l y s i s of Winds f o r Aerospace Vehicle
Design, Mission Planning, and Operations , I 1 p r e s e n t s s e v e r a l s t a t i s t i c a l
concepts w i t h examples.
�2.
Contracts
a.
A l l i e d Research A s s o c i a t e s , I n c . , Concord, Mass.
( C o n t r a c t NAS8-21040)
The f i n a l r e p o r t and t h e b a s i c s t a t i s t i c s f o r t h e World-Wide
Cloud Cover Study f o r AAP m i s s i o n a n a l y s i s have been d e l i v e r e d . Computer
programs t o e n a b l e u s t o u s e t h e cloud s t a t i s t i c s i n m i s s i o n s i m u l a t i o n
s t u d i e s a r e b e i n g developed in-house.
b.
U n i v e r s i t y of Georgia, Department of S t a t i s t i c s
( C o n t r a c t NAS8-11175)
We have r e c e i v e d a n i n t e r i m t e c h n i c a l r e p o r t e n t i t l e d "The
Use of P r i o r I n f o r m a t i o n i n Determining Confidence I n t e r v a l s on Success
P r o b a b i l i t i e s , " by F. R u s s e l l Helm.
c.
Lockheed-Huntsville
The c o n t r a c t o r compared t h e f o l l o w i n g t h r e e methods t o
determine t h e parameters of F i s h e r - T i p p e t t Type I d i s t r i b u t i o n from a
s t a t i s t i c a l sample of extremes:
(1) Gumbells method of moments, ( 2 )
~ i e b l e i n ' smethod, and (3) method of maximum l i k e l i h o o d . The a c c u r a c y
and e f f i c i e n c y of t h e s e methods i n e s t i m a t i n g t h e parameters depend on
sample s i z e and t h e parameter. A computer program was devised which
w i l l be a u s e f u l t o o l i n t h e a n a l y s i s of extreme v a l u e s t a t i s t i c s .
This o f f i c e has a requirement f o r f i t t i n g t h i s d i s t r i b u t i o n f u n c t i o n
t o many samples.
3.
In-House Tasks
a . Data a r e being produced t o b e t t e r d e f i n e t h e p r o b a b i l i t y
of e a s t e r l y winds f o r t h e AS-205 and AS-503 e a r l y a b o r t problems.
b
.
Ground Wind I n v e s t i g a t i o n s
Considerable e f f o r t has been devoted t o e s t a b 1 i s h i n g u n i f i e d
exposure p e r i o d p r o b a b i l i t i e s f o r ground winds. An e x t e n s i o n of extreme
v a l u e s t a t i s t i c a l techniques proves t o produce cons i s t e n t r e s u l t s f o r t h e
r i s k of exceeding wind peak speed v a l u e s . The r e s u l t s of t h i s i n v e s t i g a t i o n a r e u r g e n t l y needed by KSC f o r r e d e s i g n of LUT p l a t f o r m s , and by
MSFC f o r o p e r a t i o n s and m i s s i o n planning.
�c . S e v e r a l i n v e s t i g a t i o n s have been completed and the following r e p o r t s a r e being prepared:
(1)
Thunderstorm P e r s i s t e n c e f o r Cape Kennedy.
(2)
A u t o c o r r e l a t i o n s f o r Winds A l o f t over Cape Kennedy.
(3)
Winds A l o f t Exceedance P r o b a b i l i t i e s f o r Mission Planning.
( 4 ) Winds A l o f t C o n d i t i o n a l P r o b a b i l i t i e s f o r Mission Planning.
IV.
(5)
Exceedance P r o b a b i l i t i e s f o r Peak Ground Winds.
(6)
E s t i m a t i o n s i n Extreme Values.
PROJECTS OFFICE
1.
S a t u r n I B and V EDS
a.
High Q Abort Problem
For s e v e r a l months MSFC has been a n a l y z i n g t h e problem of
i n a b i l i t y t o w i t h s t a n d t h e l o a d s d u r i n g a l l engine shutdown f o r a b o r t
d u r i n g t h e max q r e g i o n (60 t o 110 seconds) f o r S a t u r n I B and V. During
a b o r t , t h e compression l o a d s being a p p l i e d by t h e engine t h r u s t a r e
suddenly l o s t , r e s u l t i n g i n i n c r e a s i n g c r i t i c a l t e n s i o n l o a d s . Under
c e r t a i n m a l f u n c t i o n s t h e L / V exceeds t h e s t r u c t u r a l c a p a b i l i t y i n l e s s
than - 5 seconds a f t e r a b o r t i n i t i a t i o n . I t is p o i n t e d o u t t h a t t h e CM/SM
p h y s i c a l s e p a r a t i o n occurs a b o u t . 2 seconds a f t e r a b o r t i n i t i a t i o n . MSFC
has been a t t e m p t i n g t o meet a n MSC s p e c i f i e d c r i t e r i a of a b o u t a 300-foot
s e p a r a t i o n d i s t a n c e between t h e a b o r t CM and L / V b e f o r e breakup. This
r e q u i r e d a t l e a s t 2 t o 3 seconds s e p a r a t i o n time and was t o a s s u r e < 6 . 1
p s i o v e r p r e s s u r e on t h e CM a f t e r a n e x p l o s i o n , which was assumed t o occur
a t L/V breakup. During t h e l a s t Crew S a f e t y Panel Meeting, MSC pres e n t e d some p r e l i m i n a r y r e s u l t s of t h e l a t e s t e x p l o s i o n s t u d i e s which
i n d i c a t e d t h a t t h e r e q u i r e d s e p a r a t i o n d i s t a n c e f o r S a t u r n I B was n o t s o
g r e a t a s e a r l i e r s p e c i f i e d . The most i n t e r e s t i n g and important a s p e c t of
t h e r e v i s e d d a t a is t h a t , f o r a l t i t u d e s corresponding t o and above t h e
max q r e g i o n where t h e problem e x i s t s , t h e o v e r p r e s s u r e c r i t e r i a < 6 . 1
p s i can b e met w i t h v i r t u a l l y z e r o s e p a r a t i o n d i s t a n c e r e q u i r e d between
t h e a b o r t e d CM and L / V b e f o r e L / V breakup. This means t h a t t h e S a t u r n I B
problem has disappeared based on t h e r e v i s e d e x p l o s i o n c r i t e r i a d a t a . I n
d i s c u s s i o n s w i t h MSC, they s t a t e d t h a t t h e S a t u r n V e x p l o s i o n s t u d i e s a r e
n o t complete. However, they f e e l t h a t t h e S a t u r n V r e s u l t s w i l l be
s i m i l a r t o S a t u r n IB r e s u l t s . The r e c e n t r e s u l t s have been p r e s e n t e d t o
b o t h S a t u r n I B and V Program Managers, and t h e small r i s k involved w i t h
max q a b o r t s has been a c c e p t e d .
�b.
S-IC Control Engine Out S / C Breakup Problem
Analysis conducted on AS-504 v e h i c l e i n d i c a t e s t h a t l o a d s
a t t h e CM/SM j o i n t w i l l exceed t h e c a p a b i l i t y a s t h e r e s u l t of a s i n g l e
S-IC e n g i n e - o u t . The bending moment a t t h i s j o i n t i s approximately
30 p e r c e n t h i g h e r than t h e maximum l o a d s p r e d i c t e d f o r AS-503 ( 5 . 3 x
10" i n - l b s f o r AS-503 compared t o 6 . 9 x l o 6 i n - l b s f o r AS-504 a t SIC
s t a t i o n 1010). This bending moment i n c r e a s e i s due t o t h e f o l l o w i n g
d i f f e r e n c e s between t h e AS-503 and AS-504:
(1) i n c r e a s e d payload
weight (95 K f o r AS-503; 100 K f o r AS-504); (2) i n c r e a s e d p r o p e l l a n t
l o a d i n g (255,000 pounds i n S-IC and 40,000 pounds i n S - I 1 s t a g e ) ; and
approximately 14 p e r c e n t . This
(3) decreased S - I 1 s t a g e s t i f f n e s s
c o n d i t i o n i s n o t s i g n i f i c a n t l y a f f e c t e d by winds. Data f o r t h e s e
a n a l y s e s have been s e n t t o MSC f o r more d e t a i l e d s t r u c t u r a l load s t u d i e s .
This problem i s s e v e r e i n s o f a r a s i t w i l l n o t a l l o w warning time f o r EDS
t o a l l o w s a f e a b o r t . These d a t a have been p r e s e n t e d t o D r . Rudolph,
S a t u r n V Program Manager, and t o D r . Rees a t Downey, C a l i f o r n i a . A t t h e
meeting w i t h D r . Rees, i t was concluded t h a t a S I C beef-up t o w i t h s t a n d
l o a d s of 6.9 x l o 6 i n - l b s (maximum p r e d i c t e d l o a d s f o r 504 a t S/C s t a t i o n 1010) was n o t f e a s i b l e . I n a d d i t i o n , i t was f e l t t h a t l o a d s of
t h i s magnitude would probably cause problems i n o t h e r p o r t i o n s of t h e
S / C such a s SM o r LM, a s w e l l a s CM/SM j o i n t .
The problem w i l l be
s t u d i e d by MSFC i n v e s t i g a t i n g methods of reducing l o a d s , and MSC i n v e s t i g a t i n g methods of i n c r e a s i n g S / C load c a p a b i l i t y . The f o l l o w i n g a c t i o n
items a r e i n p r o g r e s s :
(1) MSFC w i l l r e - a n a l y z e F-1 engine-out malfunct i o n , from t h e s t a n d p o i n t s of component r e l i a b i l i t y and engine t h r u s t
decay c h a r a c t e r i s t i c s following m a l f u n c t i o n s (SIC l o a d s a r e v e r y s e n s i t i v e
t o t h r u s t decay r a t e ) ; (2) MSFC w i l l i n v e s t i g a t e a l l a s p e c t s of c a n t i n g
t h e F-1 outboard c o n t r o l e n g i n e s , w i t h e i t h e r a n e l e c t r i c a l b i a s o r
mechanical f i x , t o h e l p a l l e v i a t e t h e l o a d s f o r S-IC c o n t r o l engine o u t .
(A 2 1 / 2 degree c a n t w i l l be a n a l y z e d , s i n c e t h i s i s approximately t h e
l i m i t f o r e l e c t r i c a l b i a s , and being a b l e t o m a i n t a i n c o n t r o l f o r nominal
f l i g h t ; t h i s w i l l reduce t h e S / C l o a d i n g t o 5 . 8 x 10" i n - l b s f o r one
S-IC engine o u t . ) ( 3 ) Msc/NAR w i l l determine p r e s e n t S / C c a p a b i l i t y f o r
s i n g l e F-1 c o n t r o l engine o u t , and beef-up n e c e s s a r y t o w i t h s t a n d l o a d s
of 6 . 0 x 10" i n - l b s bending moment; and (4) MSC/NARw i l l t e s t S / C i n
August 1968.
-
The S a t u r n I B AS-206/LM-2 m i s s i o n which was planned a s backup
t o AS-204/L,M-I has been c a n c e l l e d . The AS-206 v e h i c l e w i l l now be used,
i f r e q u i r e d f o r t h e Apollo Program, w i t h AS-207 f o r t h e S a t u r n I B d u a l
miss i o n . A l l AS-206/CM-2 s t u d i e s have been c a n c e l l e d e x c e p t f o r t h o s e
v e r y n e a r completion. These s t u d i e s a r e b e i n g documented f o r f u t u r e
reference.
�3.
S - I 1 Spray Foam I n s u l a t i o n
F u r t h e r t e s t s of t h e S - I 1 S t a g e Spray Foam I n s u l a t i o n were
conducted on t h e X-15 d u r i n g March. The i n s u l a t i o n samples were mounted
on t h e upper speed b r a k e , i n s t r u m e n t e d , and flown over t h e AS-504 max
h e a t i n g t r a j e c t o r y . The temperatures t o b e a t t a i n e d on t h e i n s u l a t i o n
was t h e p r e d i c t e d smooth w a l l temperature of 530" F. The sample on t h e
s t a r b o a r d speed brake was t o be photographed w i t h a camera mounted i n
t h e s t a r b o a r d wing t i p ; however, t h e camera f a i l e d a f t e r exposing 2 f e e t
of f i l m . The d a t a a r e being analyzed t o determine t h e temperatures
a t t a i n e d and t h e e f f e c t i v e n e s s of t h e i n s u l a t i o n . The r e s u l t s of t h i s
a n a l y s i s a r e expected i n e a r l y A p r i l .
4.
AAP C l u s t e r
The a n a l y s i s of t h e f i r s t c l u s t e r m i s s i o n has continued, and
s p e c i f i c a l l y , t h e impact of t h e ML-13A schedule on t h e c l u s t e r r e q u i r e ments was p r e s e n t e d t o D r . Mueller a t t h e LM/ATMTask Team Review i n
Washington, D. C . on March 15 and 16, 1968. R e s u l t s of t h i s meeting
i n d i c a t e d t h e d e s i r a b i l i t y , s u b s e q u e n t l y approved, f o r t h e LM/ATM
unmanned rendezvous and remote manual docking. I n t e r c e n t e r a c t i v i t i e s
on m i s s i o n r e q u i r e m e n t s , guidance, performance, dynamics, and o t h e r
a r e a s have been coordinated by Mission Requirements Panel Meetings on
February 20 and 21, 1968, and March 28 and 29, 1968.
�V.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
Guidance Theory Branch
1.
Support C o n t r a c t S t u d i e s
a.
General I n t e r p l a n e t a r y S t u d i e s
Work i s c o n t i n u i n g on program development f o r t h e FPR s t u d y
u s i n g load r e l i e f c o n t r o l . Modules f o r computing quaternion'' r a t e s from
i n p u t gimbal a n g l e r a t e s and f o r computing gimbal a n g l e r a t e s from i n p u t
q u a t e r n i o n r a t e s have been f o r m a l i z e d , programmed and checked o u t f o r
F o r t r a n e r r o r s on t h e Univac 1107 computer.
A t e c h n i c a l n o t e e n t i t l e d , "Comparison of S e v e r a l Midcourse
Guidance Schemes" has been completed.
b.
Optimal Guidance Study
The problem of o b t a i n i n g good i n i t i a l approximations f o r
t h e Lagrange m u l t i p l i e r s has e s s e n t i a l l y been s o l v e d . The u s e of t h e
impulsive approximations a s s t a r t i n g v a l u e s i n t h e Newton-Raphson i t e r a t i o n has l e d t o convergence i n every case a t t e m p t e d . The p a r t i c u l a r
problems examined were two-dimensional a s c e n t - t o - c i r c u l a r - o r b i t s w i t h
r a d i i ranging from 200 t o 1100 n a u t i c a l m i l e s . Bang-bang c o n t r o l was
implemented and t h e t r a n s f e r t r a j e c t o r i e s were t y p i c a l l y s h o r t t h r u s t /
long coas t / s hor t t h r u s t
.
It i s i n t e r e s t i n g t o n o t e t h e l i n e a r r a t e of convergence of
t h e Newton-Raphson i t e r a t i o n . Empirical checks by computational means
i n d i c a t e t h a t t h e m a t r i x of p a r t i a l d e r i v a t i v e s of t h e t e r m i n a l f u n c t i o n s
w i t h r e s p e c t t o the unknown m u l t i p l i e r s and f i n a l time becomes s i n g u l a r
a t t h e c o r r e c t v a l u e s of t h e m u l t i p l i e r s and f i n a l time. This i d e a i s
being i n v e s t i g a t e d a n a l y t i c a l l y . Because of t h e slow l i n e a r convergence
of t h e Newton-Raphson i t e r a t i o n on t h e s e p a r t i c u l a r problems, v a r i o u s
e x t r a p o l a t i o n a l g o r i t h m s a r e b e i n g implemented.
-
>'c
The t r a n s f o r m a t i o n of c o o r d i n a t e s through t h e commonly used E u l e r a n g l e s
can be r e p l a c e d by a t r a n s f o r m a t i o n i n v o l v i n g f o u r E u l e r parameters i n
which t r i g o n o m e t r i c f u n c t i o n s do n o t e x p l i c i t l y a p p e a r . These E u l e r
parameters may be regarded a s the components of a q u a t e r n i o n . The
q u a t e r n i o n f o r m u l a t i o n i s h i g h l y e f f i c i e n t f o r computing purposes.
�I n v e s t i g a t i o n of i n t e g r a t i o n techniques has continued.
l i m i n a r y i n v e s t i g a t i o n of t h e Romberg i n t e g r a t i o n method has r e v e a l e d
t h a t Romberg i s n o t s o s a t i s f a c t o r y a s e q u i v a l e n t Runge-Kutta formula,
The flaw i n Romberg methods i s due t o t h e p r o h i b i t i v e number of d e r i v ~
t i v e e v a l u a t i o n s r e q u i r e d . For example, a t h i r d o r d e r Romberg (using
~ y s t r o m ' s second o r d e r method) r e q u i r e s t h r e e e v a l u a t i o n s of t h e
d e r i v a t i v e p e r i n t e g r a t i o n s t e p , w h i l e t y p i c a l Runge-Kutta methods
r e q u i r e d two e v a l u a t i o n s . For h i g h e r o r d e r methods, Romberg i s even
more punishing:
a n i n t h - o r d e r Romberg r e q u i r e s 31 e v a l u a t i o n s , RungeK u t t a t e n t h - o r d e r , o n l y 12. However, t h e s t e p - s i z e c o n t r o l f e a t u r e of
Romberg may be u s e f u l f o r low o r d e r formulas.
c.
Quas i-Optimal Guidance Study
T r a j e c t o r i e s t e r m i n a t i n g i n v a r i o u s e l l i p t i c a l o r b i t s were
g e n e r a t e d u s i n g QUOTA a s a guidance technique. The r e s u l t s a r e now b e i l
compared w i t h COV and IGM r e s u l t s . A survey of t r a j e c t o r i e s w a s general
v a r y i n g t h e frequency of update time f o r t h e guidance scheme (QUOTA).
Also, a s t u d y of a l t e r n a t e m i s s i o n p o s s i b i l i t i e s f o r t h e (100 n.mi. x
Sync) a l t i t u d e e l l i p t i c a l o r b i t has been i n i t i a t e d .
A s t u d y of QUOTA a p p l i e d t o h y p e r b o l i c - t o - e l l i p t i c deboos t
p o i n t e d o u t t h e need f o r a n a l y t i c c o n t i n u a t i o n i n e v a l u a t i n g t h e s t a t e
v a r i a b l e i n t e g r a l s f o r QUOTA. A f t e r t h i s m o d i f i c a t i o n , t h e r e s u l t s
have been v e r y s a t i s f a c t o r y .
2.
Contracts
a.
Lockheed
-
Voyager Terminal Guidance A n a l y s i s
The examination of e r r o r s e n s i t i v i t y a s a f u n c t i o n of
t e r m i n a l geometry i s p r o g r e s s i n g . During t h e l a s t r e p o r t i n g p e r i o d ,
t h e c a p a b i l i t y t o a c c o u n t f o r c o r r e l a t e d n a v i g a t i o n a l e r r o r s was
included i n t h e program. A s ix-dimens i o n a l c o v a r i a n c e m a t r i x , which
i s a f u n c t i o n of t h e n a v i g a t i o n a c c u r a c y p o s t u l a t e d , is i n p u t i n o r d e r
t o c o r r e l a t e t h e p o s i t i o n and v e l o c i t y e r r o r a t i g n i t i o n . It was found
t h a t the parameter a ( t h e a n g l e between t h e t h r u s t v e c t o r and t h e v e l o c i t y v e c t o r a t i g n i t i o n ) has a major e f f e c t on t h e magnitude of many of
the o r b i t a l e r r o r p a r t i a l d e r i v a t i v e s .
b.
Lockheed
-
Rendezvous Guidance
Two r e p o r t s have been submitted t h i s period: "The Minimizat i o n of t h e Fuel Consumption i n t h e F i r s t Burn of a P l a n a r Two-Burn
Rendezvous" and "Extens i o n of t h e Dual-Phase Plane Terminal Guidance
The f i r s t r e p o r t shows t h a t t h e
Method t o Long Terminal Burn Times."
f i r s t burn i t e r a t i o n scheme is s u p e r l i n e a r , and t h e second extends t h e
dual-phase plane a n a l y s i s of t h e second burn t o i n c l u d e f i r s t o r d e r
gravitational effects.
�3.
In-House S t u d i e s
a , A paper e n t i t l e d "A Method of T r a j e c t o r y A n a l y s i s w i t h
Multimission C a p a b i l i t y and Guidance Application" has been accepted
f o r p r e s e n t a t i o n a t t h e 1968 AIAA Guidance, C o n t r o l and F l i g h t
Dynamics Conference.
The three-dimensional o p t i m i z a t i o n deck programmed f o r
t h e CDC-3200 performs q u i t e w e l l , and has a u t o m a t i c a l l y found t h e optimal
time f o r a s i m u l a t e d m i x t u r e r a t i o s h i f t of a two s t a g e v e h i c l e , t h e
optimal launch azimuth of a s i m i l a r v e h i c l e s , and t h e optimal c o a s t time
f o r a v e h i c l e t r a n s f e r r i n g between 100 n.m. c i r c u l a r o r b i t and a coplanar
200 n.m. c i r c u l a r o r b i t .
b. The C a r t e s i a n c o o r d i n a t e , completely g e n e r a l , closed-form
s o l u t i o n of t h e two-body s t a t e and s t a t e t r a n s i t i o n m a t r i c e s have been
used t o connect two p o s i t i o n v e c t o r s w i t h a c o n i c i n a f i x e d i n t e r v a l of
time. Then a 3 x 3 m a t r i x i s developed which m u l t i p l i e s e r r o r s i n t h e
p o s i t i o n v e c t o r t o y i e l d t h e c o r r e c t i o n i n t h e v e l o c i t y v e c t o r f o r midc o u r s e guidance. This m a t r i x can be computed i n c l o s e d form a t any time
i n t h e i n t e r v a l of i n i t i a l time t o f i n a l time. F u r t h e r e f f o r t s a r e
needed t o p a t c h c o n i c s a t b o t h ends o r t o n u m e r i c a l l y i n t e g r a t e a t t h e
two ends s o t h a t t h e e f f e c t s of t h e launch p l a n e t and t h e t a r g e t p l a n e t
can b e included i n t h e computations. An e x t e n s i o n of t h i s work l e a d s t o
c l o s e d form s o l u t i o n s f o r t h e primer v e c t o r ( o r t h e Lagrangian m u l t i p l i e r s ) which can be used t o minimize t h e V, o r t h e AV needed t o accomp l i s h rendezvous ( i n s t e a d of j u s t matching t h e p o s i t i o n v e c t o r s ) . A s
was mentioned i n t h e previous p r o g r e s s r e p o r t , t h e closed-form s o l u t i o n s
f o r t h e m u l t i p l i e r s and a s s o c i a t e d t r a n s i t i o n m a t r i c e s a r e a v a i l a b l e and
d u r i n g t h i s r e p o r t i n g p e r i o d t h e f o r m u l a t i o n of t h e optimal two-impulse
rendezvous u s i n g t h e closed-form s o l u t i o n s has been completed. A computer
program u s i n g t h i s f o r m u l a t i o n i s y e t t o be developed.
c . An a p p l i c a t i o n of t h e techniques developed i n t h e f i n a l
r e p o r t f o r c o n t r a c t NAS8-20269 (Optimal Control Theory w i t h A p p l i c a t i o n s
t o Optimal T r a j e c t o r y and Guidance Problems by Charles M. Chambers) has
been formulated f o r u s e as a computer program. When t h e computer
programming is completed , t h i s method can be compared w i t h o t h e r methods
f o r s o l v i n g boundary v a l u e problems a s s o c i a t e d w i t h optimal guidance.
B.
O p t i m i z a t i o n Theory Branch
1.
A p p l i c a t i o n of F u n c t i o n a l A n a l y s i s t o O p t i m i z a t i o n Theory
Research i s now underway i n t h e a r e a of f u n c t i o n a l a n a l y s i s .
The o b j e c t is t o survey some of t h e e x i s t i n g l i t e r a t u r e t o determine
whether advances i n t h e f i e l d have u s e f u l a p p l i c a t i o n t o problems i n
optimization theory.
�2.
Research i n Control Moment Gyros Momentum Management
Work was i n i t i a t e d on a problem i n h e r e n t i n t h e use of c o n t r o ~
moment gyros f o r a t t i t u d e c o n t r o l of a s p a c e v e h i c l e , i . e . , l o s s of t h e
a b i l i t y t o provide a needed c o n t r o l torque because of t h e o r i e n t a t i o n of
t h e a n g u l a r momentum v e c t o r s of t h e g y r o s . The s t u d y w i l l u s e optimal
c o n t r o l t h e o r y t o f i n d a n optimal s o l u t i o n t o t h e problem e i t h e r through
m o d i f i c a t i o n of t h e e x i s t i n g scheme o r development of a new concept.
3.
A n a l y t i c S o l u t i o n of T r a j e c t o r i e s P e r t u r b e d by P l a n a r Force
The NASA Technical Note d e a l i n g w i t h t h e motion of a s a t e l l i t e
under t h e combined i n f l u e n c e of K e p l e r i a n and p l a n a r f o r c e f i e l d s has
been prepared. P r e l i m i n a r y d r a f t p u b l i c a t i o n s a r e expected soon.
4 . I n i t i a l work has been undertaken on a problem which c o n s i d e r s
l a r g e s c a l e d e f l e c t i o n s of ropes and c a b l e s . This s t u d y should have
important a p p l i c a t i o n s t o t e t h e r s between s a t e l l i t e s , t e t h e r s f o r
a s t r o n a u t s t o a s a t e l l i t e , and p o s s i b l y even t o t h e problem of a s t a t i o n a r y s a t e l l i t e a t t a c h e d t o t h e s u r f a c e of t h e e a r t h .
5. A paper "Load-Reducing F l i g h t Control Systems f o r t h e S a t u r n V
w i t h Various Payloads," submitted t o t h e A I M Guidance, Control and
F l i g h t Dynamics Conference, was a c c e p t e d f o r p r e s e n t a t i o n .
6.
Northrop Schedule Order No. 5 2
a.
A n a l y t i c a l F i l t e r Design Study
The f i n a l r e p o r t on t h e i n v e s t i g a t i o n of t h e a n a l y t i c a l f i l t e r
d e s i g n technique proposed by R. W. Bass i n 1965 has been r e c e i v e d and
d i s t r i b u t e d . Because of d i f f i c u l t i e s encountered i n a c h i e v i n g good overa l l performance w i t h t h e f i l t e r s designed by t h i s t e c h n i q u e , no f u r t h e r
i n v e s t i g a t i o n i s planned.
I
A p r e s e n t a t i o n was made on t h e r e s u l t s of i n i t i a l i n v e s t i g a t i o n of a modified a n a l y t i c a l d e s i g n technique proposed by Bass i n 1967
t o overcome some of t h e problems of h i s e a r l i e r technique.
It was demons t r a t e d a n a l y t i c a l l y that t h i s modified technique has a g r e a t d e a l of
d i f f i c u l t y i n a c h i e v i n g s u c c e s s f u l o p e r a t i o n w i t h low o r d e r f i l t e r s . I f
h i g h o r d e r f i l t e r s a r e t o be used, one might as w e l l t r y t o approximate
Kalman-type f i l t e r s .
S i n c e previous e f f o r t s u s i n g known a n a l y t i c a l d e s i g n techniques have been u n s u c c e s s f u l f o r space v e h i c l e a p p l i c a t i o n s , some
thought i s now b e i n g g i v e n t o t r y i n g t o e s t a b l i s h what requirements on
t h e f i l t e r we have i n p r a c t i c e , i n t h e hope t h a t a n a n a l y t i c o r computero r i e n t e d i t e r a t i v e technique can be devised t o meet our s p e c i f i c
requirements.
�b.
Sampled-Data Root Locus Program
The o r i g i n a l program assumed t h a t continuous f i l t e r s and
sampling occurred o n l y on t h e t o t a l compensated e r r o r s i g n a l . Capabili t y t o employ d i g i t a l compensation on t h e loop s i g n a l has been added.
However, t h i s a d d i t i o n has d e t e c t e d what a r e a p p a r e n t l y some l o g i c
e r r o r s i n t h e o r i g i n a l program n o t p r e v i o u s l y found. Logic changes
have a l s o been i n c o r p o r a t e d t o permit more a c c u r a t e d e t e r m i n a t i o n of low
frequency r o o t s and t o permit more r a p i d d e t e r m i n a t i o n of t h e s t a b i l i t y
of t h e closed-loop system. It i s hoped that t h i s e f f o r t w i l l be concluded i n t h e near f u t u r e .
c.
S p a c e c r a f t A t t i t u d e Control Study
A previous s t u d y of a t t i t u d e c o n t r o l of a l a r g e s p a c e c r a f t
d u r i n g i n s e r t i o n i n t o o r b i t a b o u t a n o t h e r p l a n e t showed undue s e n s i t i v i t y
of performance t o CG o f f s e t s . Before t h e s t u d y was t e r m i n a t e d , a b r i e f
e f f o r t was conducted t o s e e i f t h e a d d i t i o n of some e a s i l y o b t a i n e d
a c c e l e r a t i o n o r i n t e g r a l a t t i t u d e e r r o r s i g n a l s would reduce t h e s e n s i t i v i t y . Only l i m i t e d s u c c e s s w a s achieved w i t h o u t s o p h i s t i c a t e d s i g n a l
p r o c e s s i n g . The f i n a l r e p o r t on t h i s s t u d y has been published and
d i s t r i b u t e d t o i n t e r e s t e d persons.
d.
Load R e l i e f of t h e S a t u r n v / ~ p o l l o
An i n v e s t i g a t i o n has been i n i t i a t e d t o determine i f s i g n i f i c a n t load r e l i e f of t h e S a t u r n v I ~ p 0 1 1 0is p o s s i b l e u s i n g some simple
techniques n o t considered by Boeing i n t h e i r r e c e n t s t u d y . This
i n v e s t i g a t i o n i s a l s o being used as a n o p p o r t u n i t y t o e v a l u a t e t h e
u t i l i t y of a d e s i g n technique proposed by Tomovic and b r i e f l y i n v e s t i g a t e d by D r . F r e d e r i c k a s a Summer F a c u l t y Fellow l a s t summer.
The f i n a l r e p o r t by Boeing under c o n t r a c t NAS8-21070 and
t h e d a b used by Boeing i n t h e i r s t u d y have been r e c e i v e d and e v a l u a t e d ,
and a computer program t o employ Tomovic's method has been w r i t t e n .
7.
Lockheed Schedule Order 57
a.
Parameter Optimization Study f o r ATM System
Work continued on t h e h y b r i d s i m u l a t i o n of t h e ATM a t t i t u d e
c o n t r o l s y s tern f o r t h e c o n j u g a t e g r a d i e n t method of parameter optimizat i o n . A l i n e a r i z e d dynamic model of t h e system has been developed. Two
performance i n d i c e s a r e now under cons i d e r a t i o n . One minimizes t h e
mean-square e r r o r of t h e p o i n t i n g system, and t h e o t h e r minimizes t h e
mean-square command e r r o r t o t h e cMG's.
�b.
t r o l f o r any
checked o u t .
Alabama, t h e
algorithm t o
ncorporated
8.
A p p l i c a t i o n of C-Minimax Control Theory
The a l g o r i t h m f o r computation of t h e C-minimax optimal cons p e c i f i e d p l a n t has been s e t up on t h e hybrid computer and
Suggestions by D r . C. D. Johnson of t h e U n i v e r s i t y of
o r i g i n a t o r of t h e a l g o r i t h m , on m o d i f i c a t i o n s t o t h e b a s i c
improve a c c u r a c y and v i s i b i l i t y of t h e r e s u l t s have been
and checked o u t .
Honeywell (NAS8-21171)
O b j e c t i v e : To improve t h e performance of t h e load r e l i e f cont r o l system f o r t h e S a t u r n V l ~ o y a g e rdesigned by Honeywell under
NAS8-11206.
The c o n t r a c t p e r i o d c l o s e d on March 26, 1968. P r e l i m i n a r y c o p i e s
of t h e f i n a l r e p o r t have been r e c e i v e d and reviewed. The o f f i c i a l f i n a l
r e p o r t s w i l l be d i s t r i b u t e d w i t h a summarizing cover memo t o complete t h e
study.
C.
As trodynamics Branch
1.
Mission A n a l y s i s Programs
A number of programs n e c e s s a r y f o r n e a r - p l a n e t a r y and i n t e r p l a n e t a r y m i s s i o n a n a l y s i s a r e b e i n g assembled and developed by Lockheed
under t h e m i s s i o n s u p p o r t c o n t r a c t . These programs, i n c l u d i n g t h e
f o l l o w i n g , a r e being documented and t r a n s f e r r e d t o inhouse c a p a b i l i t y .
a.
Planetary Orbiter Occultation
This program computes o c c u l t a t i o n of v a r i o u s b o d i e s (e .g. ,
s u n , e a r t h , Canopus) a s viewed from a probe i n o r b i t a b o u t a g i v e n p l a n e t .
The program i s now o p e r a t i o n a l .
b.
Swingby
A program t o compute t r a j e c t o r i e s which make use of c l o s e
swingbys of p l a n e t s a s a means of t r i p time o r energy m o d i f i c a t i o n has
a l s o been checked-out and t r a n s f e r r e d . Some q u e s t i o n s concerning t h e
o p t i m i z a t i o n o p t i o n s f o r t h e t o t a l t r a j e c t o r y a r e s t i l l being s t u d i e d .
c.
Ground Track and I l l u m i n a t i o n
This Lockheed/Sunnyvale program has n o t y e t been made
operational locally.
�d.
Broken-Plane T r a j e c t o r i e s
Work i s c o n t i n u i n g on checkout of a program t o compute
broken-plane ( t h r e e - i m p u l s e ) t r a j e c t o r i e s . Some a p p a r e n t d i s c r e p a n c i e s
i n t h e d a t a have l e d t o a n i n v e s t i g a t i o n by Lockheed of t h e o p t i m i z a t i o n
scheme which determines t h e p o i n t f o r a p p l y i n g t h e midcourse plane-change
impulse.
2.
Mission Design C h a r t s
a.
Improved V a r i a b l e s
A means of g e n e r a t i n g miss i o n maps i n terms of payload i n
t a r g e t - p l a n e t o r b i t has been developed. C e r t a i n assumptions concerning
t h e v e h i c l e and miss i o n must be i n c o r p o r a t e d t o a c h i e v e t h i s t r a n s f ormat i o n . Other s i g n i f i c a n t v a r i a b l e s a r e being i n v e s t i g a t e d f o r p o s s i b l e
r e p r e s e n t a t i o n on miss i o n c h a r t s .
b.
Expansion t o I n c l u d e Other T r a j e c t o r y Types (Lockheed)
C u r r e n t l y a v a i l a b l e m i s s i o n maps c o n s i d e r d i r e c t t r a j e c t o r i e s o n l y . A r e c e n t l y i n i t i a t e d e f f o r t w i l l expand t h e n o n - d e t a i l e d
v e r s i o n s of t h e maps t o i n c l u d e o t h e r forms of t r a j e c t o r i e s , i n c l u d i n g
b o t h Type I and Type I1 d i r e c t , broken p l a n e , and swingby.
3.
A p p l i c a t i o n s of Non-Central Force Problems t o C e l e s t i a l
Mechanics
Closed-form s o l u t i o n s f o r t r a j e c t o r y problems which approximate
r e a l i s t i c s i t u a t i o n s a r e being studied f o r possible a p p l i c a t i o n t o i n t e r p l a n e t a r y t r a j e c t o r y c a l c u l a t i o n . The work i n t h i s a r e a is based on t h e
f a c t t h a t two-body motion i n a n o n - c e n t r a l f i e l d d e r i v e d from a p o t e n t i a l
of t h e form V(r, 8) = Vl(r
v 2 ( e ) / r 2 (where r and 9 a r e p o l a r c o o r d i n a t e s
of t h e body i n motion) l e a d s t o a s e p a r a b l e Hamilton-Jacobi e q u a t i o n .
The f o r c e on a s p a c e v e h i c l e a t t r a c t e d by s e v e r a l b o d i e s can be reasona b l y w e l l approximated, l o c a l l y a t l e a s t , by such n o n - c e n t r a l f i e l d s .
A program t o p l o t t h e a s s o c i a t e d t r a j e c t o r i e s i s b e i n g developed. It
is expected t h a t we w i l l e v e n t u a l l y use t h e s e t r a j e c t o r i e s , t o g e t h e r w i t h
a p a t c h i n g program t o compute i n t e r p l a n e t a r y t r a j e c t o r i e s .
+
4.
I n t e r p l a n e t a r y n-Body Programs
a.
Program Development
Work on t h e i n t e r p l a n e t a r y n-body program i s c o n t i n u i n g i n
d e p e n d a b i l i t y of i s o l a t i o n r o u t i n e s and program s e l f two main a r e a s :
s u f f i c i e n c y . I s o l a t i o n r o u t i n e s a r e being studied i n a n e f f o r t t o
i d e n t i f y one r o u t i n e which w i l l provide a l a r g e r e g i o n of convergence
�w i t h f a s t convergent p r o p e r t i e s .
To a t t a i n a s e l f - s u f f i c i e n t program two
a r e a s a r e being i n v e s t i g a t e d . F i r s t , a method is needed f o r t h e program
t o o b t a i n double p r e c i s i o n s t a t e v e c t o r s of t h e p l a n e t s a s a f u n c t i o n of
time w i t h o u t u s i n g e x t e r n a l t a p e s o u r c e s . Secondly, a method f o r g e n e r a t ing i n i t i a l g u e s s e s i s needed. P r e s e n t l y , a s e p a r a t e program has t o be
r u n t o g e n e r a t e t h e s e g u e s s e s , b u t such a r o u t i n e could be i n c o r p o r a t e d
i n t o t h e n-body program. Then, t r a j e c t o r i e s could be g e n e r a t e d w i t h o u t
g e t t i n g o f f t h e computer.
(See paragraphs f o r p r o g r e s s r e p o r t on t h i s
i n i t i a l guess g e n e r a t o r program.)
b.
T a r g e t i n g Research (Northrop)
S e v e r a l approaches t o the i n t e r p l a n e t a r y t a r g e t i n g problem
a r e being pursued. The a r t i f i c i a l focus method would determine a c o n i c
connecting t h e launch and a r r i v a l p l a n e t s u s i n g a n a r t i f i c i a l f o c u s . A
second method would r e q u i r e f i t t i n g a two-body c o n i c through t h e d e s i r e d
d e p a r t u r e and a r r i v a l p o i n t s and then computing t h e n e t a c c e l e r a t i o n f o r
s e v e r a l s e l e c t e d p o i n t s a l o n g t h e t r a j e c t o r y i n hopes of more n e a r l y
r e p r e s e n t i n g a n i n t e g r a t e d n-body s o l u t i o n . Another approach is t h e
p o s s i b i l i t y of u s i n g a c o n s t a n t s t e p i n t e g r a t i o n scheme w i t h a s implifiied
model of t h e s o l a r system.
c.
I s o l a t i o n Routine Research (Northrop)
I n the s t u d y of i s o l a t i o n r o u t i n e s , s e v e r a l promising methods
have been i d e n t i f i e d , and more d e t a i l e d s t u d i e s a r e b e i n g conducted i n a n
e f f o r t t o s e l e c t a "best" r o u t i n e o r combination of r o u t i n e s which can be
included i n
a n i n t e r p l a n e t a r y program f o r c r i t i c a l e v a l u a t i o n .
5.
Conic Program f o r Small Computers
Work is w e l l underway i n t h e g e n e r a t i o n of a scaled-down c o n i c
program f o r u s e on s m a l l computers (IBM 1130, CDC 930). This program has
a two-fold purpose. F i r s t , i t would provide most of t h e i n f o r m a t i o n t h a t
l a r g e r c o n i c programs p r o v i d e , b u t would be more e a s i l y a v a i l a b l e and
would have cons i d e r a b l y f a s t e r turn-around time
Secondly, i n s u b r o u t i n e
form, i t would provide i n i t i a l guesses f o r t h e i n t e r p l a n e t a r y programs.
The program i s being assembled by combining s e v e r a l s m a l l inhouse programs
w i t h a few programs o b t a i n e d from o t h e r groups, s u c h as t h e S u r f a c e Launch
Window program provided by R-AERO-X.
.
6.
Optimum Orb i t T r a n s f e r
a.
Energy Requirements Study
The i n v e s t i g a t i o n of t h e g e n e r a l energy requirements f o r
o r b i t a l t r a n s f e r i s c o n t i n u i n g . Programming of t h e c o p l a n a r - c i r c u l a r ,
c o p l a n a r - e l l i p t i c a l , and i n c l i n e d - c i r c u l a r c a s e s should s t a r t soon.
�b.
Impulsive T r a j e c t o r y Survey (United A i r c r a f t MS8-21091)
A rough d r a f t of t h e f i n a l r e p o r t is being reviewed. The
b i b l i o g r a p h y of t h e survey l i s t s 310 s i g n i f i c a n t papers i n t h e f i e l d of
impulsive t r a j e c t o r i e s . The r e p o r t should s e r v e t o summarize t h e s u b j e c t
a r e a t o d a t e , a s w e l l a s i n d i c a t i n g r e g i o n s where f u r t h e r r e s e a r c h i s
required.
7.
Odyssey (Lockheed)
P r e l i m i n a r y t r a j e c t o r i e s have been r u n f o r t h e e l l i p t i c o r b i t
Odyssey experiment. This o r b i t experiment makes use of the s o l a r and
l u n a r p e r t u r b a t i o n e f f e c t s t o a c h i e v e a f a i r l y wide range of p e r i g e e
a l t i t u d e s over t h e experiment l i f e t i m e . Q u a l i t a t i v e e f f e c t s of l u n a r
and s o l a r p e r t u r b a t i o n s a r e being determined i n o r d e r t o s p e c i f y i n i t i a l
c o n d i t i o n s t o y i e l d t h e d e s i r e d range of p e r i g e e a l t i t u d e .
QI. AEROPHYSICS D I V I S I O N
A.
F l u i d Mechanics Research O f f i c e
1.
Aerodynamic Crossed-Beam Programs
The redesigned s p e c i a l t e s t s e c t i o n of t h e 14-inch wind t u n n e l
was r e t u r n e d t o the ME Laboratory f o r rework. D i f f i c u l t y was encountered
i n t h e assembly d u r i n g p r e p a r a t i o n f o r checkout and c a l i b r a t i o n . The
t e s t s e c t i o n has been r e t u r n e d and assembled, and t e s t i n g i s now underway.
2.
Atmospheric Crossed-Beam Program
From January 15 t o A p r i l 3 , 1968, 24 complete t e s t runs cons i s t i n g of crossed-beam and anemometer r e c o r d s have been r e p o r t e d by
Colorado S t a t e U n i v e r s i t y . The r e c o r d s c o n s i s t e d of t h e following:
a.
z e r o beam s e p a r a t i o n s ,
b.
l a r g e beam s e p a r a t i o n s ( g r e a t e r t h a n 60 m), and
c.
experiments w i t h beams p a r a l l e l t o t h e ground t o d e t e r mine i f measurements can be made under cloudy c o n d i t i o n s .
A simple o n - l i n e phase c a l i b r a t i o n method has been designed and
t e s t e d by CSU. These t e s t s r e v e a l e d a phase mismatch i n t h e photod e t e c t o r e l e c t r o n i c s . Steps a r e being taken t o c o r r e c t t h i s mismatch.
The c o n t r a c t f o r t h e new computer code i s being n e g o t i a t e d w i t h
IITRI. The CSU c o n t r a c t amendment was signed on March 25. CSU's r e p l y
on the RFQ has been r e c e i v e d and i s being e v a l u a t e d .
�3.
Base Flow and S e p a r a t i o n Study
The second t e s t phase of t h e base flow and s e p a r a t i o n s t u d y was
completed on February 29, 1968, a t t h e Rosemount Aero-Hypersonic Laborat o r y ' s 6 x 9-inch blowdown t u n n e l . F i f t y - f i v e runs were made d u r i n g a
s i x - d a y period i n v o l v i n g base f l u c t u a t i n g p r e s s u r e and h o t w i r e c o r r e l a t i o n measurements. The d a t a a r e being e v a l u a t e d .
B.
Mechanical Des ign O f f i c e
1. The Transonic T e s t S e c t i o n f o r t h e High Reynolds Number T e s t
Equipment i s being redesigned t o i n c l u d e v a r i a b l e - p o r o s i t y w a l l s . The
o r i g i n a l d e s i g n by Fluidyne Corporation d i d n o t have t h i s f e a t u r e .
2. A p r o t o t y p e micro-force balance system f o r use i n measuring
r o c k e t c o n t r o l impingement f o r c e s on s p a c e c r a f t components i s being
designed. The b a l a n c e system w i l l use semi-conductor s t r a i n gages t o
measure up t o 5 components of f o r c e . T e s t w i l l be conducted i n t h e Low
Density Chamber.
3 . A v a r i a b l e p o r o s i t y t r a n s o n i c t e s t s e c t i o n f o r t h e 18.75 p e r c e n t
High Reynolds Number Equipment P i l o t Model has been designed and r e l e a s e d
for fabrication.
4. The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and t h e i r
current s t a t u s .
Redesign of F l a t P l a t e Protuberance Heat
T r a n s f e r Model, L.R. C . , 4' WT (AT)
Design
Heated Plenum Chamber, L.D. WT (AE)
Design
Redesign of Survey Probe, 14" WT (AE)
Drafting
4" O.D. P r e s s u r e Model, L.T.V.
WT (AD)
Drafting
Low Volume Diaphragm C u t t e r , IBFF (AE)
Drafting
P r e s s u r e Models, X-Beam, STS, 14" WT (AF)
Des i g n
S l o s h Force Measuring System (DD)
Fabrication
Strap-on Force Models, 14" WT (AD)
Fabrication
Tracer M a t e r i a l I n j e c t o r , X-Beam, STS,
14" WT (AF)
Fabrication
�C.
5" O . D . , S a t . V, o a s e Flow Model, X-Beam
14" WT (AF)
Fabrication
Force Models, Experimental, L.D.C.
Fabrication
(AE)
Major Components f o r High Reynolds Number
T e s t Equipment (AE)
Fabrication
Heat S h i e l d , Model and D i f f u s e r Assembly (AT)
De 1i v e r e d
18.75% Model of High Reynolds No. T e s t
Equipment (AE)
Delivered
Remote F l o o r and C e i l i n g Adjustment Hardware,
14" WT (AE)
Delivered
P r e s s u r e Model (5' Cone), 14" WT (AU)
Delivered
Temperature Model (5' Cone), 14'' WT (AU)
Delivered
Diaphragm C u t t e r f o r High Reynolds Number
T e s t Equipment (AU)
Delivered
P r e s s u r e Model, New S o l a r Panel Shroud,
AAP, 14" WT (AD)
Delivered
Aerodynamic Design Branch
1.
E x t e r n a l L o n g i t u d i n a l P r e s s u r e D i s t r i b u t i o n s over t h e
Apollo-Saturn V S p a c e c r a f t Compartment
The e x t e r n a l p r e s s u r e d i s t r i b u t i o n s over t h e Apollo-Saturn V
s p a c e c r a f t compartment have been extended and s l i g h t l y r e v i s e d . The
d a t a , f o r a n g l e s of a t t a c k of 4, 8 and 12 degrees and f o r Mach numbers
between 0.80 and 1 . 4 0 , a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-68-12.
2.
S a t u r n V S t a t i c Aerodynamic T e s t s a t CAL
Some e s t i m a t e s have i n d i c a t e d t h a t a r e d u c t i o n of t e n p e r c e n t
i n forebody a x i a l f o r c e f o r t h e Apollo-Saturn V would be r e a l i z e d w i t h
t h e r e c e n t removal of b a s e scoops from t h e S-IC s t a g e . Consequently,
a t e s t was conducted i n t h e CAL 8 - f o o t t r a n s o n i c wind t u n n e l t o o b t a i n
s t a t i c aerodynamic c h a r a c t e r i s t i c s f o r t h e v e h i c l e w i t h scoops removed.
T e s t s were conducted March 25, 1968 a t Mach numbers between 0.5 and 1 . 3
u s i n g a 0.9 p e r c e n t s c a l e d model. P r e l i m i n a r y r e s u l t s i n d i c a t e a reduct i o n i n forebody a x i a l f o r c e v a r y i n g from 15 p e r c e n t a t Moo = 1.1 t o
5 0 p e r c e n t a t M o o D 0.5, w h i l e low a n g l e - o f - a t t a c k c e n t e r of p r e s s u r e and
normal f o r c e g r a d i e n t s remain unchanged.
�3.
S a t u r n V/S-11-8
Spray Foam I n s u l a t i o n
The second phase of aerodynamic t e s t s on 10 x 10-inch samples
of S-11-8 s p r a y foam i n s u l a t i o n were completed i n t h e MSFC 14-inch
t r i s o n i c wind t u n n e l d u r i n g t h e l a t t e r p a r t of March. T e s t panels
coated w i t h a "chemical dynatherm" and uncoated panels were f l u s h mounted i n t h e t u n n e l s i d e w a l l and s u b j e c t e d t o aerodynamic l o a d s
which simulated t h o s e of t h e maximum dynamic p r e s s u r e c o n d i t i o n s of
t h e 501 f l i g h t t r a j e c t o r y . These t e s t s , a s i n t h e f i r s t phase, d i d
not simulate the S-I1 s k i n f l i g h t temperatures.
These t e s t s included t h e i n v e s t i g a t i o n of t h e e f f e c t s due t o
debonded a r e a s under t h e foam f o r b o t h coated and uncoated p a n e l s .
F a i l u r e s of t h e f i r s t phase t e s t s were due t o d i f f e r e n t i a l p r e s s u r e s
a c r o s s t h e closed c e l l s c r e a t e d by a i r trapped under t h e foam. This
was avoided i n t h e s e t e s t s by a p p l y i n g a vacuum t o t h e a r e a under t h e
foam. This procedure was considered t o be a r e a s o n a b l e s i m u l a t i o n
of t h e p r e s s u r e s under cryogenic temperatures encountered on t h e a c t u a l
S - I 1 s t a g e . Under t h e s e c o n d i t i o n s , t h e r e were no f a i l u r e s of debonded
panels even f o r dynamic p r e s s u r e s of a b o u t 180 p e r c e n t g r e a t e r than
t h a t of f l i g h t .
Other d e f e c t s s t u d i e d c o n s i s t e d of s k i n cracks and debonds of
coated p a n e l s , and coated panels w i t h seams i n t h e foam. The l a t t e r
occur on t h e v e h i c l e where s e c t i o n s of i n s u l a t i o n meet i n a r e a s where
i t i s n o t f e a s i b l e t o s p r a y t h e tank s k i n i n one continuous s h e e t ,
There were no s k i n f a i l u r e s e x c e p t those which occurred f o r 4-inch o r
l a r g e r t r a n s v e r s e cracks i n c o n j u n c t i o n w i t h l a r g e s e m i - c i r c u l a r s k i n
debonds 4-inches wide and 3-inches deep. The s k i n t o r e a t t h e ends
of t h e c r a c k and propagated outward. Based on t h e s e o b s e r v a t i o n s , t h e
p r e d i c t i o n of s k i n l o s s on t h e S - I 1 s t a g e i s n o t p o s s i b l e s i n c e t h e
f a i l u r e propagated t o t h e s i d e edges of t h e s m a l l t e s t p a n e l s . A
r e p o r t p r e s e n t i n g t h e t e s t r e s u l t s is being p r e p a r e d .
4.
Nonlinear L i f t of Bodies of Revolution
The Phase I s t u d y , which i n c l u d e s t h e d e t e r m i n a t i o n of t h e
d e t a i l e d p r e s s u r e d i s t r i b u t i o n on o g i v e - c y l i n d e r and o g i v e - c y l i n d e r /
f r u s t u m - c y l i n d e r models i n t h e MSFC 14-inch t r i s o n i c wind t u n n e l i s
scheduled f o r A p r i l 15, 1968.
An a t t e m p t t o r u n t h e Phase I d a t a r e d u c t i o n program on t h e
R-COMP 7094 f a i l e d because of t h e u n a v a i l a b i l i t y of a s u b r o u t i n e which
CCSD has r e c e i v e d permission t o r u n t h e
had been included by C h r y s l e r .
program a t S l i d e l l , thus e l i m i n a t i n g t h e need f o r modifying and checking
o u t t h e program a t R-COMP.
�C h r y s l e r has completed t h e f a b r i c a t i o n and d e l i v e r y of the
Phasc I p r e s s u r e models. The d e s i g n of t h e Phase I1 v o r t e x survey
equipment i s underway.
5.
Aerodynamic Loads on t h e Proposed SLA F a i r i n g f o r AAP-I1
Vehicles
The l o c a l aerodynamic loads on a proposed f a i r i n g f o r t h e MDA
probe have been determined. The e f f e c t s on t o t a l v e h i c l e s t a b i l i t y ,
drag and l o a d s were a l s o determined. These d a t a have been published
i n O f f i c e Memorandum R-AERO-AD-68-8, "Aerodynamic Loads on t h e SLA F a i r ing f o r AAP-I1 Mission," dated February 23, 1968.
6.
Plume Impingement E f f e c t s t o t h e MDA o r ATM due t o E j e c t i o n
of t h e Nose Cone/SLA from t h e AAP-I1 and AAP-IV Vehicle
P r e l i m i n a r y p r e s s u r e , h e a t t r a n s f e r , and plume c o n s t i t u e n t
e f f e c t s experienced by t h e payloads of t h e AAP-I1 o r AAP-IV v e h i c l e s
d u r i n g nose cone/SL,A e j e c t i o n have been developed. The d a t a a r e
a p p l i c a b l e f o r d e f i n i n g a d v e r s e e f f e c t s of p a r t i c l e contamination o r
aerodynamic thermal loads o r p r e s s u r e loads on ATM experiment packages
o r MDA f u n c t i o n a l s u r f a c e s . These r e s u l t s a r e p r e s e n t e d i n O f f i c e
Memorandum R-AERO-AD-68-13, d a t e d March 13, 1968.
7.
S a t u r n I B A x i a l Force C h a r a c t e r i s t i c s
The aerodynamic a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n I B
v e h i c l e s have been r e v i s e d based on a n a n a l y s i s of f l i g h t b a s e p r e s s u r e
measurements. These d a t a have been published i n R-AERO-AD-68-19 f o r t h e
AS-206 and AS-207 v e h i c l e s .
8.
Apollo-Saturn I Vehicle Aerodynamics
S t a t i c s t a b i l i t y and normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s
f o r t h e Apollo-Saturn I v e h i c l e were d e f i n e d a t a n g l e s of a t t a c k of
1 4 and 16 degrees over t h e Mach number range. These d a t a were d e f i n e d
based on experimental t r e n d s and lower a n g l e of a t t a c k d a t a . These
r e s u l t s , published i n O f f i c e Memorandum R-AERO-AD-68-9, supplement t h e
d e s i g n c r i t e r i a published i n NASA TM X-53657.
These d a t a a r e f o r i n p u t
i n t o c o n t r o l and s t r u c t u r a l a n a l y s i s of t h e v e h i c l e f o r off-nominal t r a jectories studies
.
9.
O r b i t a l Aerodynamics
During t h i s r e p o r t i n g p e r i o d , aerodynamic d a t a f o r AAP m i s s i o n
"A" have been updated t o i n c l u d e a n g l e s of a t t a c k from 250 t o 290 d e g r e e s .
P r e v i o u s l y , d a t a ( p r e s e n t e d i n O f f i c e Memorandum R-AERO-AD-67-90) had
been c a l c u l a t e d o n l y f o r a n a n g l e of a t t a c k of 270 d e g r e e s . The updated
�d a t a a r e contained i n Off i c e Memorandum R-AERO-AD-68-10, " O r b i t a l
d a t e d February 28, 1968.
Aerodynamic Data f o r AAP Mission "A","
10.
Body of Revolution Viscous Cross flow I n v e s t i g a t i o n
A method has been found by which t h e s t a i n l e s s s t e e l flowv i s u a l i z a t i o n models can be darkened (chemically t r e a t e d ) . A g r i d of
l o n g i t u d i n a l and r a d i a l l i n e s w i l l t h e n b e a p p l i e d t o t h e model by
u s i n g a s m a l l t h i n b u r n i s h i n g t o o l . The c o n t r a s t between t h e d a r k
models and t h e w h i t e c h i n a c l a y should provide e x c e l l e n t f l o w - v i s u a l i z a t i o n p i c t u r e s . The g r i d system on t h e model w i l l a l l o w changes i n flow
c h a r a c t e r is t i c s due t o Reynolds number t o be r e l a t e d t o l o n g i t u d i n a l
and r a d i a l d imens i o n s .
Some a d d i t i o n a l f o r c e d a t a a r e r e q u i r e d f o r comparison w i t h
follow-on p r e s s u r e t e s t s of v i s c o u s c r o s s flow models. The f o r c e t e s t s
a r e scheduled t o b e g i n on A p r i l 9 , 1968 and t h e p r e s s u r e t e s t s a r e
scheduled t o b e g i n on A p r i l 15, 1968.
D.
Experimental Aerophysics Branch
1.
Low Density Chamber
The problems of j e t plume behavior i n vacuum and j e t plume
impingement f o r c e s from c o n t r o l j e t s s t r i k i n g s p a c e c r a f t components
have c r e a t e d a need f o r experimental d a t a . To e s t a b l i s h a c a p a b i l i t y
i n t h e a v a i l a b l e f a c i l i t i e s t o measure flow and thermodynamic p r o p e r t i e s
i n cool and h o t j e t s , a program has been s t a r t e d t o determine t h e f e a s i b i l i t y of (1) u s i n g t h e low-density chamber a s t h e a l t i t u d e s i m u l a t o r
and (2) e x h a u s t i n g s c a l e model n o z z l e s i n t o t h e chamber w i t h C 0 2 a s t h e
flow medium. Various experiments have been r u n t o determine t h e o p e r a t ing l i m i t s and t o d e v i s e t e s t i n g approaches. The f o l l o w i n g parameters
have been e s t a b 1 ished:
( a ) Mass flow r a t e s of 10 grams/second of C02 can be maintained
a t a l t i t u d e s of approximately 75 km. Of c o u r s e , l e s s e r flow r a t e s ( 0 . 1
gram p e r second) can be maintained a t h i g h e r a l t i t u d e s (150-200 km).
(b) Model s i z e s have been e s t a b l i s h e d t o r a n g e from 1 0 : l s c a l e
t o 4 0 : l s c a l e . The 1 0 : l s c a l e model would be a segment of t h e O r b i t a l
Workshop, and t h e 40:l s c a l e would be a complete OWS model w i t h a body
diameter of approximately 6 i n c h e s . One problem now being i n v e s t i g a t e d
is t h e a l l o w a b l e t o l e r a n c e s when b u i l d i n g such s m a l l model n o z z l e s .
For
i n s t a n c e , t h e 4 0 : l s c a l e of t h e APS t h r u s t e r would have a t h r o a t diameter
of 0.011 i n c h ; t o g e t a t h r u s t ' e r r o r of l e s s t h a n 2 p e r c e n t , t h e t o l e r a n c e
on t h e t h r o a t diameter would have t o be +0.0001 i n c h .
�(c) Experiments have been r u n which i n d i c a t e t h a t t h e p r e s s u r c s t o be measured a r e i n t h e range of t h e thermocouple gauge type
p r e s s u r e s e n s o r . Some of t h e s e s e n s o r s a r e on hand and o t h e r s have been
o r d e r e d . A l l should be a v a i l a b l e when f a b r i c a t i o n of t h e f i r s t p r e s s u r e
model i s completed. R-AERO-AD has f u r n i s h e d t h e c o n f i g u r a t i o n of the
p r e s s u r e model. A s i n g l e component b a l a n c e i s on hand f o r measuring
a x i a l loads and a multi-component b a l a n c e i s being designed by R-AERO-AM.
(d) A problem has come t o l i g h t d u r i n g t h e s e i n i t i a l s t u d i e s
t h a t r e q u i r e s f u r t h e r i n v e s t i g a t i o n . The temperature and p r e s s u r e t o
which t h e C02 is expanded i n t h e t h r u s t e r nozzle t h e o r e t i c a l l y p l a c e
t h e C02 i n a two-phase ( g a s - s o l i d ) r e g i o n . I n i t i a l experimental r e s u l t s
However, more d e t a i l e d
i n d i c a t e t h a t supersaturation i s occurring
experiments w i l l be conducted t o determine c o n c l u s i v e l y whether t h e r e
is condensation.
.
2.
Impulse Base Flow F a c i l i t y (IBFF)
The t h r e e - e n g i n e phase of t h e p a r a m e t r i c b a s e h e a t i n g s t u d y was
completed d u r i n g February. Remaining i n t h i s program a r e s i n g l e engine
w i t h c o n i c a l and contoured nozzles and a four-engine c o n f i g u r a t i o n . This
program, however, has been i n t e r r u p t e d f o r high p r i o r i t y Reynolds Number
P i l o t Model t e s t i n g .
The 18.75 p e r c e n t High Reynolds Number P i l o t Model equipment has
been i n s t a l l e d and h y d r o s t a t i c a l l y p r o o f - t e s t e d .
Work is being done t o
p e r f e c t t h e new diaphragm c u t t e r mechanism. T e s t i n g scheduled t o b e g i n
w i t h i n t h e month i s expected t o provide experimental d a t a on t h e unsteady
s t a r t i n g process a s s o c i a t e d w i t h t h i s type of f a c i l i t y . Of primary
i n t e r e s t i n t h e t e s t s a r e parameters such a s model and s t i n g s t a r t i n g
l o a d s , t u n n e l blockage from model and s t i n g s i z i n g , tunnel s t a r t time,
etc.
3.
High Reynolds Number T e s t Equipment
The 50-foot s p h e r e and 45-degree i n l e t elbow a r e complete and
a r e being p a i n t e d . S i n c e b i d s r e c e i v e d on a l l remaining hardware a r e
below our o r i g i n a l e s t i m a t e s , s u f f i c i e n t money remains t o purchase a
t r a n s o n i c t e s t s e c t i o n . The Fluid-Dyne drawings a r e b e i n g modified s o
t h a t t h e t r a n s o n i c t e s t s e c t i o n may go o u t f o r b i d s .
The 48" diaphragm t e s t was begun, and should be completed w i t h i n
t h e n e x t s i x o r e i g h t weeks.
�4.
Thermal-Acous t i c J e t F a c i l i t y
(TAJF)
The c o l d flow d u c t of t h e TAJF i s being used t o phase NASA
personnel i n t o t h e o p e r a t i o n of t h e c r o s s beam. This work was formerly
done by IITRI a s p a r t of t h e i r c o n t r a c t .
Power and h i g h p r e s s u r e gas connections t o t h e Helium Heater
have s t i l l n o t been made. S i n c e t h e l a s t r e p o r t , R-OM managed t o have
t h e work removed from t h e o v e r a l l center-wide c o n s o l i d a t e d b i d package
and handled a s a s e p a r a t e item. The b e n e f i t s a r e d o u b t f u l , however,
because t h e b i d package of which i t was o r i g i n a l l y a p a r t has a l r e a d y
been awarded, and t h e s e p a r a t e job is j u s t now a t Purchasing Off i c e t o
go o u t f o r b i d s . The Laboratory had t o f u r n i s h $5,000, and i n t h e
p r o c e s s , t h e e n t i r e job went t o Washington f o r review. With l u c k , we
may be hooked up by mid-May.
5.
1 4 x 14-Inch T r i s o n i c Wind Tunnel
The following t e s t s were r u n d u r i n g February and March 1968:
(1) A p r e l i m i n a r y i n v e s t i g a t i o n t o d e f i n e t h e mean flow
around v a r i o u s protuberances and t o a c q u i r e i n i t i a l d a t a on t h e magnitude of t h e f l u c t u a t i n g loads a t b o t h t r a n s o n i c and s u p e r s o n i c Mach
numbers. T o t a l runs:
191.
(2) A c o n t i n u a t i o n of t h e i n v e s t i g a t i o n f o r R-AERO-AU of t h e
quas i - s t e a d y o s c i l l a t i o n wake s t u d y . This s t u d y cons i s ts of determining
t h e dynamic damping c h a r a c t e r i s t i c s of a 30-degree cone model submerged
i n t h e wake of v a r i o u s wake-source c o n f i g u r a t i o n s a s t h e r e l a t i v e o r i e n t a t i o n between t h e wake s o u r c e and t h e submerged models is v a r i e d . This
t e s t e n t r y was t h e f i f t h phase of t h e s t u d y . T o t a l r u n s : 80.
( 3 ) An i n v e s t i g a t i o n f o r R-AERO-AU t o determine t h e e f f e c t of
changes i n Mach number, o s c i l l a t i o n a m p l i t u d e , and a f t e r - b o d y geometry
on t h e p i t c h damping d e r i v a t i v e s of a r i g i d S a t u r n / A p o l l o forebody
con£ i g u r a t i o n . The t e s t w a s terminated prematurely because of a model
f a i l u r e . T o t a l runs: 45.
A n o t i c e a b l e improvement i n compressor maintenance has r e s u l t e d
from t h e r e c e n t change-over from o r g a n i c o i l t o s y n t h e t i c o i l l u b r i c a t i o ]
This s u b s t i t u t i o n w i l l v i r t u a l l y e l i m i n a t e dangers from b u r n i n g o i l vapol
and reduce carbon d e p o s i t s on compressor v a l v e s .
�6.
Instrumentation
The d i g i t a l magnetic t a p e u n i t has been completely checked o u t
w i t h the former shock t u n n e l a n a l o g - t o - d i g i t a l c o n v e r t e r . This system
i s t o be used i n t h e f u t u r e f o r p i l o t s t u d i e s of o n - l i n e r e a l - t i m e
d i g i t i z i n g of atmospheric cross-beam d a t a . I n t h e meantime, i t has been
used i n a d a t a decimation s t u d y f o r R-AERO-AU.
The u n i t worked q u i t e
s u c c e s s f u l l y and i s a v a i l a b l e f o r any o t h e r work.
The l a s e r crossed-beam system formerly was engineered and
o p e r a t e d by IITRI. MSFC has now assumed t h i s r e s p o n s i b i l i t y and the
system has been i n s t a l l e d a t t h e f a c i l i t y , checked o u t and i s i n use
on a t e s t . As "simple" a s t h e s y s tem was, i t r e q u i r e d a b o u t t h r e e weeks
t o g e t i t operating properly.
For a c o u s t i c t e s t i n g i n t h e 14" t u n n e l and t h e TAJF, a 34-channel
m u l t i p l e x system has been b u i l t o u t of t h e 122-channel system purchased
f o r t h e S a t u r n 45 p e r c e n t t e s t a t AEDC. It has been i n s t a l l e d i n a s m a l l
p o r t a b l e r a c k which can be placed a t t h e t e s t f a c i l i t i e s and cabled t o a
c e n t r a l wide-band r e c o r d e r l o c a t e d i n t h e l a b s p a c e . This w i l l save moving t h e e n t i r e system f o r s m a l l t e s t s and t h e a t t e n d a n t wear and t e a r .
R-AERO-AU i s c o n s i d e r i n g a t e s t t o measure t h e unsteady f o r c e s
on a span-wise c y l i n d e r . This poses some i n t e r e s t i n g and d i f f i c u l t
problems of measurement, and a crude a n a l y s i s has been made i n a memo
d a t e d March 2 7 , 1968, e n t i t l e d "Balances t o Measure Unsteady Loads on
C y l i n d e r s . I'
The plume impingement problems mentioned e a r l i e r have opened
t h e a r e a of low-range f o r c e measurements, ranging from one o r two pounds
downward t o a few thousandths of a pound. A s t a t u s r e p o r t is g i v e n i n a
memo d a t e d March 26, 1968, "Low-Range Force Balances f o r Plume Impingement work."
7.
O r b i t a l Aerodynamics
The p h o t o - c e l l s c a n n e r system i s complete i n a l l r e s p e c t s . The
program t o provide moment d a t a a b o u t b o t h t h e X and Y axes has been comp l e t e d and checked o u t . The program has a l s o been r u n on t h e CDC 3200
computer i n B u i l d i n g 4200, and runs w i t h o u t change. Thus, backup comput a t i o n i s a v a i l a b l e . The o u t p u t d a t a and o u t p u t format have been agreed
upon by a l l concerned. No f u r t h e r r e p o r t i n g w i l l be made on t h i s item.
The d i g i t a l TV s c a n n e r is s t i l l i n computer checkout.
�8.
Data Reduction
Aside from t h e normal f a c i l i t y d a t a r e d u c t i o n , s e v e r a l a d d i t i o n a l programs have been w r i t t e n . One program t o l e a s t - s q u a r e s - c u r v e f i t wind t u n n e l c o e f f i c i e n t d a t a and remove t h e t a r e v a l u e s of t h e
c o e f f i c i e n t has been w r i t t e n and checked o u t f o r a p a r t i c u l a r t e s t .
The new n o z z l e f o r t h e s p e c i a l t e s t s e c t i o n f o r crossed-beam
work i s t o be c a l i b r a t e d . A s p e c i a l program was w r i t t e n f o r t h i s
work .
As p a r t of t h e n o n l i n e a r l i f t (viscous c r o s s flow) s t u d i e s , a
t e s t i s t o be r u n i n t h e 14-inch t u n n e l u s i n g a model w i t h about 300
p r e s s u r e o r i f i c e s . A program was w r i t t e n t o reduce t h e s e d a t a t o p r e s s u r e c o e f f i c i e n t s , s o r t i t i n t o s e q u e n t i a l form, p r i n t , and punch t h e
r e s u l t s f o r f u r t h e r a n a l y s i s by C h r y s l e r .
E
.
Thermal Environment Branch
1. The s p e c t r o r a d i o m e t e r developed by Rocketdyne under C o n t r a c t
NAS8-21144 i s being i n s t a l l e d i n t h e B-3 t e s t c e l l a t t h e Rocketdyne
Nevada F i e l d Laboratory (NFL). The a b s o r p t i o n - s o u r c e housings and
s p a t i a l s c a n mechanism have been assembled, a l i g n e d , and checked o u t ,
and a r e being i n s t a l l e d i n t h e t e s t c e l l a t NFL. I t is hoped t h a t
t h e f i r s t t e s t s i n t h e t e s t c e l l , beginning t h e l a s t of March, can
be monitored.
The measurement of HF a b s o r p t i o n c o e f f i c i e n t s was
delayed because of t h e r e l o c a t i o n of equipment. This problem has
been r e s o l v e d , and measurements of HF a b s o r p t i o n c o e f f i c i e n t s w i l l
b e g i n immediately.
2. The i n v i s c i d a n a l y s i s of a s i n g l e F-1 exhaust plume a t v a r i o u s
a l t i t u d e s f o r t h e S-IC s t a g e r a d i a t i o n s t u d y h a s been completed. These
plumes have been s t o r e d on t a p e and w i l l b e used by t h e Boeing Company
i n t h e i r r a d i a t i o n a n a l y s i s . The v i s c o u s a n a l y s i s of t h e s e plumes is
c o n t i n u i n g . The r e s u l t s of t h e s e f l o w - f i e l d c a l c u l a t i o n s w i l l b e used
i n t h e gaseous r a d i a t i o n program t o t r y t o e x p l a i n t h e r a d i a t i o n "hump"
i n t h e AS-501 d a t a .
3 . A f t e r a n unexpected d e l a y i n o b t a i n i n g t h e c o n t i n u a t i o n t o
C o n t r a c t NAS7-521, work has s t a r t e d on t h e experimental composite engine
s t u d y being conducted by Rocketdyne. Engine f a b r i c a t i o n and i n s t a l l a t i o n have been completed, and t h e t e s t s t a n d is b e i n g r e a c t i v a t e d . Hot
f i r i n g s a r e scheduled f o r May 1968 r a t h e r than February as p r e v i o u s l y
reported.
�4.
R a d i a t i o n and Low Density Drag C o e f f i c i e n t View F a c t o r
Program
During t h i s p e r i o d t h e checking o u t of t h e v i e w - f a c t o r computer
code was continued. An a l t e r n a t i v e pre-shade s u b r o u t i n e was developed
and coded i n which t h e elements of a s u r f a c e w i l l b e checked f o r shading
a s opposed t o checking t h e nodes of t h e p r e s e n t s u b r o u t i n e . F i n a l checko u t of t h e contour i n t e g r a l method was a l s o continued; r e s u l t s o b t a i n e d
were i n agreement w i t h a n e x i s t i n g v i e w - f a c t o r program, a s w e l l as some
e x a c t a n a l y t i c a l s o l u t i o n s . The program checkout has been delayed
because of r e c e n t long turn-around times a t t h e Computation Laboratory.
This s i t u a t i o n i s expected t o improve..
5. High a n g l e - o f - a t t a c k h e a t i n g t e s t s w i l l be r u n a t Langley
Research Center beginning i n June o r J u l y . The t e s t s w i l l be monitored
and t h e r e s u l t s analyzed by C C S D / N ~Orleans.
W
The t e s t parameters w i l l
i n c l u d e a Mach number range of 3 t o 6, Reynolds numberlft of .44 x 10"
t o 9 . 3 x lo6, and a n a n g l e - o f - a t t a c k range of 0 t o 35 d e g r e e s .
6.
Protuberance T e s t
Work has been i n i t i a t e d t o b u i l d a new t e s t p l a t e . U n f o r t u n a t e l y ,
having been weakened by s e v e r a l previous m o d i f i c a t i o n s , t h e p l a t e became
s l i g h t l y warped a l o n g t h e c e n t e r l i n e when t h e m o d i f i c a t i o n s f o r t h i s t e s t
were made. This was s u b s e q u e n t l y v e r i f i e d i n t e s t r u n s a t Langley Research
Center. Drawings of t h e p l a t e have been s e n t t o R-AERO-AM f o r s t u d y .
F.
Uns teady Aerodynamics Branch
1.
S a t u r n IB Ground Winds
S t u d i e s a r e b e i n g conducted t o determine t h e r e q u i r e d m o d i f i c a t i o n s f o r s i m u l a t i n g t h e AAP-2 and AAP-4 c o n f i g u r a t i o n s w i t h a S a t u r n I B
a e r o e l a s t i c wind t u n n e l model c o n s t r u c t e d f o r d i f f e r e n t s t r u c t u r a l charact e r i s t i c s . Wind-induced l o a d s f o r S a t u r n I B , AS-205, a r e b e i n g p r e d i c t e d .
These p r e d i c t i o n s w i l l be published as soon a s completed.
2.
S a t u r n V Ground Winds
The f a b r i c a t i o n of t h e Uprated S a t u r n V ground winds model by
A t k i n s and M e r r i l l has been delayed because of a n overrun i n funds. No
d a t e f o r model checkout t e s t s and d e l i v e r y has y e t been s e t .
A s t u d y f o r determining t h e second mode bending moment c o n t r i b u t i o n t o t h e ground wind l o a d s imposed on t h e S a t u r n V v e h i c l e empty-onpad c o n f i g u r a t i o n has been completed; t h e r e s u l t s were published Feb, 14,
1968. A s i m i l a r s t u d y i s being made f o r t h e S a t u r n V f u e l e d weight
cond i t i o n .
�P r e d i c t i o n s of ground wind loads and r e s u l t i n g d e f l e c t i o n s f o r
t h e S a t u r n V empty-on-pad and i n t e r m e d i a t e weight c o n d i t i o n s w i t h t h e
LUT and MSS c o n f i g u r a t i o n s have been completed. This i n f o r m a t i o n was
published March 22, 1968. Also, ground wind l o a d s f o r t h e S a t u r n V,
i n t e r m e d i a t e weight c o n d i t i o n w i t h t h e LUT and MSS c o n f i g u r a t i o n w i t h
dampers detached have been completed and t h e r e s u l t s were published
March 26, 1968.
3.
I n f 1i g h t Acous t i c s
a . Systematic phase and amplitude d i s t o r t i o n s t h a t occurred
i n t h e d a t a a c q u i s i t i o n and r e d u c t i o n systems used i n t h e f o u r - p e r c e n t
AEDC experiment a r e being determined e x p e r i m e n t a l l y by Baganoff and
A s s o c i a t e s . This i s a long and l a b o r i o u s e f f o r t . Experimental r e s u l t s
o b t a i n e d u s i n g t h e w h i t e n o i s e c a l i b r a t i o n d a t a recorded a t t h e time t h e
f o u r - p e r c e n t S a t u r n V model experiment was being conducted i n d i c a t e
t h a t v a r i a n c e s i n phase a n g l e due t o system d i s t o r t i o n s w i l l be of t h e
o r d e r of 1 . 5 d e g r e e s . This r e s u l t i s v e r y f a v o r a b l e and demonstrates
t h a t a l a r g e m a j o r i t y of t h e AEDC f l u c t u a t i n g p r e s s u r e d a t a w i l l be
phase-correctable.
b . F l u c t u a t i n g p r e s s u r e s have been e s t i m a t e d f o r t h e s o l a r
panel pods mounted on t h e S-IVB s t a g e of t h e S a t u r n IVB and S a t u r n V,
a s r e q u e s t e d by R-AERO-XS.
c. Supplemental cross-power s p e c t r a l d e n s i t i e s from t h e f o u r p e r c e n t S a t u r n V experiment a r e being prepared f o r R-P&VE-S t o use i n
s t r u c t u r a l response c a l c u l a t i o n s .
d . F l u c t u a t i n g p r e s s u r e d a t a o b t a i n e d from t h e f o u r - p e r c e n t
model t e s t a r e f i n a l i z e d and w i l l be published soon.
e . A wind t u n n e l program has been scheduled i n t h e AEDC 16f o o t t r a n s o n i c t u n n e l t o provide experimental i n f o r m a t i o n t o h e l p
d e r i v e methods by which f l u c t u a t i n g a i r l o a d s can be a c c u r a t e l y p r e d i c t e d
on and around e x t e r n a l protuberances on launch v e h i c l e s . The program,
t o b e g i n on May 20, 1968, w i l l l a s t f o r a b o u t two weeks. The s t a t i c
and dynamic p r e s s u r e s environment f o r a group of g e n e r a l i z e d p r o t u b e r a n c e s and some s p e c i f i c geometry protuberance w i l l be measured f o r a
Mach number range of 0.6 t o 1 . 6 .
4.
Launch S i t e A c o u s t i c s
a . An R-AERO-AU member a t t e n d e d a planning meeting a t Headq u a r t e r s , a s t h e MSFC r e p r e s e n t a t i v e , f o r a conference on NASA'S prog r e s s i n t h e a p p l i c a t i o n of r e s e a r c h on n o i s e a l l e v i a t i o n t o s u b s o n i c
a i r c r a f t . Two papers on a c o u s t i c s have M r . Weidner's a p p r o v a l t o be
g i v e n from MSFC1s Aero Lab i n October. The conference i s t o be h e l d a t
Langley Research Center w i t h approximately 300 a t t e n d e e s from a l l a r e a s
of a i r c r a f t d e s i g n and o p e r a t i o n a l concerns.
33
�.
b
Acoustic d a t a a c q u i s i t i o n f o r f a r - f i e l d locations f o r
AS-204, AS-205 and subsequent f l i g h t s i s being i n v e s t i g a t e d i n conjunct i o n w i t h KSC.
c . Attenuation-of-sound e s t i m a t e s a r e being s t u d i e d from
a c o u s t i c d a t a from 66 s t a t i c t e s t s of the F-1 engine, t h e S - I and I B ,
and t h e S-IC s t a g e s a t MSFC from 1965 t o December 1967. Data a r e being
s e l e c t e d w i t h a minimum of r e f r a c t i o n i n f l u e n c e s t o more a c c u r a t e l y
d e f i n e a c o u s t i c environments f o r r o c k e t o r j e t engine o p e r a t i o n i n
populated o r u n c o n t r o l l e d a r e a s . These r e s u l t s a r e a p p l i c a b l e t o
i n d u s t r i a l use f o r any n o i s e s o u r c e , and may a l s o be used f o r t r a n s portation applications, etc.
d . The p r e l i m i n a r y i n p u t " P r e d i c t i o n of B l a s t and A c o u s t i c
Environment of Large Space Boosters" f o r t h e j o i n t NASA/AF hazards
manual has been p r e s e n t e d f o r i n c l u s i o n by t h e Committee on Environmental Health and Toxicology of t h e I n t e r a g e n c y Chemical Rocket Propuls i o n Group. Minor r e v i s i o n s o r a d d i t i o n s may be made f o r r e a s o n s of
compatibility.
e . The concern f o r t h e a c o u s t i c environment of t h e Nuclear
Rocket s t a t i o n i s being i n v e s t i g a t e d . A copy of R-P&VE's r e p o r t on
t h e a c o u s t i c environments. w i l l be obtained and compared w i t h t h e pred i c t i o n s now being prepared by R-AERO-AU, f o r n u c l e a r engine o p e r a t i o n s .
f . A c o u s t i c d a t a from c l u s t e r t e s t s of model r o c k e t engines a t
AMTF a r e p a r t i a l l y complete. Manpower t e s t s u p p o r t is a s e r i o u s problem
w i t h programs i n t h i s a r e a .
g . T e s t s of t h e S a t u r n V s c a l e model f o r on-pad and s i m u l a t e d
l i f t - o f f c o n d i t i o n t e s t s a t AMTF has n o t begun because of manpower
l i m i t a t i o n s a t T e s t Laboratory.
5.
Panel F l u t t e r
a . E v a l u a t i o n of t h e AS-204 f l i g h t panel f l u t t e r d a t a showed
t h a t t h e most of t h e panel l o a d i n g was due t o random e x c i t a t i o n . Howe v e r , evidence of l i m i t e d amplitude panel f l u t t e r was p r e s e n t a s
expected. Both types of l o a d i n g s were i n s i g n i f i c a n t f o r t h e AS-204
panels because t h e a c t u a l parameters a f f e c t i n g t h e s e l o a d i n g s were n o t
conducive t o f l u t t e r on t h i s f l i g h t . A d d i t i o n a l i n f l i g h t f l u t t e r measurements w i l l be made on t h e S-IVB s t a g e of t h e AS-502 f l i g h t .
�b. A p r o j e c t meeting was h e l d a t ARC w i t h r e p r e s e n t a t i v e s
from ARC, MSFC and ARAP t o d i s c u s s f u r t h e r d a t a a n a l y s i s and d a t a
r e p o r t i n g of t h e two-d h e n s i o n a l wavy-wall d a t a o b t a i n e d i n t h e Ames
%
2 - f o o t t r a n s o n i c wind t u n n e l . A d d i t i o n a l t e s t s t o o b t a i n boundary
l a y e r i n f o r m a t i o n i n t h e h i g h s u b s o n i c and t r a n s o n i c Mach number
r e g i o n s were a l s o o u t l i n e d . These t e s t s w i l l a l s o be performed i n
t h e Ames 2-foot t u n n e l .
6.
Quas i-Steady O s c i l l a t i n g Wake and F r e e 0s c i l l a t i n g
o
Configuration
Dynamic T e s t s on ~ a t u r n / ~ p o l lForebody
T e s t s on t h i s phase of t h e program were conducted from February
14 t o March 1, 1968, and a g a i n from March 6 t o 13. This phase of t h e
t e s t was t o determine upstream communication e f f e c t s of 30-degree cone
on v a r i o u s wake s o u r c e s . A f r e e - o s c i l l a t i o n b a l a n c e was i n s t a l l e d i n
a 30-degree cone, which could be moved t o v a r i o u s l o c a t i o n s behind t h e
wake s o u r c e s . The v a r i o u s wake s o u r c e s were equipped w i t h e i t h e r
Bytrex o r K i s t l e r X-ducers , depending on what wake s o u r c e was being
employed. T e s t s were s a t i s f a c t o r y w i t h o n l y minor problems.
From March 1 t o March 6 (between t h e above two p e r i o d s ) , a
f r e e o s c i l l a t i o n dynamic t e s t was conducted on a S a t u r n / A p o l l o forebody
c o n f i g u r a t i o n . This program, removed from t h e s c h e d u l e because t h e
tower came l o o s e on t h e model, w i l l be rescheduled a t a l a t e r d a t e .
�VII.
A.
DYNAMICS AND FLIGHT MECHANICS DIVISION
Multi-Projects
1.
Guidance
a.
Synchronous O r b i t Study (New)
This s t u d y , s t a r t e d a b o u t one year ago on a low p r i o r i t y
b a s i s , i s n e a r l y complete, and should be documented by l a t e May 1968.
The a n a l y s i s was d i r e c t e d toward determining t h e c o m p a t i b i l i t y of t h e
IGM guidance system and t h e n e c e s s a r y t a r g e t i n g s u r f a c e f o r a c h i e v i n g
a n e a r t h synchronous o r b i t using t h e S a t u r n V launch v e h i c l e . P a r t I
of t h e s t u d y e s t a b l i s h e d t h e guided t r a j e c t o r y i n t o e a r t h synchronous
a l t i t u d e a t a n o r b i t a l i n c l i n a t i o n e q u a l t o t h e l a t i t u d e of t h e launch
s i t e , and P a r t 11 e s t a b l i s h e d a guided t r a j e c t o r y i n t o a t r u e e a r t h
synchronous o r b i t . ( ~ G I N o r t h r o p )
b.
S-IVB S o f t Lunar Landing Study (Ref: May 1966, p. 33)
This s t u d y was i n i t i a t e d a b o u t 1 1 / 2 y e a r s ago on a low
p r i o r i t y b a s i s t o e s t a b l i s h t h e f e a s i b i l i t y of using t h e b a s i c S a t u r n V
Launch Vehicle and determine t h e r e q u i r e d changes t o t h e t a r g e t i n g
philosophy f o r IGM t o g u i d e each phase of t h e m i s s i o n . The payload above
t h e d r y S-IVB s t a g e on t h e l u n a r s u r f a c e i s approximately 35,000 pounds
when t h e S-IVB s t a g e a c h i e v e s s o f t l a n d i n g v i a a l u n a r parking o r b i t .
(~GINorthrop)
An i n t e r i m review i s planned f o r e a r l y A p r i l .
2.
Dynamics and Control
a.
GPS High Speed Analog (Ref:
J a n . 1968, p. 41)
A l l t h e t a p e s f o r t h e 1120 winds have been r e c e i v e d and
checked o u t . Three t a p e s a r e a v a i l a b l e :
(1) t o t a l wind p r o f i l e , ( 2 )
f i l t e r e d wind p r o f i l e , and ( 3 ) t u r b u l e n c e f i l t e r e d o u t of t h e t o t a l wind
p r o f i l e . These t a p e s e x i s t f o r b o t h t h e s c a l a r and d i r e c t i o n a l winds.
Using the o r i g i n a l 400 s c a l a r wind sample has e s s e n t i a l l y v e r i f i e d t h e
1120 s c a l a r wind p r o f i l e s . It i s planned t o s t u d y t h e v e h i c l e r e s p o n s e
u s i n g t h e d i r e c t i o n a l winds t o v e r i f y conclusions of the s c a l a r wind
s t u d y . A l l s t u d i e s t o d a t e s t i l l show t h a t t h e s y n t h e t i c p r o f i l e i s
s l i g h t l y c o n s e r v a t i v e f o r t h e S a t u r n V.
(DDD)
�b.
Pre-Launch Wind Monitoring (New)
A c o n t r a c t was awarded i n March t o Martin-Denver t o e s tabl i s l l a b e t t e r technique f o r pre-launch wind monitoring.
The wind is t o
be s e p a r a t e d i n t o quas i - s teady and t u r b u l e n c e p r o f i l e s w i t h perk i s t e n c e
c h a r a c t e r i s t i c s a t t a c h e d t o each. The p r e d i c t e d launch v e h i c l e is t h e n
based on t h e s e winds s e v e r a l hours b e f o r e launch.
chara art in)
B.
Saturn V
1.
Mission P r o f i l e
S-IVB Disposal Analysis (Ref: 0ct.-Nov. 1967, p. 45): The
l u n a r i m p a c t l s l i n g s h o t mode of S-IVB d i s p o s a l i m p l i e s adding a n e g a t i v e
impulse t o t h e s p e n t s t a g e soon a f t e r s p a c e c r a f t s e p a r a t i o n , a l t e r i n g
t h e t r a j e c t o r y s o t h a t i t e i t h e r impacts t h e moon, passes i n t o a " s l i n g shot" c o r r i d o r where escape v e l o c i t y i s a t t a i n e d , o r a c h i e v e s a v e r y
long l i f e t i m e e l l i p t i c a l o r b i t . The a t t i t u d e of t h e s p e n t S-IVB s t a g e
a t t h e commencement of r e s i d u a l p r o p e l l a n t dumping was v a r i e d i n a s e a r c h
f o r a l u n a r i m p a c t l n o n e a r t h r e t u r n c o r r i d o r wide enough t o cover a l l
propellant residual uncertainties.
Such a c o r r i d o r was found a t an
a t t i t u d e a n g l e of 180" w i t h r e s p e c t t o t h e l o c a l h o r i z o n t a l ( p e r p e n d i c u l a r
t o t h e l o c a l r a d i u s v e c t o r and p o i n t i n g away from t h e moon), which a s s u r e s
no e a r t h r e t u r n c o n s i d e r i n g a l l earth-moon g e o m e t r i e s , a l l p r a c t i c a b l e
times of AV a p p l i c a t i o n , and +3 sigma i n j e c t i o n a c c u r a c i e s . The r e s u l t s
of t h i s Boeing s t u d y have been p r e s e n t e d t o t h e F l i g h t Mechanics Panel
(~AMI~oeing)
and t h e Guidance, Performance, and Dynamics Subpanel.
2.
Dynamics and C o n t r o l
a.
S a t u r n V T h e o r e t i c a l T r a n s f e r Functions (New)
A c o n t r a c t has been awarded t o Dynamic S c i e n c e s t o develop
a t h e o r e t i c a l t r a n s f e r f u n c t i o n f o r t h e S a t u r n V s p a c e v e h i c l e . The
approach t o be developed can be used f o r wind t u r b u l e n c e r e s p o n s e
s t u d i e s and f l i g h t e v a l u a t i o n procedures.
(DD)
b.
Local Angle-of-Attack
(New)
A
t h e e f f e c t s of
To be included
t i o n , and l i f t
E f f e c t s on Vehicle Dynamic Response
c o n t r a c t has been awarded C h r y s l e r - H u n t s v i l l e t o determine
l o c a l a n g l e of a t t a c k on v e h i c l e r e s p o n s e f o r t h e S a t u r n V.
i n t h e s t u d y a r e t h e v e h i c l e e l a s t i c modes, g u s t p e n e t r a growth e f f e c t s .
(DD)
�c.
LM E x t r a c t i o n from S-IVB ( ~ e w )
A meeting was a t t e n d e d a t M S C ' S r e q u e s t t o d i s c u s s LM
e x t r a c t i o n from t h e S-IVB s t a g e . Data which i n d i c a t e d inadequate
s e p a r a t i o n c l e a r a n c e s u s i n g t h e S e r v i c e Module RCS t o e x t r a c t t h e LM
i n t h e presence of c e r t a i n malfunctions were p r e s e n t e d . A s p r i n g powered method of LM e x t r a c t i o n was then introduced a s t h e mode of LM
e x t r a c t i o n from t h e S-IVB s t a g e . The assumptions, t h e i n p u t d a t a , and
t h e d i g i t a l program used f o r t h e dynamics s t u d i e s were r e v i s e d .
(DC)
3.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
AS-504 Dynamics Data (New)
A document c o n t a i n i n g updated SA-504 s t r u c t u r a l dynamic
c h a r a c t e r i s t i c s f o r use i n f l i g h t c o n t r o l system d e s i g n and v e r i f i c a t i o n has been prepared. R e f l e c t e d i n t h e a n a l y s i s a r e r e c e n t payload
and S - I 1 LH2 t a n k s t i f f n e s s changes, a s w e l l a s t h e dynamic e f f e c t s of
r e l o c a t i n g t h e C o n t r o l / E ~ Sr a t e gyro t o t h e bottom of i t s I U mounting
p l a t e . This document i s being d i s t r i b u t e d a s f i n a l d a t a f o r c o n t r o l
(~~S/~oeing)
system v e r i f i c a t i o n .
C.
Saturn I B
P r o j e c t I n f o r m a t i o n A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
AS-205 C a n t i l e v e r Modes (New)
A c a n t i l e v e r e d bending v i b r a t i o n a n a l y s i s f o r AS-205 was comp l e t e d . P e r t i n e n t d a t a o b t a i n e d from t h e a n a l y s i s were published i n
R-AERO-DD-~~-~~
(DDS)
.
b.
AS-205 Bending A n a l y s i s (New)
A bending v i b r a t i o n a n a l y s i s has been performed f o r t h e AS-205
v e h i c l e t o provide d a t a f o r a f i n a l c o n t r o l system v e r i f i c a t i o n .
F e a t u r e s i n c l u d e a n improved r e p r e s e n t a t i o n of t h e i n t e r s t a g e s t r u c t u r e
developed by Lockheed and use of s t a t i c t e s t s t i f f n e s s v a l u e s f o r t h e
spacecraft structures.
(DDS)
�D.
S a t u r n Apollo A p p l i c a t i o n s rrogram
1.
Cluster
a.
Mission P r o f i l e
(1)
AAP-~/UP-~
Experiment Timeline (Ref:
P. 48)
March 1967,
"AAP-~/AAP-~Experiment Timeline A n a l y s i s , I f dated
January 15, 1968 has been published.
This document, which updates a
s i m i l a r one dated January 9 , 1968, r e f l e c t s changes i n t h e experiment
l i s t , performance requirements, m i s s i o n p l a n , and crew c y c l e . The
r e p o r t i n c l u d e s a b a s i c m i s s i o n p l a n , experiment complement and time
r e q u i r e m e n t s , d a i l y experiment crew time a l l o c a t i o n s , and a d e t a i l e d
t i m e l i n e of a c t i v i t i e s .
Updates of t h e experiment t i m e l i n e s f o r t h i s m i s s i o n
a r e continuous, a s c u r r e n t changes r e q u i r e d through use of t h e F l i g h t
D i r e c t i v e 3C and new b a s e l i n e s c o n f i g u r a t i o n d e f i n i t i o n s a r e i n c o r p o r a t e d .
The n e x t update i s expected t o be documented by A p r i l 1. ( ~ ~ M / ~ a r t i n )
(2)
C o m p a t i b i l i t y Analysis f o r
1968, p. 44)
Am
(Ref:
Dec. -Jan.
1967-
ATM o p e r a t i o n a l time requirements f o r t h e 56-day AAP-314
miss ion have been subs t a n t i a l l y reduced through simultaneous s c h e d u l i n g
of compatible experiments. Requirements of each experiment w i t h r e s p e c t
t o p o i n t i n g and c o n t r o l were d i v i d e d i n t o f i v e modes of o p e r a t i o n .
Experiments w i t h modes of t h e same o r l e s s s t r i n g e n t p o i n t i n g and cont r o l requirements a r e scheduled t o r u n s i m u l t a n e o u s l y w i t h t h e e x p e r i ment c o n t r o l l i n g t h e c l u s t e r a t t i t u d e . It was found t h a t i f compatible
experiments a r e o p e r a t e d s i m u l t a n e o u s l y , i t i s p o s s i b l e t o almost double
t h e amount of d a t a - t a k i n g time f o r t h e t o t a l ATM package of experiments.
It a p p e a r s t h a t we w i l l be a b l e t o meet t h e d a t a - t a k i n g requirements of
ATM by using t h i s approach. This philosophy was p r e s e n t e d t o D r . M u e l l e r ,
March 1 5 , 1968.
Timelines a r e being g e n e r a t e d f o r b o t h a one-man and
two-man requirement f o r simultaneous Am experiment o p e r a t i o n . Also, t h e
human f a c t o r element of one-versus-two-man o p e r a t i o n i s being e v a l u a t e d ,
a l o n g w i t h t h e impact of simultaneous o p e r a t i o n s of s e v e r a l experiments
on s y s tem and sub-sys tems r e q u i r e m e n t s .
�AAP C o m p a t i b i l i t y Analysis i s a t a s k covered under t h e
M a r t i n AAP I n t e g r a t i o n C o n t r a c t . As a r e s u l t of a v i s i t t o Denver,
M a r t i n was r e c e n t l y d i r e c t e d t o b e g i n t h i s t a s k . The c o m p a t i b i l i t y
a n a l y s i s was envisioned a s a f u n c t i o n t o be performed a f t e r r e l e a s e of
t h e Design Reference Mission Document ( s e e p a r a . D.L.a.(5), AAP Base1i n e M i s s i o n D e s c r i p t i o n Document).
I n the c o m p a t i b i l i t y a n a l y s i s , the miss i o n , e x p e r i ments, and s y s tems con£ l i c t s and i n c o m p a t i b i l i t i e s evidenced i n t h e
f i r s t v e r s i o n of t h e DRMD w i l l be i d e n t i f i e d and documented. From t h a t
p o i n t on, t h e c o m p a t i b i l i t y a n a l y s i s w i l l be c o n t i n u o u s l y updated a s
old i n c o m p a t a b i l i t i e s a r e r e s o l v e d and new ones a p p e a r . A t t h e meeting
i n Denver, M a r t i n was d i r e c t e d t o
(a)
produce a f u n c t i o n a l flow diagram of t h e t a s k ,
(b) make a d e t a i l e d o u t l i n e of t h e documentation,
(c)
produce a l i s t of purposes and o b j e c t i v e s of
the task,
(d)
make a l i s t of i n p u t s and o u t p u t s f o r t h e t a s k .
A d d i t i o n a l d e t a i l s a r e contained i n a t r i p r e p o r t d a t e d March 1 8 .
Mart i n )
(3)
(DAM/
AAP-3A Launch Opportunity and Rendezvous (New)
A launch o p p o r t u n i t y and rendezvous a n a l y s i s f o r AAP-3A
m i s s i o n i s being made. AAP-3A l i f t - o f f i s scheduled (ML-13) t o occur
a f t e r day 119 ( r e f e r e n c e d t o U P - 2 l a u n c h ) . The AAP-2 workshop o r b i t
The mishas decayed t o a 219 n.mi. c i r c u l a r o r b i t a t AAP-3A l i f t - o f f .
s i o n p r o f i l e f o r AAP-3A r e q u i r e s a n i n j e c t i o n a t p e r i g e e of a n 81/120
n.mi. o r b i t . A f t e r a c o a s t of one r e v o l u t i o n , r a i s e apogee t o 209 n.mi.
A t apogee make a phase maneuver t o a 209/199 o r b i t . A f t e r c o a s t i n g one
r e v o l u t i o n , c i r c u l a r i z e i n t o a 209 n.mi. o r b i t ( c o - e l l i p t i c ) , c o a s t a
minimum of 30 minutes and perform TPI and TPF. The nominal phasing
r e q u i r e s t h a t AAP-3A l e a d AAP-2 by 6.438 degrees a t AAP-3A launch. The
b e s t p a i r of in-phase, i n - p l a n e launch o p p o r t u n i t i e s f o r AAP-3A o c c u r s
on day 129. For in-phase launches on t h i s day, t h e plane changes
r e q u i r e d cause a payload d e g r a d a t i o n of l e s s t h a n 10 pounds. The launch
parameters f o r t h e two launch o p p o r t u n i t i e s a r e a s f o l l o w s :
�Timc
-
F i r s t Opportunity
Day: 1Ir:Min: Sec
Second Opportunity
129: 2:43:45.8
129:4:31:51.9
Node (deg)
I n c l . (deg)
Plane Change
A s i m i l a r a n a l y s i s was made f o r AAP-112 documented i n R-AERO-DAO-4-68,
March 2 1 , 1968. (DAO)
(4)
-
CSM/LM A l t e r n a t e Mission
Sun Observation Time
Aug.-Sept.
1967,
p.
46)
(Ref:
One of t h e f a c t o r s determining t h e d e s i r a b i l i t y of t h e
LM/ATM f l y i n g decoupled from the OWS i n a h i g h i n c l i n a t i o n o r b i t i s t h e
t o t a l amount of sun o b s e r v a t i o n time a v a i l a b l e d u r i n g t h e e n t i r e miss i o n .
A s t u d y made d u r i n g t h i s r e p o r t i n g period g i v e s t h e maximum and minimum
t o t a l times f o r t h e m i s s i o n d u r i n g which t h e s p a c e c r a f t i s o u t s i d e t h e
e a r t h ' s umbra ( t h e e x a c t t o t a l time depending on t h e launch time of d a y ) .
These maximum and minimum times a r e p l o t t e d v s i n c l i n a t i o n f o r a l t i t u d e s
of 150 NM, and 200 NM.
It was assumed t h a t t h e launch d a t e was i n
January 1971 and t h e l e n g t h of t h e m i s s i o n was 28 days. I n a d d i t i o n t o
t h i s , a n e s t i m a t e was made of t h e percentage of t h e o r b i t s t h a t t h e sun
and the two t r a c k i n g s t a r s , Canopus and Achernar, a r e a l l t h r e e simult a n e o u s l y o c c u l t e d by t h e e a r t h . Two c a s e s were considered:
(5)
(a)
Launch January 1, 1971, a t 3 p.m. EST i n t o a 50
p e r c e n t i n c l i n a t i o n , 200 NM o r b i t . For a 28-day
m i s s i o n , a l l t h r e e w i l l be s i m u l t a n e o u s l y
o c c u l t e d a t some time f o r 25 p e r c e n t of t h e
orbits.
(b)
Launch March 1, 1970, a t 3 p.m. EST i n t o a 28.95O
i n c l i n a t i o n , 230-NM o r b i t . For a 56-day m i s s i o n ,
a l l t h r e e w i l l be s i m u l t a n e o u s l y o c c u l t e d a t some
time f o r 40 p e r c e n t of t h e o r b i t s .
(DAO)
Mission P r o f i l e f o r C l u s t e r Miss i o n (Ref:
1967-68, p. 43)
Dec. -Jan.
A p r e l i m i n a r y m i s s i o n p r o f i l e has been completed f o r
the AAP-2 m i s s i o n . The launch v e h i c l e c o n s i s t s of t h e 208 S-IB s t a g e
and the 2 1 2 S-IVB s t a g e which i n s e r t s i t s e l f and payload c l o s e t o
apogee i n t o a 230 x 215 NM o r b i t . Oxidizer and f u e l dump sequences a r e
�immediately i n i t i a t e d t o c i r c u l a r i z e i n a 230-mile o r b i t . SLA/Nose cone
j e t t i s o n d u r i n g S-IVB powered f l i g h t was used f o r t h i s p r o f i l e .
P a r a m e t r i c performance d a t a f o r t h e AAP-1 miss i o n
using v e h i c l e 207 have been g e n e r a t e d . S p e c i f i c c a s e s f o r e a r l y , l a t e ,
and t h e w o r s t launch window cases a r e being s t u d i e d .
(DAP)
b.
Dynamics and Control
(1)
OWS o r i e n t a t i o n S t u d i e s (Ref:
P . 46)
Dec. -Jan. 1967-68,
The c o n t r o l system impulse requirements f o r t h e
C l u s t e r I M - 1 3 m i s s i o n schedule a r e being determined. The s t u d y is
concerned w i t h t h e e f f e c t s of man motion, aerodynamic g r a v i t y g r a d i e n t ,
v e h i c l e v e n t s , s e n s o r e r r o r s , o r b i t decay, docking d i s t u r b a n c e s , and
g r a v i t y g r a d i e n t s t o r a g e . The p r e s e n t b a s e l i n e has a r e a c t i o n j e t w i t h
pseudo-rate c o n t r o l d u r i n g Mission 1, 2, and 3A and has CMG f o r t h e
o t h e r m i s s i o n s . The p r o p u l s i o n system i s s i z e d f o r 220,000 l b - s e c of
impulse using 25 l b engines w i t h a minimum impulse of 1.25. P r e s e n t
s t u d i e s i n d i c a t e a impulse requirement of 130 l b s - s e c . per o r b i t t o
keep t h e workshop i n t h e X-POP o r i e n t a t i o n mode and t o t a l impulse
requirement s l i g h t l y above 200,000 l b s - s e c .
(DD)
c.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
(1)
AAP-2 Mission Rigid Body Response Study (New)
A r i g i d body response a n a l y s i s of t h e f i r s t s t a g e
f l i g h t of t h e AAP-2 m i s s i o n is being performed. F l i g h t c o n d i t i o n s of
Mach 1, qa max, q max and n e a r IECO a r e being i n v e s t i g a t e d . Rigid body
responses a r e being obtained f o r t h e RSS bending moments f o r t h e s e c a s e s .
Aerodynamic d a t a r e c e i v e d f o r t h e workshop have n o t included any d a t a
concerning coupling between planes due t o t h e s o l a r p a n e l s b e i n g o u t of
p l a n e ; t h e r e f o r e , t h i s e f f e c t has n o t been included i n t h e p r e s e n t
a n a l y s i s . The 95 p e r c e n t i l e winds a r e b e i n g used, and i t i s expected
t h a t , i n t h e q max c a s e , ' t h e 8' gimbal l i m i t w i l l be reached f o r t h e
RSS bending moment c o n d i t i o n s , b u t l o s s of c o n t r o l i s n o t expected.
(DC)
(2)
S L , / N O SCone
~
J e t t i s o n a s a n I n t e g r a l P i e c e (Ref:
Jan.-Feb. 1968, p. 46)
Development of a scheme t o j e t t i s o n t h e SLA and nose
cone as a n i n t e g r a l p i e c e i n t h e AAP-2 and AAP-4 m i s s i o n s c o n t i n u e s .
A d d i t i o n a l t r a j e c t o r i e s of t h e s I , ~ / n o s e cone r e l a t i v e t o t h e S-IVB s t a g e
and payload have been g e n e r a t e d a s d a t a and assumptions have been r e f i n e d .
�P r e l i m i n a r y c l e a r a n c e d a t a were f u r n i s h e d t o R-AERO-P
f o r p r e s e n t a t i o n a t an AAP Systems Review f o r D r . von Braun on January 24,
1968. These d a t a were documented i n R-AERO-DCC-1-68.
A more r e c e n t s t u d y has been made i n which two base
t h r u s t v e c t o r c a n t a n g l e s f o r t h e LES tower j e t t i s o n motor were compared.
Both base c a n t a n g l e s , 3.8 degrees and 2.5 d e g r e e s , provide c l e a r a n c e s ,
though t h e s m a l l e r (2.5") b a s e c a n t i s p r e f e r a b l e because t h e margin of
c l e a r a n c e f o r t h e 3.8 degrees base c a n t a n g l e i s s m a l l .
(DC)
2.
OWS
P a s s i v e A t t i t u d e Control (Ref:
Dec.-Jan.
1967-68, p. 46)
The p a s s i v e s t a b i l i t y s t u d y of approximate models of space
v e h i c l e c l u s t e r s was completed. R e s u l t s of t h e "angular momentum"
approach a r e summarized i n LMSC TM 54130-171 e n t i t l e d " R o t a t i o n a l Motion
of a S a t e l l i t e a b o u t I t s Center of Mass Under G r a v i t a t i o n a l and AeroThe approach uses t h e Bogolyubov method of a v e r a g i n g
dynamic Torques . ' I
on t h e aerodynamic and g r a v i t y g r a d i e n t t o r q u e s . The r e s u l t s a g r e e w i t h
complete dynamic computer r u n s .
A study t o define the i n i t i a l conditions f o r g r a v i t y gradient
c a p t u r e of t h e s t o r e d c o n f i g u r a t i o n has been i n i t i a t e d . S t a b i l i t y over
t h e f i r s t N-orbits w i l l be considered.
(~CAILockheed)
3.
ATM
AAP Launch Vehicles C a n t i l e v e r Modes (New)
C a n t i l e v e r e d bending v i b r a t i o n a n a l y s e s f o r t h e AAP launch
v e h i c l e s were made. Each v e h i c l e was analyzed i n t h e l i f t - o f f f u e l condit i o n and w i t h a l l p r o p e l l a n t removed from t h e S-IVB and S-IB s t a g e s . Data
(DDS)
.
o b t a i n e d from t h i s s t u d y a r e g i v e n i n R - A E R O - D D - ~ ~ - ~ ~
4.
Unmanned Rendezvous
a.
Mission P r o f i l e
(1)
Unmanned Rendezvous
-
Tether (New)
A b r i e f s t u d y was made d u r i n g t h i s p e r i o d t o determine
t h e f e a s i b i l i t y of docking a n unmanned LM/ATM t o t h e OWS by u s i n g a
t e t h e r . The s t u d y was e s s e n t i a l l y i n two p a r t s :
�(a)
Tether deployment between t h e OWS and t h e LM/ATM
which w a s i n v e s t i g a t e d by t h e M a r t i n Company,
Denver, Colorado.
(b)
R e t r i e v a l techniques whereby t h e LM/ATM could b e
brought w i t h i n c l o s e proximity of t h e OWS by
making d i s c r e t e p u l l s on t h e t e t h e r a f t e r
attachment.
Two d i f f e r e n t r e t r i e v a l techniques were i n v e s t i g a t e d .
The f i r s t r e q u i r e s t h a t t h e LM/ATM be i n s e r t e d i n t o a n e a r c i r c u l a r o r b i t
c o n c e n t r i c w i t h the OWS o r b i t e i t h e r above and c o n s i d e r a b l y ahead of t h e
OWS o r below and c o n s i d e r a b l y behind t h e OWS. The LM/ATM i s t h e n caused
t o go through a s e r i e s ( 3 o r 4) of n e a r Hohmann t r a n s f e r s by p u l l i n g on
t h e t e t h e r . The f i n a l c i r c u l a r a t t i t u d e of each t r a n s f e r i s made t o l i e
n e a r e r and n e a r e r t o t h a t of t h e OWS u n t i l t h e LMIATM i s i n t h e same
o r b i t and q u i t e n e a r t h e OWS. I n t h e o t h e r r e t r i e v a l method, t h e LN/ATM
i s i n s e r t e d i n t o a n o r b i t of e q u a l period w i t h t h e OWS, b u t w i t h a d i f ferent eccentricity.
(The LM/ATM remains i n a n e a r l y c o n s t a n t i n e r t i a l
d i r e c t i o n from t h e OWS i n t h i s o r b i t . ) By p u l l i n g on t h e t e t h e r a t
s p e c i f i c times, t h e LM/ATMo r b i t a l e c c e n t r i c i t y can be brought n e a r e r
and n e a r e r t o t h a t of t h e OWS u n t i l a g a i n t h e two a r e brought i n t o c l o s e
proximity.
(DAO)
(2)
Unmanned Rendezvous
-
Using S-IVB S t a g e (New)
To determine t h e f e a s i b i l i t y of u s i n g t h e S-IVB and I U
s t a g e t o p l a c e t h e LMIATM w i t h i n 500 f e e t of t h e OWS, a s t u d y w a s made
us ing t h e f o l l o w i n g ground r u l e s :
(a)
The S-IVB w i l l have r e s t a r t c a p a b i l i t y .
(b)
Two R-IE l o n g i t u d i n a l t h r u s t e r s w i l l be provided.
(c)
LM r a d a r w i l l be used f o r v e r n i e r maneuvers.
(d)
The I U l i f e t i m e w i l l be extended t o 1 0 112 h o u r s .
(e)
Guidance and Navigation w i l l be improved by 213.
(f)
The launch window requirement i s 30 seconds.
(g)
The S-IVB i s i n s e r t e d a t a p e r i g e e a l t i t u d e of
80
NM.
A nominal t i m e l i n e and m i s s i o n p r o f i l e was developed
which s a t i s f i e d t h e s e ground r u l e s and a p r o p e l l a n t budget f o r t h e
nominal p r o f i l e was prepared. The most promising f l i g h t p r o f i l e
�c o n s i s t s of d i r e c t i n j e c t i o n i n t o a n e l l i p t i c a l phasing o r b i t , a minor
c o r r e c t i o n a f t e r 112 o r b i t using t h e S-IVB a u x i l i a r y p r o p u l s i o n system
o r workshop a u x i l i a r y c o n t r o l (WAC) system, a f t e r 1 114 t o 1 314 o r b i t
c i r c u l a r i z a t i o n w i t h a second S-IVB burn, a l l c o n t r o l l e d by t h e I U .
These maneuvers a r e followed t y p i c a l l y by 4 v e r n i e r b u r n s , l e s s t h a n
4 m/s each, u s i n g t h e a u x i l i a r y p r o p u l s i o n system. The s t u d y i s proceeding w i t h an a n a l y s i s of t h e consequences of i n s e r t i o n e r r o r s a t c i r c u l a r i z a t i o n due t o S-IVB p r o p u l s i o n , n a v i g a t i o n , and guidance.
(~~O/~orthrop)
b.
Guidance
AAP-4 LM/ATM Unmanned Rendezvous (New)
The f e a s i b i l i t y of a c h i e v i n g unmanned rendezvous of t h e uu
ATM w i t h t h e o r b i t a l workshop has been s t u d i e d . The b a s i c K e p l e r i a n
a n a l y s i s and IGM t a r g e t i n g , a l o n g w i t h d e t a i l e d guidance and n a v i g a t i o n
a n a l y s i s of t h e d i f f e r e n t approaches t o rendezvous, were achieved through
The a n a l y s i s included u s i n g t h e LM/ATM prot h e e f f o r t s of R-AERO-DG.
p u l s i o n system t o a c h i e v e rendezvous and u s i n g t h e S-IVB s t a g e w i t h a
proposed second i g n i t i o n of t h e S-IVB s t a g e . A f t e r t h e second S-IVB
i g n i t i o n , t h e f i n a l rendezvous maneuvers were achieved u s i n g t h e APS
(DG)
p r o p u l s i o n s y s tern.
E.
General
Dynamic Response of a Launch Vehicle Model (New)
A s e r i e s of damping and response t e s t s on t h e 115 s c a l e model
S a t u r n I w a s r u n . T h e o r e t i c a l p r e d i c t i o n s based on r e s o n a n t response
d a t a a r e shown t o be a c c u r a t e f o r e i t h e r s i n u s o i d a l o r random e x c i t a t i o n .
However, experimental r e s u l t s on response peaks due t o combined and s i n e random e x c i t a t i o n s did n o t a g r e e w i t h a n a l y t i c a l p r e d i c t i o n s .
I n another
t e s t , t h e s t r u c t u r a l damping i n one mode was found t o be independent of
(DD~/~ockheed).
r e s p o n s e amplitude i n a n o t h e r mode.
�VIII.
A.
FLIGHT TEST ANALYSIS DIVISION
Special Projects Office
1. AS-204 F l i g h t E v a l u a t i o n
The AS-204 F l i g h t E v a l u a t i o n has r e v e a l e d t h a t a l l major systems
performed w i t h i n d e s i g n l i m i t s and c l o s e t o p r e d i c t e d v a l u e s throughout
f l i g h t . Although no malfunctions o r d e v i a t i o n s t h a t a d v e r s e l y a f f e c t e d
f l i g h t o r m i s s i o n accomplishment o c c u r r e d , a few r e f i n e m e n t s based on
f l i g h t t e s t r e s u l t s a r e being i n c o r p o r a t e d f o r f u t u r e f l i g h t s . These
a r e d i s c u s s e d i n d e t a i l i n t h e r e p o r t , " R e s u l t s of t h e Fourth S a t u r n I B
Launch Vehicle T e s t F l i g h t AS-204,'' by t h e S a t u r n F l i g h t E v a l u a t i o n Working Group. This r e p o r t w i l l be d i s t r i b u t e d by A p r i l 1 2 , 1968.
The AS-204 t e s t f l i g h t demonstrated t h e s u c c e s s f u l performance
of t h e o r b i t a l s a f i n g experiment i n c l u d i n g p r o p e l l a n t v e n t i n g , p r o p e l l a n t
dump, cold helium dump, and s t a g e / e n g i n e pneumatic s u p p l y dump. This
f l i g h t a l s o demonstrated t h e adequacy of t h e a t t i t u d e c o n t r o l and v e h i c l e
e l e c t r i c a l systems t o perform f o r extended d u r a t i o n i n o r b i t .
2.
F l i g h t E v a l u a t i o n Panel
The f i f t e e n t h meeting of t h e Apollo F l i g h t E v a l u a t i o n Panel
took p l a c e a t MSC on March 5 , 1968. Main d i s c u s s i o n items were launch
and f l i g h t anomalies d e f i n i t i o n s , e v a l u a t i o n r e p o r t s e c u r i t y c l a s s i f i c a t i o n , range z e r o and l i f t - o f f times d e f i n i t i o n s , and e v a l u a t i o n p l a n s
f o r Apollo 6 (AS-502). An e v a l u a t i o n summary of t h e Apollo 5 (AS-204)
f l i g h t was p r e s e n t e d by MSC and MSFC.
3.
Apollo A p p l i c a t i o n s
-
FEWG-Payload
E x t e n s i v e e f f o r t s have been made d u r i n g t h i s p e r i o d t o a r r i v e
a t t a s k d e f i n i t i o n and d e s c r i p t i o n s of work d e s i r e d from t h e Payload
I n t e g r a t i o n C o n t r a c t o r s r e l a t e d t o planning f o r and r e p o r t i n g t h e r e s u l t s
of t h e p o s t f l i g h t e v a l u a t i o n . These e f f o r t s were n o t involved i n t h e
phase C work, and many a s p e c t s have n o t r e a d i l y been made c l e a r , p a r t i c u l a r l y a s t o t h e c a r r i e r systems. This a r e a i s s t i l l being pursued and
w i l l b e r e s o l v e d soon.
E f f o r t s have been made t o g e t t h e proper i d e n t i f i c a t i o n of p o s t £1 i g h t d a t a hand1 ing and e v a l u a t i o n f u n c t i o n s i n t o t h e Experiment I n t e g r a t i o n Requirement Documents (EIRD). This s e c t i o n , which should l o g i c a l l y
be a t t h e end of t h e document f o l l o w i n g t h e Mission Operations S e c t i o n ,
has n o t been a p p e a r i n g . A l l d e t a i l s a r e n o t y e t a v a i l a b l e , b u t t h e AAP
Program O f f i c e has agreed t o t h i s item and w i l l b e g i n implementation.
The d e t a i l s of t h e s a t i s f a c t i o n of t h e s e requirements w i l l be p r e s e n t e d
Payload (FEWG-P) documents.
i n t h e v a r i o u s F l i g h t E v a l u a t i o n Working Group
-
�B.
F l i g h t Mechanics Branch
1.
Saturn I B
a.
205/CS~-101 Rendezvous Mission
Work was i n i t i a t e d February 1, 1968, t o g e n e r a t e a wind
b i a s e d and a n unbiased t r a j e c t o r y p r o f i l e f o r t h e 205 m i s s i o n . The S-IB
t i l t programs, S-IVB p r e s e t t i n g s , and a s s o c i a t e d t r a j e c t o r i e s were comp l e t e d on February 13. These t r a j e c t o r i e s were g e n e r a t e d u s i n g a 0.7%
t h r u s t b i a s . On March 1 3 , i t was agreed by R-AERO and R-P&VE t h a t t h e
t h r u s t b i a s should be reduced t o 0.4% and t h a t t h e S-IB s t a g e drag coeff i c i e n t should be r e v i s e d . These changes were i n c o r p o r a t e d i n t h e
unbiased t r a j e c t o r y p r o f i l e . A t p r e s e n t , it a p p e a r s t h a t t h e S-IVB
u s a b l e p r o p e l l a n t s a r e a b o u t 300 pounds g r e a t e r than t h e r e q u i r e d FPR.
The o r b i t a l t r a j e c t o r y is s t i l l n o t complete because of
i n s u f f i c i e n t d a t a and o r b i t a l sequence changes.
The d i s p e r s i o n a n a l y s i s i s a b o u t 90 p e r c e n t complete. This
e f f o r t was delayed because t h e S-IVB propuls i o n d i s p e r s ions were n o t
available.
About 5 p e r c e n t of t h e a b o r t and a l t e r n a t e m i s s i o n t r a j e c t o r i e s have been g e n e r a t e d .
Before t h i s m i s s i o n was o f f i c i a l l y c a n c e l e d , t h e f o l l o w i n g
documents had been completed:
(1) "AS-206lLM-2 Launch Vehicle Operat i o n a l F l i g h t T r a j e c t o r y D i s p e r s i o n A n a l y s i s , " d a t e d March 1 5 , 1968;
and (2) "AS-206lLM-2 Launch Vehicle O p e r a t i o n a l F l i g h t T r a j e c t o r y , "
d a t e d March 1 8 , 1968.
c.
2061 207 Rendezvous
The 206 v e h i c l e has been r e a s s i g n e d t o t h e d u a l 2061207
m i s s i o n . Government Furnished Documentation i s being prepared t o be
forwarded t o CCSD t o g e n e r a t e t h e o p e r a t i o n a l t r a j e c t o r i e s and d i s p e r s ion analyses f o r t h i s mission.
d.
S a t u r n I B Q u a r t e r l y Performance Sununary
The performance summary f o r t h e mainstream Apollo miss ions
was d i s t r i b u t e d i n memorandum R-AERO-FMR-64-68, March 13, 1968.
�2.
Saturn V
The "revised" f i n a l t r a j e c t o r y f o r AS-502 i s b e i n g d i s t r i b u t e a . A d i s t u r b i n g f a c t o r has been i n t h e S-IC s t a g e p r o p u l s i o n . It
appears t h a t t h e "tag" v a l u e s had been updated a l o n g w i t h t h e r e v i s i o n s
which allowed a f u e l s e n s o r c u t o f f , a b o u t 1 . 5 p e r c e n t i n c r e a s e i n t h r u s t .
This r e s u l t e d i n a n e f f e c t i v e i n c r e a s e i n s p e c i f i c impulse s i n c e t h e
flow r a t e remained r e l a t i v e l y unchanged.
The r e v i s e d ECF (End Conditions of F l i g h t ) and PCF (Pred i c t e d c o n d i t i o n s of F l i g h t ) memos have been p u b l i s h e d . An update t o
t h e D i s p e r s i o n A n a l y s i s is being v e r i f i e d and should be r e l e a s e d b e f o r e
aunch.
The P r o j e c t s O f f i c e has informed R-AERO-FMT t h a t t h e ~ P / 3 0
w i l l be o f f - l o a d e d 11,000 l b s i n s t e a d of t h e 6,000 l b s o r i g i n a l l y planned.
As f a r a s EMT knows now, t h e r e a r e no r e q u i r e d p r e s e t t i n g changes.
In-house range s a f e t y a n a l y s i s on t h i s m i s s i o n is c o n t i n u i n g .
c.
AS-503 D Mission
TBC i s scheduled t o d e l i v e r t h e S-IC t i l t programs t o MSFC
by A p r i l 3, 1968. TBC i s a l s o examining t h e f o l l o w i n g 8 c a s e s i n o r d e r
t o s e l e c t t h e c a s e t h a t s a t i s f i e s t h e most c o n s t r a i n t s f o r t h e D mission:
70 2nd S-IVB burn
70
I'
11
11
0"
-
10
p i t c h 45"
It
11
yaw t o t h e l e f t
11
11
11
I1
The r e s u l t s of t h e s e c a s e s w i l l be a v a i l a b l e by A p r i l 3, 1968.
It i s s l i g h t l y d i s t u r b i n g t h a t TBC has been engaged i n t h i s
e f f o r t s i n c e February 2 1 , 1968, and s t i l l R-AERO-FM had t o s e l e c t which
r u n s were t o be made f o r a p a r a m e t r i c s t u d y i n t h e shaping and t a r g e t i n g
of t h e 503-D mission.
�A demonstration of t h e Quick Response T a r g e t i n g Program
(QRTP) was given t o MSFC p r i m a r i l y t o e v a l u a t e t h e c o n t r a c t u a l l i n e
items 105 and 106. This program was designed and planned f o r r a p i d
l u n a r t a r g e t i n g and o p e r a t i o n a l t r a j e c t o r y a n a l y s i s . The following i s a
summary of t h i s demonstration:
It was found t h a t t h e program was n o t r e a l l y o p e r a t i o n a l ;
t h a t t h e p l o t s of t h e i n t e r c e n t e r t a r g e t o b j e c t i v e s were incomplete;
t h a t t h e AV'S r e s u l t i n g from midcourse c o r r e c t i o n s r a n h i g h e r than
expected ( j u s t w i t h i n t o l e r a n c e ) ; t h a t t h e s p l i t t i n g of t h e d u a l
o p p o r t u n i t y time of launch d i d n o t o p e r a t e w i t h i n s p e c i f i c a t i o n s ; t h a t
i n t h e e v e n t a time of launch was s e l e c t e d which caused something o t h e r
than a n e x a c t azimuth which was on one of t h e i n p u t t a p e s , t h e deck (a)
would n o t r u n , and (b) t h e f i x was t o r e c y c l e back t o GRR (which is
u n d e s i r a b l e ) ; t h a t p o r t i o n s of t h e e a r t h parking o r b i t were being i n t e g r a t e d twice; t h a t a much l o n g e r p o r t i o n of t h e t r a n s l u n a r i n j e c t i o n was
being i n t e g r a t e d by t h e on-board n a v i g a t o r t h a n was n e c e s s a r y ; t h a t t h e
i n t e g r a t i o n s t e p s used i n b o t h c o a s t and powered f l i g h t were n o t optimum,
b u t could be s i g n i f i c a n t l y i n c r e a s e d ; t h a t t h e documentation would n o t
a l l o w experienced e n g i n e e r s t o work, decode, and r u n t h e program.
On t h e p l u s s i d e , t h e program d i d accomplish t h e o v e r a l l job
i n t h e s p e c i f i e d time l i n e ; t h e program was shown t o be s a t i s f a c t o r i l y
continuous and a u t o m a t i c , and t h e program a l l o w s MSFC t o s a t i s f y i t s
i n t e r c e n t e r commitments i n a s a t i s f a c t o r y manner. Also t h e program cont r i b u t e d t o t h e MSFC s t a t e of t h e a r t i n ( a ) use of burn polynomials f o r
i s o l a t i o n and c a l i b r a t i n g w i t h two cOV' s ; (b) i n c r e a s i n g i s o l a t i o n
r e 1 i a b i l i t y by i n t r o d u c t i o n of a d i s c o n t i n u i t y method which a l l o w s convergence of a l m o s t a l l l u n a r c a s e s ; ( c ) providing a n automated s p l i t
launch time model; (d) providing m u l t i - c a s e s t a c k i n g c a p a b i l i t y ; and
( e ) p r o v i d i n g a continuous t a r g e t t o v e r i f i c a t i o n t o midcourse c a p a b i l i t y .
e.
O r b i t a l Debris
Documents LMsc/HREc A 791053 and LMSC/HRECA 791097, "AS-502
S u r v i v a l and Risk Hazard Analyses," were reviewed and d i s t r i b u t e d .
The 503 b o i l e r p l a t e o r b i t a l d e b r i s a n a l y s i s i s a b o u t 50 perc e n t complete.
�C.
Tracking and O r b i t a l Analysis Branch
1.
Saturn I B
Tracking and communications a n a l y s i s on t h e o p e r a t i o n a l
t r a j e c t o r y launch phase has been completed. Documentation w i l l be
delayed u n t i l t h e o r b i t a l t r a j e c t o r y i s a v a i l a b l e t o complete o r b i t a l
coverage a n a l y s i s .
The AS-206/LN-2 L / V o p e r a t i o n a l t r a j e c t o r y t r a c k i n g and
communications a c q u i s i t i o n and l o s s times were r e c e i v e d from CCSD. S i n c e
t h e m i s s i o n has been c a n c e l l e d , t h e d a t a w i l l n o t be d i s t r i b u t e d .
2.
Saturn V
(1) A considerable amount of in-house e f f o r t has been s p e n t
i n a n a l y z i n g e a r t h and moon impacts of t h e AS-502 S-IVB s t a g e . The s t a g e
i s i n j e c t e d i n t o a h i g h l y e l l i p t i c a l o r b i t (period of a b o u t 16 d a y s ) , and
depending on time and d a t e of launch, t h e s t a g e could impact e i t h e r t h e
moon o r t h e e a r t h on i t s f i r s t o r b i t . Some of t h e r e s u l t s have been docuand R-AERO-FT-6-68.
These memoranda
mented i n memoranda R-AERO-FT-~.-~~
p r e s e n t impact d a t a f o r t h e weeks of March 25 and A p r i l 1, r e s p e c t i v e l y .
Data f o r t h e week of A p r i l 8 have a l s o been g e n e r a t e d .
(2) M r . Tom Buckley, Bendix F i e l d Engineering Corporation,
16 days)
i n s u p p o r t of GSFC, r e q u e s t e d g e o d e t i c d a t a (one f u l l o r b i t
on t h e nominal AS-502 o r b i t a l t r a j e c t o r y . S i n c e t h e s e d a t a were n o t
a v a i l a b l e i n t h e AS-502 o p e r a t i o n a l t r a j e c t o r y , t h e y were g e n e r a t e d
in-house by t h i s o f f i c e .
The i n f o r m a t i o n was assembled and s e n t t o
M r . Buckley by l e t t e r d a t e d February 9, 1968.
-
( 3 ) Transformations of t h r e e s t a t e v e c t o r s from MCCH
s i m u l a t i o n s were provided t o M r . Cremin. These t r a n s f o r m a t i o n s were i n
response t o MSC r e q u e s t f o r v e r i f i c a t i o n of n a v i g a t i o n v e c t o r u p d a t e s .
M r . Cremin used t h e d a t a i n a memorandum t o t h e MSC Co-Chairman of t h e
G&P Subpanel.
( 4 ) Because of a delayed i n i t i a t i o n of t h e i n e r t i a l hold
b e f o r e t h e r e s t a r t of t h e S-IVB, t h e look-angle d a t a provided t o R-ASTR
and s e v e r a l c o n t r a c t o r s w i l l be s l i g h t l y i n e r r o r . We have c o n t a c t e d
M r . Ely, R-ASTR-I, who i n d i c a t e t h a t t h e o r i g i n a l in£ ormation would be
a c c e p t a b l e . The v a r i o u s c o n t r a c t o r s were n o t i f i e d of t h i s s l i g h t change.
�(1) S t u d i e s s i m i l a r t o t h e AS-502 S-IVB impact a n a l y s e s
were performed on t h e AS-503 (UM) S-IVB s t a g e i n s u p p o r t of R-AERO-FM.
It appears t h a t t h i s type of a n a l y s e s w i l l be r e q u i r e d on a l l t r a j e c t o r i e s which a r e h i g h l y e l l i p t i c a l and undergo b o t h s o l a r and l u n a r
perturbations.
(2) Tracking and communications coverage on t h e AS-503
b o i l e r p l a t e c o n f i g u r a t i o n was d i s t r i b u t e d under Memorandum R-AERO-FT1-68.
(3) A memorandum, R-AERO-FT-7-68, showing t h e command
coverage f o r t h e nominal and c o n t i n g e n c i e s c a s e s of t h e S-IVB r e s t a r t s
has been d i s t r i b u t e d . This memorandum i n a d d i t i o n t o R-AERO-FT- 2-68,
which p r e s e n t s t r a c k i n g and communications coverage on t h e p r e l i m i n a r y
AS-503 a l t e r n a t e m i s s i o n p r o f i l e u t i l i z i n g t h r e e S-IVB b u r n s , r e p r e s e n t s
a c o n s i d e r a b l e e f f o r t on our p a r t . These s t u d i e s were done i n conjunct i o n w i t h R-AERO-DA i n s u p p o r t of t h e G&P Subpanel and t h e FMP on t h e
AS-503 manned miss i o n .
(4) Meetings have been h e l d w i t h R-AERO-FM and TBC t o
d i s c u s s c r i t e r i a used t o o b t a i n t e l e m e t r y coverage f o r t h e second
r e s t a r t of t h e S-IVB on t h e manned m i s s i o n . These meetings should
a i d TBC t o c l a r i f y c e r t a i n ground r u l e s t o shape t h e S-IVB b u r n s .
c.
General
(1) TBC has completed SSR-167, "The E f f e c t of Launch AziThis e f f o r t was d e s i g n a t e d t o i n d i c a t e
muth on Antenna Look Angles .I1
t h e v a r i a t i o n i n look a n g l e s d u r i n g launch, parking o r b i t , and t r a n s l u n a r i n j e c t i o n p e r i o d s , and was based on t h e AS-504 Reference T r a j e c t o r y
and t h e l a t e s t a t t i t u d e t i m e l i n e s . The i n f o r m a t i o n was p r e s e n t e d t o
R-ASTR and I-MO and was a l s o p r e s e n t e d a t t h e Reference T r a j e c t o r y
Subpanel h e l d a t MSC on March 22, 1968.
( 2 ) NSL m i s s i o n s u p p o r t i s c u r r e n t l y i n v e s t i g a t i n g t h e
S-Band ground s t a t i o n key-hole v a r i a t i o n s due t o t h e v a r i a b l e launch
azimuth requirements of t h e LLM.
3.
Apollo A p p l i c a t i o n s
a.
C l u s t e r Mission
(1)
Lifetime Analysis
( a ) The l a t e s t l i f e t i m e i n f o r m a t i o n on t h e ML-13
c l u s t e r m i s s i o n was p r e s e n t e d a t t h e Mission Requirements Panel on
February 2 1 , 1968, and has been documented i n Memorandum R-AERO-FT-3-68.
M r . Lavender p r e s e n t e d t h i s same i n f o r m a t i o n i n Washington on February 27.
�(b) P r e s e n t planning on t h e c l u s t e r m i s s i o n is t o f l y
t h e OWS t o a 230 n.m. a l t i t u d e . This a l t i t u d e w i l l g u a r a n t e e (-20) a n
o r b i t a l l i f e t i m e t o complete f l i g h t s 1, 2 , 3A, 3 , and 4. The nominal
decay w i l l provide enough l i f e t i m e t o complete t h e e n t i r e ML-13 s c h e d u l e
of r e v i s i t s w i t h f l i g h t s 5 , 6, and 7 . I t may be p o s s i b l e t o b o o s t t h e
OWS w i t h SIC RCS burns w i t h t h e CSM'S on f l i g h t s 1, 3A, o r 3 by approximately 5 o r 1 0 n.m., and t h i s would i n c r e a s e t h e l i f e t i m e of t h e OWS.
These b o o s t s would be n e c e s s a r y only i f t h e OWS decayed a l o n g t h e -20
decay curve. We have i n v e s t i g a t e d b o o s t i n g t h e OWS a t t h e beginning of
each CSM rendezvous o r j u s t b e f o r e d e o r b i t of t h e CM.
This means t h a t
b o o s t s a r e p o s s i b l e a t 1, 29, 119, 175, 270, and 326 days i n t o t h e m i s s i o n . Only one b o o s t i s p o s s i b l e f o r each CSM, hence, b o o s t a t e i t h e r
1 o r 29 d a y s , a t e i t h e r 119 o r 175 days, and a t e i t h e r 270 o r 326 days.
It i s a l s o p o s s i b l e t o b o o s t w i t h each CSM v i s i t o r w i t h two of t h e
v i s i t s . Again, t h i s would depend on t h e decay. I n any e v e n t , t h e
b o o s t must n o t p l a c e t h e OWS i n t o a h i g h e r o r b i t t h a n 230 n.m. f o r t h e
n e x t CSM rendezvous. A l l combinations of CSM b o o s t s have been i n v e s t i g a t e d . These s t u d i e s a r e documented i n memorandum R-AERO-FT-8-68.
( c ) A p r e s e n t a t i o n on t h e CSM b o o s t e f f e c t s on t h e
c l u s t e r l i f e t i m e were p r e s e n t e d t o D r . Mueller on March 1 5 , 1968. A t
t h i s time, MSC i n d i c a t e d i t was p o s s i b l e f o r t h e CSM t o b o o s t t h e OWS.
(2)
Tracking and Communications A n a l y s i s
A p r e s e n t a t i o n on communications coverage on t h e
c l u s t e r m i s s i o n was g i v e n a t t h e Mission Requirements Panel on February
21, 1968. The d a t a p r e s e n t e d a r e o n l y a small p a r t of t r a c k i n g and
communications a n a l y s i s on t h e c l u s t e r m i s s i o n p r e s e n t l y underway. We
hope t o have t h e s t u d y documented by May 1st.
(3)
Martin I n t e g r a t i o n Contract
S e v e r a l meetings have been held w i t h t h e MMC personnel
concerning branch t a s k s . A t t h i s time, i t a p p e a r s t h a t a l l our t a s k s
which we r e q u e s t e d w i l l be included i n t h e c o n t r a c t . From t a s k d e s c r i p t i o n s and c o n v e r s a t i o n s w i t h Martin and Bendix p e r s o n n e l , they seem t o
understand and seem t o be capable of responding t o a l l phases.
b.
A 1 t e r n a t e Uncoupled Mission
L i f e t i m e Analysis:
S t u d i e s have been made on b o t h t h e OWS
m i s s i o n (AAP-1, 2, and 3A f l i g h t s ) and on ATM Mission (AAP-3, 4 f l i g h t s ) .
R e s u l t s w i l l be published soon.
�c.
S a t u r n V Workshop
(1)
L i f e t i m e Analyses
L i f e t i m e a n a l y s e s on t h e S a t u r n V workshop have been
completed and a r e documented i n Memorandum R-AERO-FT-9-68.
These s t u d i e s
included l i f e t i m e s on t h e workshop f o r v a r i o u s c i r c u l a r o r b i t s i n c l i n e d
a t 50 d e g r e e s , on a n S - I 1 s t a g e i n b o t h a 270 n.m. c i r c u l a r o r b i t and
a 100 by 270 n.m. e l l i p t i c o r b i t , and on a n S-IVB s t a g e of a l o g i s t i c s
f l i g h t i n a n 87 x 120 n.m. e l l i p t i c o r b i t . O r b i t a l i n c l i n a t i o n e f f e c t s
on l i f e t i m e a r e a l s o included. These d a t a were s u p p l i e d t o M r . Goldsby
f o r i n c l u s i o n i n t h e Phase A r e p o r t t o be published by Bellcomm.
(2)
Tracking and Communications Analyses
Data a r e being prepared on t h e a s c e n t and o r b i t a l
coverage of t h e S a t u r n V Workshop. These d a t a w i l l be included i n t h e
MSFC documentation on t h e S a t u r n V Workshop which w i l l be more d e t a i l e d
than t h e Bellcomm r e p o r t .
4.
General
a . M r . Fleischman a t t e n d e d a symposium i n Washington, D. C . ,
a t NASA Headquarters on January 29-30, 1968. The symposium was e n t i t l e d
11
Recent Advances i n Numerical Analysis" and was sponsored by D r . Raymond
Wilson of OART. M r . Fleischman made a p r e s e n t a t i o n on "The A p p l i c a t i o n
of Numerical Techniques i n O r b i t a l L i f e t i m e and S a t e l l i t e Decay Analysis."
b. D r . Wilson (OART) c a l l e d M r . Fleischman and r e q u e s t e d cop
of the a r t i c l e i n t h e January " A s t r o n a u t i c s and Aeronautics ." This ha,
bcen done. He a l s o r e q u e s t e d t h a t he be s e n t any c o p i e s of o t h e r pub1
ished m a t e r i a l which we may have. I n response t o t h i s , we have s e n t
him p r e l i m i n a r y c o p i e s of t h e paper which M r . Fleischman w i l l p r e s e n t
a t New Orleans i n May. Copies of t h e l i f e t i m e a r t i c l e i n January
A s t r o n a u t i c s and Aeronautics have a l s o been s e n t t o D r . Mueller.
c. A paper e n t i t l e d "A Mathematical Programming Approach t o
t h e Scheduling of Experiments i n Space," by E . F. Fleischman, AeroAstrodynamics Laboratory,and P. M. T r e u e n f e l s and P. R. R e b e l e i n of
Honeywell, I n c o r p o r a t e d , has been submitted t o PA0 f o r a p p r o v a l . This
paper i s t o be g i v e n a t t h e 33rd N a t i o n a l Meeting of t h e Operations
Research S o c i e t y of America t o be h e l d i n San F r a n c i s c o on May 1-3,
1968.
�D.
F l i g h t E v a l u a t i o n Branch
1.
Saturn I B
(1)
Post-Flight Trajectory
The i n t e r m e d i a t e (7-day) and f i n a l (14-day) pos t - f 1i g h t
l
e s t a b l i s h e d by CCSD. This i s t h e f i r s t
t r a j e c t o r i e s on ~ ~ - 2 0 4 / L M -were
v e h i c l e f o r which CCSD c o n t r a c t u a l l y had t h e r e s p o n s i b i l i t y f o r t h e t o t a l
p o s t - f l i g h t t r a j e c t o r y e f f o r t w i t h t h e e x c e p t i o n of t h e p r e l i m i n a r y (2-day)
t r a j e c t o r y . They performed v e r y w e l l , d e l i v e r i n g t r a j e c t o r i e s of e x c e l l e n t q u a l i t y i n a t i m e l y manner.
The AS-204 o r b i t a l f l i g h t was e v a l u a t e d , and a s a t i s f a c t o r y agreement w i t h the MSC-determined ephemeris from i n s e r t i o n t o
S-IVB/LM-1 s e p a r a t i o n was o b t a i n e d . Tracking d a t a d e l i v e r y was somewhat
improved over t h e AS-501 f l i g h t , b u t s t i l l l e f t much t o be d e s i r e d . The
b i g g e s t problem i n the o r b i t e v a l u a t i o n was a c c u r a t e l y modeling t h e v e n t ing p r o f i l e .
The v e n t i n g was n o t continuous, a s i t was on AS-501, b u t was
confined t o the p a s s i v a t i o n experiment and subsequent time. F u r t h e r comp l i c a t i n g t h e s i t u a t i o n were occurrences such a s a d a p t e r panel deployment
and S-IVB/LM-1 s e p a r a t i o n which imparted impulsive p e r t u r b a t i o n s t o t h e
o r b i t a l t r a j e c t o r y . The a c c u r a t e d e t e r m i n a t i o n and modeling of a l l t h e s e
e f f e c t s was, of course, of primary importance i n determining t h e o r b i t a l
ephemeris.
(2)
P o s t - F l i g h t Control E v a l u a t i o n
The AS-204lLM-1 I U t e l e m e t r y i n d i c a t e d a l o s s of a l t i ,
tude c o n t r o l on the s p e n t s t a g e between 37,208 and 37,308 seconds range
time. Analyses t o p i n p o i n t t h e e x a c t cause have been somewhat hampere
by l a c k of good t r a j e c t o r y d a t a t o p i n p o i n t t h e a l t i t u d e and a t t i t u d e
time h i s t o r i e s d u r i n g t h i s period of f l i g h t . Since t h e S-IVB t e l e m e t r y
was n o t o p e r a t i n g a t t h i s time, i t was not p o s s i b l e t o determine whether
t h e a u x i l i a r y p r o p u l s i o n system (APS) had r u n o u t of p r o p e l l a n t o r had
ceased o p e r a t i n g due t o o t h e r c a u s e s . A t t h e time t h e l o s s of c o n t r o l
o c c u r r e d , t h e v e h i c l e was f l y i n g a t a c o n s t a n t s p a c e - f i x e d a t t i t u d e ,
and t h e l o c a l a n g l e of a t t a c k was approximately 80 degrees (nose up).
Since t h e o r b i t would have had t o decay t o a b o u t 105 km a l t i t u d e f o r
aerodynamic f o r c e s t o overcome t h e APS, t h e most probable cause was APS
p r o p e l l a n t d e p l e t i o n coupled w i t h aerodynamic f o r c e s .
The most r e c e n t t r a j e c t o r y a v a i l a b l e based on a s t a t e
v e c t o r e s t a b l i s h e d a t 9117 seconds range time (immediately a f t e r p a s s i v a t i o n ) shows t h a t p e r i g e e s h i f t e d and occurred between Tananarive and Hawaii
a t approximately 141 km a l t i t u d e . A p r e l i m i n a r y i n v e s t i g a t i o n of t h e
�aerodynamics involved i n d i c a t e s t h a t even a t 140 km t h e r e i s enough moment
t o cause t h e observed motion and t h a t between 120 and 130 krn t h e aerodynamic
f o r c e s would have been more than s u f f i c i e n t t o cause t h e observed d i s t u r b a n c e . Both IBM and MDAC have agreed t h a t l o s s of APS p r o p e l l a n t coupled
w i t h aerodynamics i s the most f e a s i b l e e x p l a n a t i o n .
Data from Hawaii showed t h e v e h i c l e t o be coning w i t h
t h e base of t h e S-IVB p o i n t i n g g e n e r a l l y a l o n g t h e v e l o c i t y v e c t o r ( i . e . ,
f l y i n g t a i l f i r s t ) . It i s n o t expected t h a t any more d e t a i l e d a n a l y s e s
can be made u n l e s s a b e t t e r t r a j e c t o r y can be obtained from t h e l i m i t e d
t r a c k i n g d a t a a v a i l a b l e from the 6 t h and 7 t h passes over Tananarive and
Hawaii.
Pos t - F l i g h t P r o p u l s i o n Simulation
(3)
The p r o p u l s i o n systems of t h e S-IB and S-IVB s t a g e s were
e v a l u a t e d u s i n g t h e r e c o n s t r u c t e d p r o p u l s i o n s y s tem performance a n a l y s i s
c o n t r i b u t e d by t h e s t a g e c o n t r a c t o r s . The e v a l u a t i o n s d e r i v e d by t h e s t a g e
c o n t r a c t o r s were included i n t h e FEWG r e p o r t . The S-IB and S-IVB s t a g e
a n a l y s i s r e s u l t s a r e summarized i n t h e t a b l e below.
(These r e s u l t s a r e
from a f l i g h t s i m u l a t i o n a n a l y s i s . ) The averages a r e computed over t h e
t o t a l s t a g e burn times,
Av . T h r u s t (N)
Nom.
Act.
-
Stape
S-IB
S-IVB
% Deviation
A C- ~
N O ~ / N O ~
A'v. ISP
NO^
~ c t .
.
% Deviation
~ct-NO~/NO~.
7265223
7355609
1.24
260.62
263.48
1.10
950549
962492
1 26
426 07
425 1
- .23
The p r o p u l s i o n e v a l u a t i o n techniques a r e b e i n g s t u d i e d f u r t h e r i n preparation for future flights.
2.
Saturn V
a.
General
(1)
LVDC Navigation Update
There r e c e n t l y has been much i n t e r e s t i n t h e updating of
t h e launch v e h i c l e guidance computer b e f o r e second burn on t h e S a t u r n V
v e h i c l e s . The a c c u r a c y w i t h which t h i s can be performed i s g r e a t l y
i n f l u e n c e d by t h e accuracy of t h e n e a r - r e a l - t i m e i n s e r t i o n v e c t o r . To
o b t a i n a n e s t i m a t e of t h e a c c u r a c y of t h e n e a r - r e a l - t i m e v e c t o r , a comparison was made between i t and t h e corresponding time p o i n t on t h e f i n a l p o s t These v e c t o r s were o b t a i n e d
f l i g h t trajectory for three recent vehicles.
r e c e n t l y from MSC f o r t h r e e v e h i c l e s and a r e what t h e y considered t h e realtime v e c t o r s .
�SA-203
Space-Fixed V e l o c i t y (m/s)
F l i g h t Path Angle (deg)
Near-RealTime
7788.7
-0.044
Final PostFlight
7793.6
-0.002
Final-RealTime
4.9
-0.042
A l t i t u d e (m)
190926
191039
Cross Range (m)
45139
44927
-212
Cross Range V e l o c i t y (m/s)
358.2
362.2
4.0
113
This comparison i s made a t 442.9 seconds range time. The n e a r - r e a l - t i m e
v e c t o r on AS-203 was determined w i t h d a t a from t h e impact p r e d i c t o r .
Near-RealTime
Space-Fixed V e l o c i t y (m/s)
F l i g h t P a t h Angle (deg)
7798.3
-0.014
F i n a l PostFlight
Final-RealTime
7792.3
-6.0
0.010
-0.024
A l t i t u d e (m)
192011
192097
Cross Range (m)
56293
55677
Cross Range V e l o c i t y (m/s)
252.6
266.2
86
-616
13.6
This comparison is made a t 681.25 seconds range time. On AS-501 t h e nearr e a l - t i m e v e c t o r was determined from U n i f i e d S-Band t r a c k i n g d a t a .
AS-2041~-1
Near-RealTime
Final PostFlight
Final-Real.
Time
Space-Fixed V e l o c i t y (m/s)
7829.2
7828.5
-0.7
F l i g h t P a t h Angle (deg)
0.013
0.005
-0.008
A l t i t u d e (m)
169253
163443
-5810
Cross Range (m)
93217
92688
-529
Cross Range V e l o c i t y (m/s)
533.7
532.6
-1.1
This comparison i s made a t 602.99 seconds range time. The AS-204 nearr e a l - t i m e v e c t o r was determined from Bermuda C-Band r a d a r t r a c k i n g d a t a .
�According t o MSC the n e a r - r e a l - t i m e i n s e r t i o n v e c t o r
can p r e s e n t l y be determined from f i v e d i f f e r e n t s o u r c e s :
(1) t e l e m e t e r e d
launch v e h i c l e guidance d a t a , (2) telemetered s p a c e c r a f t guidance d a t a ,
(3) u n i f i e d S-Band t r a c k i n g d a t a , (4) impact p r e d i c t o r d a t a , (5) s h i p
C-Band r a d a r d a t a . Which v e c t o r t o use i s a human d e c i s i o n t o be made
on t h e b a s i s of which v e c t o r "looks" t h e b e s t .
The accuracy w i t h which t h e v e c t o r can be updated
depends on how w e l l t h e i n s e r t i o n v e c t o r can be i n t e g r a t e d forward, i n
a d d i t i o n . t o t h e a c c u r a c y of t h e i n s e r t i o n v e c t o r . The v e l o c i t y e r r o r s
shown i n t h e above comparisons i f i n t e g r a t e d over much time would r e s u l t
i n s i z a b l e p o s i t i o n e r r o r s . Also, t h e accuracy of t h e v e n t i n g and a e r o dynamic f o r c e s w i l l a f f e c t t h e updated v e c t o r s i n c e t h e s e must be cons i d e r e d i n any i n t e g r a t i o n . T h e r e f o r e , c o n s i d e r a b l e work is y e t t o b e
done t o f u l l y understand t h e a c c u r a c y a t t a i n a b l e w i t h a v e c t o r update.
(2)
LVDC Navigation Update C a p a b i l i t y Checkout
Accelerometer measurement e r r o r s and f a i l u r e s d u r i n g
t h e b o o s t phase of t h e l u n a r m i s s i o n may c r e a t e a need f o r n a v i g a t i o n
update. This update may become n e c e s s a r y t o minimize t h e midcourse
c o r r e c t i o n o r t o b e a b l e t o perform t r a n s l u n a r i n j e c t i o n (TLI). To
determine t h e need and a b i l i t y t o perform a n u p d a t e , t h e f o l l o w i n g
a n a l y s e s must be performed t o answer t h e following q u e s t i o n s :
(a)
What is t h e philosophy of performing TLI burn
w i t h o r w i t h o u t a n update?
(b)
Can midcourse c o r r e c t i o n s be made such t h a t t h e
m i s s i o n can be achieved f o r a n a c c e l e r o m e t e r
f a i l u r e assuming t h a t a s t a t e v e c t o r update i s
made b e f o r e second burn ( s t i l l a p e r t u r b a t i o n i n
second burn plus l o s s of performance)?
The t r a j e c t o r y d i s p e r s i o n s propagated through i n s e r t i o ~
must be determined f o r t h e v a r i o u s a c c e l e r o m e t e r f a i l u r e s and f a i l u r e
t i m e s . This w i l l b e done c o n s i d e r i n g t h e p o s s i b l e p r o p u l s i o n system performance d i s p e r s i o n s which could e x i s t w i t h t h e backup f/m s e l e c t i o n s
a v a i l a b l e . The above t r a j e c t o r i e s w i l l r e q u i r e e v a l u a t i o n by MSC t o
determine i f midcourse c o r r e c t i o n s can be made f o r e i t h e r t h e "no update''
o r "update" c a s e s . The p o s s i b l e d i s p e r s i o n s which e x i s t f o r s t a t e v e c t o r
update w i l l be analyzed through t r a j e c t o r y s i m u l a t i o n programs. The
s t a t e v e c t o r update w i l l b e a f u n c t i o n of t h e a c c u r a c y of t h e r e a l - t i m e
o r b i t d e t e r m i n a t i o n and how a c c u r a t e a n e x t r a p o l a t i o n t o t h e implementat i o n p o i n t can b e made. These a c c u r a c i e s a r e dependent on t h e f l i g h t
azimuth, v e n t i n g , aerodynamics, e t c .
�The r e s u l t s of t h e s e a n a l y s e s w i l l h e l p t o determine
the philosophy f o r s e l e c t i n g t h e backup f/m t o be used f o l l o w i n g a n
accelerometer f a i l u r e .
(Bias f o r h i g h , nominal, o r low performance
case?)
MSC should provide t h e AS-502 real-time-determined
v e c t o r and a v e c t o r e x t r a p o l a t e d t o t h e p o i n t a t which a n update might
be performed (a p o i n t b e f o r e second S-IB burn) f o r comparison w i t h t h e
pos t - f l i g h t o r b i t d e t e r m i n a t i o n .
(3)
Abort and A l t e r n a t e Mission T r a j e c t o r y Simulator
The e s t a b l i s h e d o b j e c t i v e of t h i s program i s t o develop
a S a t u r n V t r a j e c t o r y s i m u l a t o r i n six-degrees-of-freedom t h a t c a l c u l a t e s
a t r a j e c t o r y from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t
phases and t h e parking o r b i t phase t o t h e p o i n t of i n j e c t i o n i n t o a
l u n a r t r a j e c t o r y . This program i s intended t o s i m u l a t e t r a j e c t o r y c a s e s
f o r a b o r t and a l t e r n a t e miss i o n s t u d i e s
The r e q u i r e d c a p a b i l i t y i s a
complete six-degrees-of-freedom t r a j e c t o r y w i t h closed-loop guidance,
closed-loop p r o p e l l a n t u t i l i z a t i o n and p r o p u l s i o n system, and c l o s e d loop c o n t r o l f i l t e r s ; each c a p a b i l i t y must handle a b o r t and a l t e r n a t e
m i s s i o n f a i l u r e s . The s t a t u s of t h e v a r i o u s c a p a b i l i t i e s of t h e d e s i r e d
program is a s f o l l o w s :
.
A complete s i x ( a ) Complete Six-Degrees-of-Freedom:
degrees-of-freedom t r a j e c t o r y generated from guidance r e f e r e n c e r e l e a s e
through a l l powered f l i g h t and o r b i t a l f l i g h t has been s u c c e s s f u l l y
implemented i n t h e SAM-V deck. The p r e s e n t method of c o n t r o l l i n g t h e
S a t u r n v e h i c l e by g e n e r a t i n g a t t i t u d e e r r o r s i g n a l s permits a p o i n t of
d i s c o n t i n u i t y d u r i n g a complete 360" o r b i t a l r e v o l u t i o n of t h e v e h i c l e
when t h e s i g n a l s may be e r r o n e o u s l y l a r g e . A new method which s u p p r e s s e s
t h i s e r r o r has been devised and checked o u t i n a l l o r b i t a l phases of
flight.
(b) Closed-Loop Guidance: The I t e r a t i v e Guidance
Scheme a s implemented i n t h e onboard S a t u r n V guidance computer has
been i n c o r p o r a t e d i n t o t h e SAAM-V program i n closed loop from guidance
r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which
s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , a c c e l e r o m e t e r
p r o c e s s i n g , minor loop s u p p o r t , and which c a l c u l a t e t h e o u t - o f - o r b i t
t e r m i n a l c o n d i t i o n s have been prepared f o r programming and l i n k i n g i n t o
t h e deck.
( c ) Closed-Loop Control F i l t e r : The complete closedloop c o n t r o l f i l t e r system of t h e S a t u r n V has been s u c c e s s f u l l y i n c o r porated i n t o t h e SAAM-V program and has been checked o u t .
�(d) Closed-Loop P r o p e l l a n t U t i l i z a t i o n P r o p u l s i o n
Sys tem: C o n t r a c t NAS8-21160 was l e t t o Operations Research I n c o r p o r a t e d
(ORI) on June 30, 1967 t o provide R-AERO-F w i t h c a p a b i l i t y t o g e n e r a t e
closed-loop p r o p u l s i o n performance. This c a p a b i l i t y was provided, b u t
new in-house r e f i n e m e n t s a r e underway t o enhance t h e c a p a b i l i t y of t h e
P r o p u l s i o n S i m u l a t i o n Module (PSM). Three of t h e s e r e f i n e m e n t s a r e :
-
(1)
Control F i l t e r s
The c o n t r o l f i l t e r s can
now be used i n c o n j u n c t i o n w i t h t h e PSM.
C e r t a i n o t h e r modules were s t r e a m l i n e d
i n o r d e r t o provide t h e machine c o r e s t o r a g e
r e q u i r e d by t h e c o n t r o l f i l t e r s .
(2)
Mass D i s c o n t i n u i t i e s
The c e n t e r of g r a v i t y ,
moment of i n e r t i a and mass r o u t i n e s have been
modified t o account f o r d i s c r e t e n a s s l o s s e s
(such a s tower j e t t i s o n , e t c . ) . These mass
d i s c o n t i n u i t i e s caused d i s c o n t i n u i t i e s i n
t h e c e n t e r of g r a v i t y and moments of i n e r t i a
which a r e now being handled p r o p e r l y .
(3)
P r e s s u r i z a t i o n Tables
The i n p u t t a b l e s f o r
u l l a g e p r e s s u r i z a t i o n , e t c . , which were i n p u t
a s a f u n c t i o n of s t a g e time a r e now being
i n p u t a s a f u n c t i o n of mass dumped overboard,
This i s more r e a l i s t i c f o r d i s p e r s i o n c a s e s
and should s u f f i c e i n handling p r e s s u r i z a t i o n
i n p u t s f o r off-nominal c a s e s .
-
-
There i s one remaining major r e f i n e m e n t f o r u s e
of t h e PSM:
t h e S-IVB p r o p e l l a n t u n t i l i z a t i o n s i m u l a t i o n r o u t i n e . P&VE
t e l l s us t h a t t h e s i m u l a t i o n we a r e now u s i n g i s n o t t h e most c u r r e n t
s i m u l a t i o n . Means of o b t a i n i n g t h e l a t e s t PU model used by P&VE a r e
b e i n g i n v e s t i g a t e d . I n a d d i t i o n , t h e r e i s t h e t a s k of t r a n s f e r r i n g t h e
PSM from t h e o r i g i n a l 6-D program i n which i t was implemented i n t o t h e
c u r r e n t SAAM-V 6-D program.
Lif t o f f Analysis
MSC has informed us t h a t t h e launch r e l e a s e s u r f a c e wind
l i m i t f o r t h e AS-502 launch w i l l be 27 knots (peak) f o r winds from 150
t o 210 degrees azimuth and 31 k n o t s (peak) from a l l o t h e r azimuths. This
i s due t o s p a c e c r a f t s t r u c t u r a l c o n s i d e r a t i o n s . This launch r e l e a s e wind
l i m i t i s more r e s t r i c t i v e than t h e l i m i t s imposed on t h e b o o s t v e h i c l e
duc t o t h e maintenance of adequate l i f t o f f c l e a r a n c e s .
�The p r e d i c t e d AS-502 s o f t r e l e a s e rod c h a r a c t e r i s t i c s w i l l
be t h e same a s t h o s e used f o r AS-501 p r e d i c t e d l i f t o f f motion s t u d i e s .
F l i g h t evaluation r e s u l t s indicated higher-than-predicted r e l e a s e forces
e x i s t e d on t h e AS-501 f l i g h t . This r e s u l t was a t t r i b u t e d t o t h e rods
being improperly l u b r i c a t e d . P&VE s t a t e s t h a t t h e AS-502 s o f t - r e l e a s e
mechanisms w i l l be more e f f e c t i v e l y greased t h a n t h e ones on AS-501.
The
s o f t - r e l e a s e mechanisms on AS-502 a r e t o be s u f f i c i e n t l y instrumented t o
more a c c u r a t e l y d e f i n e t h e rod f o r c e s because t h e i n s t r u m e n t a t i o n on t h e
AS-501 launch was inadequate. AS-502 r e s t r a i n i n g f o r c e s w i l l be t h r e e f o u r t h s of t h e p r e d i c t e d AS-501 r e s t r a i n i n g f o r c e because 12 s o f t - r e l e a s e
rods were used i n s t e a d of 16. The e f f e c t of t h i s change i s a n i n c r e a s e d
l i f t o f f a c c e l e r a t i o n and t h e r e f o r e g r e a t e r v e h i c l e / l a u n c h s u p p o r t equipment c l e a r a n c e s .
Camera coverage f o r AS-502 l i f t o f f motion w i l l be essent i a l l y t h e same a s AS-501.
Because of t h e removal of t h e a i r scoops,
t h e camera o r i g i n a l l y s e t up t o view them has been r o t a t e d t o view t h e
shroud of engine #1. The a d d i t i o n a l l i f t o f f t a r g e t camera r e q u e s t e d f o r
AS-502 was n o t approved by t h e KSC c o n t r o l board. A r e q u e s t was a l s o
made f o r r e l o c a t i n g t h e holddown arm cameras f o r AS-502, because t h e i r
view d u r i n g AS-501 launch was p a r t i a l l y obscured by t h e r e t r a c t a b l e
cover on t h e holddown arms. This r e q u e s t was a l s o r e j e c t e d by KSC.
(1)
BP-30 Wind L i m i t s
The i n f l i g h t wind speed l i m i t s f o r t h e AS-503 BP a t
t h e most c r i t i c a l a l t i t u d e (10 km) a r e 7 9 m/sec, 56 m/sec, and 62 m/sec
f o r t a i l - w i n d , cross-wind and head-wind, r e s p e c t i v e l y . Wind r e s t r i c t i o n s
of t h i s magnitude r e s u l t i n a v e r y low p r o b a b i l i t y of launch d e l a y due
t o in£ 1i g h t winds.
(2)
BP-30 Abort and A l t e r n a t e Mission A n a l y s i s
The AS-503 (BP-30) a n a l y s i s was completed by TBC and
d e l i v e r e d on t h e r e q u i r e d d a t e . The document i s r e a d y f o r d i s t r i b u t i o n
and a cover memo i s being prepared. The a n a l y s i s p o i n t e d o u t t h a t t h e
f r e e f a l l l i m i t l i n e , contained i n t h e AS-501 s p a c e c r a f t a b o r t and a l t e r n a t e m i s s i o n r e p o r t , would be v i o l a t e d i f t h e S-IC had a s i n g l e engine
t o f a i l a t c e r t a i n times. The following i s a summary of t h e m i s s i o n
completion c a p a b i l i t y which e x i s t s f o l l o w i n g e i t h e r a n S-IC s i n g l e
engine shutdown, a n S - I 1 s i n g l e engine shutdown, o r e a r l y S-111s-IVB
staging (direct).
�(a)
S-IC Single-Engine Shutdown
Performance c a p a b i l i t y t o a c h i e v e ' p a r k i n g o r b i t
i n s e r t i o n f o r a n S-IC s i n g l e - e n g i n e shutdown e x i s t s f o r a l l times.
L i f t o f f i n t e r f e r e n c e i s encountered f o r S-IC s i n g l e - e n g i n e shutdowns
b e f o r e 5 seconds. For a p e r i o d of a b o u t 10 seconds i n t h e maximum
dynamic p r e s s u r e r e g i o n , l o s s of c o n t r o l is p o s s i b l e f o r c e r t a i n wind/
engine shutdown combinations. Loss of c o n t r o l i s more l i k e l y f o r a n
upper-engine shutdown. The primary m i s s i o n , t r a n s l u n a r - o r b i t i n j e c t i o n ,
can be achieved f o r a l l S-IC s i n g l e - e n g i n e shutdown times a f t e r 125
seconds f o r a lower-engine shutdown, and a f t e r 105 seconds f o r a n upperengine shutdown. The r e q u i r e d p r o p e l l a n t r e s e r v e a t i n j e c t i o n i s maint a i n e d f o r t h i s s t a t e d c a p a b i l i t y . The S-IVB r e s t a r t l i m i t is s a t i s f i e d
f o r S-IC lower-engine shutdowns a f t e r 95 seconds and f o r upper-engine
shutdowns a f t e r 65 seconds.
(b)
S - I 1 Single-Engine Shutdown
Parking o r b i t i n s e r t i o n and S-IVB r e s t a r t c a p a b i l i t y e x i s t f o r a l l S - I 1 s i n g l e - e n g i n e shutdowns. Lower o r upper S - I 1
s i n g l e - e n g i n e shutdowns a f t e r 85 seconds a c h i e v e t r a n s l u n a r o r b i t
injection.
(c)
S-111s-IVB
Direct Staging
A l l S - I 1 p r o p u l s i o n m a l f u n c t i o n shutdowns, followed
by a n S-111s-IVB
d i r e c t s t a g i n g b e f o r e 190 seconds from S - I 1 i g n i t i o n ,
f a i l t o a c h i e v e i n s e r t i o n and r e s u l t i n s u b o r b i t a l l o b s o r e c c e n t r i c
o r b i t s , or f a i l t o achieve i n s e r t i o n with required propellant reserves.
A l l l a t e r d i r e c t s t a g i n g s a c h i e v e parking o r b i t . S-IVB r e s t a r t c a p a b i l i t y e x i s t s f o r d i r e c t i n g s t a g i n g s a f t e r 350 seconds. Primary m i s s i o n
c a p a b i l i t y e x i s t s f o r d i r e c t s t a g i n g a f t e r 360 seconds. A d i r e c t s t a g ing o c c u r r i n g b e f o r e S - I 1 i g n i t i o n plus 120 seconds r e s u l t s i n a n
A t l a n t i c Ocean impact of t h e S-IVB. Land impacts i n t h e Canary I s l a n d s
o r on t h e A f r i c a n Continent occur f o r d i r e c t s t a g i n g s from 120 t o 190
scconds. Malfunction time, g e o c e n t r i c r a d i u s , i n e r t i a l v e l o c i t y , and
i n c r t i a l p a t h a n g l e a t t h e time of ground-command i n t e r r u p t were d e t e r mined f o r maximum, minimum, and r e f e r e n c e performance.
(3)
Mission D Abort and A l t e r n a t e Mission A n a l y s i s
Most of t h e d a t a r e q u i r e d by TBC t o make t h e a n a l y s i s
has been s u p p l i e d . Four items t o be f u r n i s h e d a r e :
(a)
Mission d e s c r i p t i o n documentation.
(b)
S p a c e c r a f t v e l o c i t y and p a t h a n g l e l i m i t s v e r s u s
time r e q u i r e d t o determine v i o l a t i o n of f r e e f a l l
1i m i t s
.
�(c)
Mass c h a r a c t e r i s t i c s f o r t h e m a l f u n c t i o n case
where t h e launch escape tower f a i l s t o j e t t i s o n .
(d)
Mass c h a r a c t e r i s t i c s f o r the m a l f u n c t i o n case
where 2nd plane s e p a r a t i o n f a i l s t o occur.
Meetings have been h e l d w i t h M r . F. McDonald and
B. Hughes, TBC, concerning t h e ground r u l e s f o r t h e a n a l y s i s . Two
problem a r e a s a r e p r e s e n t l y d e l a y i n g t h e ground r u l e s . One a r e a i s
t h e s i m u l a t i o n of dual engine f a i l u r e s f o r S-IC and S - I 1 s t a g e s , and
t h e o t h e r i s t h e d e t e r m i n a t i o n of e f f e c t s of t h e a c c e l e r o m e t e r f a i l u r e s , overs peed and underspeed i n t o t h e v a r i o u s o r b i t s £011 n ~ i n n
parking o r b i t .
BIBLIOGRAPHY
1.
Purdy, K. W . , "An A c o u s t i c J e t f o r E v a l u a t i o n of Laser Doppler
V e l o c i t y I n s t r u m e n t , " IN-AERO-68-1, March 19, 1968, U n c l a s s i f i e d .
2.
Astrodynamics and Guidance Theory D i v i s i o n , "Astrodynamics,
Guidance, and Control Review $/1," TM X-53709, Feb. 21, 1968.
3.
Aerophys i c s D i v i s i o n , "Special i s t Conference on Molecular R a d i a t i o n
TM X-53711,
and I t s A p p l i c a t i o n t o D i a g n o s t i c Techniques,"
Feb. 23, 1968.
4.
Funk, B. H . , "A Simple Explanation of the Fundamental P r i n c i p l e of
Cross Beam Remote Sensing," TM X-53712, Feb. 28, 1968.
5.
Tomlin, D . , J r . , " O n e - ~ i m e n s i o n a l Wave Motion i n P r i s m a t i c Bars due
t o Impulse Loads w i t h and Without Coulomb Damping," TM X-53714,
March 1, 1968.
6.
Gwin, Hal S . , "Impulse Base Flow F a c i l i t y Technical Handbook,"
TM X-53716, March 1 3 , 1968.
�APPROVAL
/zg.r , Aero-As t r o d y n a m i c s L a b o r a t o r y
E . D. G e i s s l e r
D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y
DISTRIBUTION
R-AERO-DIR
Dr. G e i s s l e r
M r . Jean
Mr. B u t l e r
PAO, Mr. K u r t z
R-DIR, M r . W e i d n e r
MS-H, M i s s J e r r e l l (3)
R-AERO-R
M r . B e a n (4)
Mrs. Hightower
R-AERO- T
Mr. M u r p h r e e
Mr. Cummings
Dr. Heybey
Mr. Jandebeur
Dr. K r a u s e
Mr. N a t h a n
M r . Few
M r . von P u t t k a m e r
R-AERO-P
R-AERO-D
R-AERO-A
R-AERO-G
R-AERO-Y
R-AERO-F
R-AERO-X
(8)
(16)
(16)
(6)
(8)
(8)
(4)
I-V-P,
Mr. P r i c e
�
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Saturn V Collection
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Saturn V Collection
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000040
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: February - March 1968."
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George C. Marshall Space Flight Center
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1968-04-01
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1960-1969
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Saturn Project (U.S.)
NASA space programs
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Saturn V Collection
Box 26, Folder 12
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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http://libarchstor2.uah.edu/digitalcollections/files/original/20/988/spc_stnv_000041.pdf
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Text
AERO-ASTRODYNAMICS W O R A T O R Y
BTMONTRLY PROGRESS REPORT
t.
r\
February and March 1 9 6 7
:
INDEX
3
I
.
TECHNICAL AND SCIENTIFIC STAFF
.
III .
TI
IV
.
V,
VI.
.
ADVANCED STUDIES OFFICE
.........................
................................
........................................
AEROSPACE ENVLRO'NMENT DIVISION .........................
AEROPHYSICS D I V I S I O N ...... .............................
A . F l u i d Mechanics Research Office ....................
B . Mechanical Design O f f i c e ................a.m.........
C . Aerodynamic Design Branch .............. .
.
.
........
D . Experimental Aerophysics Branch ....................
E . Thermal Environment Branch .........................
F . Unsteady Aerodynamics Branch .......................
ASTRODYMHICSANDGULDANCE ~ O R Y D I V I S Z O .............
N
A . S c i e n t i f i c A d v i s o r y O f f i c e ..................*......
B . O p t i m i z a t i o n Theory Branch .........................
C . Astrodynamics Branch. ..............................
D . Guidance Theory Branch.. ...........................
PROJECTS OFFICE
.................
......................................
.....
..........................................
.............
. ................................................
VIII. PLIGHT TEST AWLYSIS DIVISION ..........................
A . S p e c i a l P r o j e c t s Office ............................
3 . Tracking and O r b i t a l A n a l y s i s Branch. ..............
C . F l i g h t Evaluarion Branch ............. ..............
l3 . F l i g h t Mechanics Branch .............................
BIBLIOGRAPHY ..................................................
VII
D~ICSANDFLIGHTMECHANLCSDIVISION
A
Multi-Projects
B
Saturn V
C
Saturn I B
D
AAP
E
General Methods
Dynamics and Control
.
..
.
.................................
1
2
5
7
12
12
13
14
20
26
30
34
34
36
39
41
44
44
4L
47
47
51
52
52
53
56
60
63
�AERO-ASTRODYWYTCS LABORATORY
BIMONTHLY PROGRESS REPORT
I,
TECmICAEAND
1.
S C I E N T I F I C STAFF
Dynamics of Cable-Connected S p a c e S t a t i o n s
An analytical method has b e e n developed f o r the dynamic
problems of t w o i d e n t i c a l cable-connected space s t a t i o n s which are
r o t a t i n g about a n a x i s p e r p e n d i c u l a r L O t h e i r orbital p l a n e in f r e e
flight. 'Fne connec Ling cable i s t r e a t e d as an elas t i c beam w i t h t r a n s verse v i b r a t o r y m o t i o n s b o t h in and out of t h e p l a n e of r o t a t i o n . Thf
nonhomogeneous boundary conditions d u e ta t h e roll, pitch, and yaw
motions of the space s t a t i o n s a r e r c s o l v e d by ustng fictitious concentrated-masses concept. This a p p r o a c h o f f e r s a more accurate r e p r c s e n t a tion of the s y s tern than that g i v e n by the lumped-masses t r a n s £ex matrix
method.
T h i s a n a l y s i s can be e x t e n d e d e a s i l y f o r a nonsyrrtmetric s y s t e m .
(Liu)
2.
ODYSSEY
Experiment concepts and p r e l irninary s t u d y r e s u l ts p e r t a i n i n g
to the Odyssey configuration, m i s s i o n p l a n s , and s u b s y s t e m requirements
a r e b e i n g i n v e s t i g a t e d a s part of Ehe p r o j e c t d e f i n i t i o n s t u d y .
Specifically, c u r r e n t s t u d i e s a r e i n v e s t i g a t i n g t h e passive s p h e r e s , r e q u i r e d
o r b i t a l a l t i t u d e s , and r e s u l t i n g s p h e r e s e p a r a t i o n d i s t a n c e s f o r varying
o r b i t a l lifetimes. A reference m i s s i o n p l a n ( n o t to b e confused with
t h e a c t u a l mission p l a n which requires a l a u n c h d a t e ) has been o u t l i n e d
which serves as a tool f o r data a c q u i s i t i o n times, command sequences,
a n d b u s subs ys t e m requircrnenEs s u c h as g u i d a n c c a n d c o n t r o l a c c u r a c i e s ,
t r a n s m i t t e r and r e c e i v e r p o w e r , and r e c o r d e r capacities. A preliminary
perturbation a n a l y s i s of the g u i d a n c e e r r o r s h a s been completed. The
r e s u l t s i n d i c a t e t h a t e x t r e m e a c c u r a c i e s a r e not required, a n d e r r o r s
of two d e g r e e s in a t t i t u d e d u r i n g t h r u s t i n g p e r i o d s will be a l l o w a b l e
to m e e t orbit change accuracy requirements. P r e l i m i n a r y s t u d i c s t h u s
f a r i n d i c a t e a preference f o r the C - l e n g i n e over the TRW a n d R - 4 ~
e n g i n e s as p r o p u l s i o n r c q u i r e m c n t s f o r t h e b u s .
Tankage of t h e Saturn V/
S-IVB APS p r o v i d e s capacities r e q u i r e d for f u e l a n d o x i d i z e r . P r o p e l l a n t c a p a c i t y , i n c l u d i n g b a t h t a n k s , i s a b o u t 660 pounds which i s a d e q u a t e f o r Odyssey f i r s t - c u t r e q u i r e m e n t s o f about 5 6 0 pounds. C o n t i n u e d
i n v e s t i g a t i o n into the pos s ibSe l o c a r ion aboard a l a u n c h vehicle has
confirmed t h e i n a d e q u a c y of i n t e r n a l s p a c e . Fur themore, t h e uprared
S a t u r n IB v e h i c l e s considered as p o s s i b l e c a n d i d a t e s a r e m a r g i n a l in
r e g a r d to p a y l o a d capacity. F u r t h e r a n a l y s i s of the externaLly m a u n t c d
pod approach appears as the most p r o m i s i n g c o n f i g u r a t i o n .
Mass a n d
moment of i n e r t i a da L a for t h e bus c o n f i g u r a t i o n have been g e n e r a t e d anc:
�u s e d i n prelimfnary a t t i t g d e c o n t r o l system s t u d i e s .
Seme l a y o u t s of
the S - I V E a f t skirt s u p p o r t i n g s t r u c t u r e w e r e made to aid in determining
pod s u p p o r t r e q u i r e m e n t s . Aerodynamic e f f e c r s r e l a t e d LO this c o n f i g u r a tian a r e a l s o under study by R-AERO-A.
Both steady a n d unsteady pod
l o a d s a r e S e i n g i n v e s t i g a t e d as well as t h e overall e f f e c t s on v e h i c l e
aerodynamic c h a r a c t e r is tics due to the e x t e r n e l l y mounted pod s t r u c t u r e .
IFevr]
TI.
ADVAXCED STUDIES OFFICE
A.
F l i g h t Flechanics and Performance
An i n v e s t i g a t i o n of the T i t a n 111-C performance capability has
been p u b l i s h e d in m e m o r a n d m R-AERO-X-67-45.
Much e f f o r t has been d e v o t e d te g e n e r a t i n g performance d a t a of
the S a t u r n V (516) launch v e h i c l e ( u s L ~ g3-2 and J-2s p r o p u l s i o n ) .
The
a n a l y s i s a l s o compares the P r o d u c t Improved S a t u r n V.
The study considers three different m i s s i o n p r o f i l e s : 100 N. mi. c i r c u l a r , 100 x
263.5 e l l i p s e , and a 72-hour lunar transfer. The exercise lus been in
s u p p o r t of che Planetary JAG, When u p r a t e d F-L analysis with ?"nsust
t a i l o r i n g has been completed, the r e s u l t s w i l l be documented.
An investigation of the performance c a p a b i l i t y of the S a t u r n
vehicle (516) to high energy (C3 km2/sec2) type m i s s ions has been
i n i t i a t e d . The f l i g h t geometry reserves have been r e c a l c u l a t e d far
these p r o f i l e s and r e s u l t s are expected in about t w o weeks.
T h e f i n a l phase of t h e 3-burn S-IVB s t u d y (S-ZVB in lunar o r b i t )
has been c o m p l e t e d , i n d i c a t i n g the capability of p u r t i n g approximately
103,000 I b s ( i n c l u d i n g the S-IVB s t a g e ) in a 100 N. mi. circular Puner
o r b i t u s i n g 5-25 propulsion. The f i n a l report i s b e i n g documented.
A performance analysis of (two-burn) S - I n i n s e r t i o n i n t o a
6,000 N. mi. e q u a t o r i a l o r b i t has been published in memorandum R-AERO-X47 -37.
A memorandum e n t i t l e d ' ' P e r f o ~ n c eand T r a j e c t o r y Daca f o r t h e
S a t u r n 5P.- 217 Vehicle" has been d i s t r i b u t e d . This memorandum, R-AEROX-67-14, which is in response to R-P&m-AV-66-246, shows a comparison of
:he 5-25 and s t a n d a r d 5-2.
A s requested by DMSF, the performance c h a r a c t e r i s t i c s of t h e
u p r a t e d Saturn v e h i c l e s have been u p d a t e d f o r t h e H z a d q u a r t e r s
Prospectus.
�B.
Syscems Analysis Group
l.
Spent Stage U t i l i z a t i o n
An orientation m e e t i n g w i t h DAC on t h e spent S - I n u t i l i z a t i o n study was h e l d a t MSFC onMarch 8 - 9 .
The majority of t h c f i r s t
d a y was ~ a k e nup w i t h presentations by MSFC personnel on t h e status of
Workshop #1, o b j e c t i v e s and s c h e d u l e s of the p r e s e n t study e f f o r t , and
a transmf t t a l of technical data to DAC. Mr. Wood of t h i s off i c e p r e s e n t e d the f Light performance d a t a to be used d u r i n g the study. The
remainder of the time was used by DAC to present their s t u d y organization, clarify questions r a i s e d previously a b o u t certain k e y p c o p l c
a s s i g n e d to the s t u d y , and the t e c h n i c a l approach to be used.
M r . Verderaime of R-MRO-D and M r . Josh Johnson of R-AERO-A
were invited t o attend the orientation. DAC personnel expressed a great
i n t e r e s t Pn the orbital aerodynamic work b e i n g done by AERO and i n d i c a t e d
khey w o u l d c o n t a c t M r . Johnson on t h i s matter in t h c near f u t u r e .
2.
IU Xodif i c a t i e n
A p r o p o s a l from IBM in response to a s o l e source RFQ from
AS0 for s t u d y i n g requtred modifications to the As tr ionics sys terns t o be
u s e d w i t h the u p r a t e d S a t u r n launch vehicles has bccn evaluated. The
s c o p e of the proposal was w i t h i n the available resources of $225,000 for
the s t u d y . A technical pre-negotiation s e s s i o n was h e l d on February 10,
1967, attended by the c o n t r a c t i n g o f f i c e r , representatives of A S 0 and
the coLlocated off ices, and representatives of IBM to i n s u r e u n d e r s t a n d ing of the level of t e c h n i c a l d e p t h expected and the approach to be
Laken.
Tile l u n d s available f o r the s t u d y must be c o n t r a c t u a l l y committed
by A p r i l 15, 1967.
3.
S a t u r n I 3 Improvement
The proposal f r o m CCSD f o r a Phase 111 s t u d y of fur thes
u p r a t i n g the S a t u r n I l a u n c h vehicle wa6 of 9 scope more t h a n twice the
a v a i l a b l e r e s o u r c e s of $125,000. An i n f o r m a l pre-negotiation session
was held a t MSFC on March 2 , 1 9 6 7 , at which CCSD p r e s e n s e d a d e t a i l e d
b r e a k - o u t of the man-hours involved on a task- to-task bas is and t h e i r
recommendations on ways i n which the scope of work c o u l d be r e d u c e d
w i t h o u t compromising rhe d e s i r e d r e s u l t s . The scope of work still was
somewhat t o o l a r g e , and CCSD was instructed to come back w i t h a r e d u c e d
proposal b y the following week, s i n c e this money nus t a l s o b e c o m i t t c d
by A p r i l 15, 1967.
�4.
S a t u r n V Improvement S t u d i e s
a.
Launch F a c i l i r y Test
T h e Tes t L a b o r a t o r y is checking o u t t h e i r f a c k l i t f e s
modc-1, u s i n g n Saturn V model, The s o l i d propellant f o s t h e u p r a t e d
cnnf t g u r a r Ton is on o r d e r from UTC.
b.
Base Beating Tes t
The base he&ting t e s t s nr Cornel I A e r o n a u t i c a l Laborat n r s l u v e r u n i n t o d i f f i c u l t y in model f a b r i c a t i o n . This w i l l delay the
t e s t s t a r t i n g d a t e u n t i l September.
The solid p r o p e l l a n t for rhe GAL
t e s t s is b e i n g o r d e r e d with t h e group for R-TEST from UTC.
C,
As trodyaamics &
Miss i n n Analysis Group
I. Manned Planetary Flyby Missions
B a s e d on ~ a r u r n / ~ ~ c l l l o
Sys tern
T h i s twelve-month s t u d y c o n t r a c t w i t h North American Aviat i o n is c u r r e n t 1 y approaching the three-quarter comp Le t i o n mark.
The
t h i r d - q u a r t e y - r e v i e w of t h i s s t u d y c o n t r a c t w i l l be h e l d at MSFC approximately May 1, 1967. The particulars of rhe meeting will be announced
as they become f i r i a 1 i z t . d .
2.
NASA In-House P l a n e t a r y J o i n t A c t i o n Group (JAG)
The r e s u l t s of t h i s s t u d y a r e being documented. The i n p u t s
of R-AERO-X are t a be submitted to R-AS0 on A p r i l 1 4 , 1967. AS0 has t17t
respoils i b i 1i ~ Lor
y
coord i n a ting the MSFC e f f o r t s .
R-AERO-X w a s res pous ibl e f o r launch sequence and timelines, as c e n t p r o f i l e s and e a r t h 1 nunch
vehicle p e r f e m a c e , i n t e r p l a n e t a r y i n j e c t i o n r e q u i r e m e n t s , and bascline
m i s s i o n definition. It is expected t h a t the planatary JAG will cantinup
for s e v e r a l months y e t , bur. at t h i s t i m e it is not clear what goals w i l l
b e p u r s u e d or a t w h a t p a c e .
3,
Con t r a c t o r s
O p t i m u m r e e n t r y a n a l y s i s u s i n g the s t e e p e s t a s c e n t
o p t i m i z r i t i u n teclin i q u e has b e e n c ~ l p l ted
r
and d o c u m e n t e d in Xor ~ h r o p
r e p o r t TM-792-7-143 March 1 9 6 7 . The report p r e s e n t s t h e s t e e p e s t a s c e n t
m e t h o d d e v ~ l c p e dby B r y s o n and Denham for s o l v i n g o p t i m a l p r o g r a m i n g
problems v i t h s t a t e v a r i a b l e i n e q u a l i t y c o n s t r a i n t s .
�A s t u d y 05 impulsive v e l o c i t y requirement: far a b o r t i n g
a planned Mars stopover mission i n t o a powered Mars f l y b y m i s s i o n has
been completed, The a n a l y s i s considered direct f l i g h t p r o f i l e s to Mars
and return, a n d p r o f ilcs which i n c l u d c d t h c Vcnus s w i n g b y mode. This
s t u d y has been documented in Lockheed R e p o r t TM 54130-130 LMSC/HREC,
F e b r u a r y 1967.
4.
Analytical Launch Window Program
An analytical digital computer program model d e s i g n e d to
c a l c u l a t e o r b i t a l launch window requirements for interplanetary m i s s i o n
has been d e v e l o p e d , programmed and checked o u t . E x c e l l e n t a g r e e m e n t of
r e s u l t s has been demonstrated between a calculus of v a r i a t i a n trajectory
program and the analytical program. Parametric a n a l y s i s f o r selected
Venus and Mars m i s s ion is underway.
111.
PROJECTS OFFICE
1.
F l i g h t Limits Sub-panel
T h e seventh F l i g h t Limits Sub-panel meeting was held a t MSFC
on F e b r u a r y 14, 1 9 6 7 . During the meeting MSFC p r e s e n t e d the Saturn V
EDS status and the planned a c t i v i t i e s toward d e f i n i n g r e q u i r e m e n t for
the launch vehicle a n d spacecraft to a t t a i n an a c c e p t a b l e emergency
d e t e c t i o n s y s t e m . The r e s u l t s of the meeting a r e documented in
memorandum R-AERO-P-82-67, d a t e d F e b r u a r y 23, 1967.
2.
Range S a f e t y Sui-Panel
The seventh Range S a f e t y Sub-Panel meeting w a s h e l d a t KSC on
Elarch 15, 1967.
The Eastern Test: Range (ETR) was b r i e f e d on the
S a t u r n I B rendezvous m i s s i o n and the S a t u r n V lunax l a n d i n g m i s s ion,
ETR p r e s c n t c d t h c i r u s e o f the NASA Range S a f e t y data. This r e s u l t s
in a b e t t e r u n d e r s t a n d i n g of the use/requirernent f o r data. The minutes
of the meeting are b e i n g documented.
3.
G u i d a n c e and Performance Sub-panel Meeting
The Twenty-Fif th Guidance and Performance Sub-Pane 1 mee r i n g
was h e l d a t MSC on March 2 2 , 1 9 6 7 . The e m p h a s i s was on adjusting the
m i s s i o n p l a n n i n g and o r b i t a l a t t i t u d e maneuver and v e n t i n g timelines to
the S a t u r n I3 mission changes. Other t o p i c s included the c o o r d i n a t e
reference systems f o r gimbal a n g l e data t r a n s f e r s , a s t a t u s r e p o r t on
the AS-503 ?ropellant r e s i d u a l s problem, and some r e s u l t s of AS-503 two
i n j e c t i o n simulations. The r e s u l t s o f the meeting are b e i n g d o c r ~ m ~ n t e d .
�4.
S a t u r n IB Piissiwn Change
Direction has been received t o implement the AS-204/LY-1m i s q i o n f r m l a u n c h complex 37B. AS-205, though n o t f i n n e d up on a11
d r t a i l s , w i l l c a r r y a CSM p a y l o a d . AS-206 w i l l c a r r y a LM payload and
AS-207 a CSY; this w i l l be a d u a l m i s s i o n .
P r i m a r y crnphasis is being
p l a c e d on accomplishment of the work f o r A S - 2 0 4 .
The CCSD systems
s u p p o r t e f f o r t s a r e be ing realigned f o r t h e above m i s s i o n c h a n g e s .
5.
S a t u r n IB Program Review
An Aero-Astrodynamics Laboratory S a t u r n IB Program RevLew was
h e l d on February 2 0 , 1967. The follo17ing t o p i c s w e r e covered: (1)
m i s s i o n description, ( 2 ) s t a t u s of mission planning for Apol.10 and M P ,
and ( 3 ) s p e c i a l problems,
E f f o r t s have been e x p e n d e d on the e f f e c t of various Locat i o n s of t h e o r b i t a l Workshop (OWS) solar a r r a y on the S-IVB. Tile
p r e s e n t baseline conf i g u r a r i o n for the OWS has a solar array arrangement extended from the a l r l o c k module (AM).
This con£ i g u r a t i o n is
e x p e c t e d to change in the near future to a c o n d u i t arrangement along
rhe S-IVB. A c t i v i t y has a l s o involved c o n s i d e r a t i o n of an a c t i v e cont r o l s y s t e m f o r the OWS to extend the s t a b i l i z a t i o n beyond the i n i t i a l
7 I/2 h o u r s a n d f o r reuse.
E f f o r t s have been expended on the o p t i m i z a t i o n of payload
for the AAP-3/4 f l i g h t s . However, f i n a l i n s e r t i o n a l t i t u d e for the
U P - 4 EL i g h t cannot b e determined u n t i l a f t e r the MSC-MSFC M i s s i o n
Requirements Panel has worked the task j o i n t l y .
C o n s i d e r a t i o n has
been g i v e n to t"n empact: o f a 3 - f o o t s l i c e between the IU a n d SLR to
allow more room f o r rhe ATM telescape-hydrogen tank clearance and r o
allow lowering t h e A m package r e l a t i v e to the ATM rack for b e t t e r
as r r o n a u t a c c e s s a n d f i l m recovery.
7.
1967.
S a t u r n V Speech
M r . Ttnius s p o k e to the Tuscaloosa Kiwanis C l u b on February 53,
The speech was e n t i t l e d , " S a t u r n V Program and ALabam."
�8.
AERO S/ C na ta Book
D i s t r i b u t i o n has been c o m p l e t e d on Revision 5 to the Internal
Aero-Astrodynanics Laboratory S / C Data Book ( W B ) . This reviscon
c o n s i s t e d principally of an u p d a t e d G&C section, many S / C system and
s u b s y s t e m illustrations and d e s c r i p t i o n s ( i n c l u d i n g recerll d e t a i l s on
t h e o p e r a t i o n a l systems of t h e crew such as p e r s o n a l e q u i p m e n t , couches,
waste management, survtval equipment, etc.) and d e t a i l s on the S / C s y s tems t h a t a r e t o b e o p e r a t e d by t h e crew (such as docking and e a r t h Pandi n g s y s terns). A t t e m p t s are a l s o being m a d e t o d e c l a s s i f y the data book
s o t h a t it w i l l be more a c c e s s i b l e to R-AERO p e r s o n n e l .
IV.
AEROSPACE ENVIRONMENT D I V I S I O N
1. The FPS- 16 radar/Jimsphere temperature sensor was f 1ight t e s t e d
a t Cape Kennedy, F l o r i d a , d u r i n g the week of February 27 t h r o u g h March 3,
1967.
These tests were conducted by Ms. D e n n i s Canp ol: R-AERO-YE,
c o n t r a c t o r personnel from the GCA C o r p o r a t i o n of B e d f o r d , Mass., a n d
KSC personnel. The f l i g h t tests were partial-lly successful. The major
problems experienced d u r i n g these t e s t s were w i t h the balloon-borne
a n t e n n a a n d with the o u t p u t of power from the balloon-born transmitter.
Work is underway by GCA to correct: these problems. Subsequently, mock-up
f l i g h t r e s t s w i l l be m a d e at the contractor's p l a n L L o a s c e r t a i n t h a t
these problems have been corrected before returning to KSC to c o n d u c t
additional i d e a l i z e d f l i g h t tes ts
'This Jitnsphere temperature task is
b e i n g c o n d u c t e d under the M S F C / ~ S Ac o n t r a c t NAS8-20588.
.
2 . Wind profile d a t a f o r MSFC' s meteorological t o w e r i n t e r £esence
on w i n d s p r o g r a m b e i n g c o l l e c t e d at NP.SAt s 2 5 0 - m meteorological tower
facility a t KSC, F l o r i d a , a r e b e i n g r e c o r d e d on magnetic tape in analog
form and p u t i n t o d i g i t a l f o r m by personnel of MSFC1s Computation Labora-
Lory. The inhouse Baeing contractors a r e to perform the a n a l y s i s and
prepare a f i n a l r e p a r t o n t h i s t o p i c . The final r e s u l t s will i n c l u d e
wind velocity c o r r e c t i o n factors w i t h r e s p e c t to height and wind disection, s p e c t r d l analyses w h l d l w i l l relaLe Llle severiLy of the tower's
i n t e r f e r e n c e , s u g g e s t i o n s on how to r e d u c e t h e t o w e r i n t e r f e r e n c e on
w i n d s , i f a p p r e c i a b l e , etc.
3 . Average and peak hourly wind profile data have been r e c e i v e d
f o r a one-week p e r i o d a s measured in May 1966 an t h e 1600-foot
meteorological tower f a c i l i t y (WKY-TV Tower, Oklahoma C i t y ) o p e r a t e d
by the National Severe Storms Laboratory (NSSL) at Norman, Oklahoma
(NASA contract
government order No. H-92101). Mr. Charles K. H i l l
(R-AERO-YE) has recently been named technical representative on t h i s
program w i t h Mr. John Kaufman (R-AERO-YE) as a s s i s t a n t . The format of
the punched c a r d sample o f data has been checked out by p e r s o n n e l of
-
�MSFC/R-COMP and d c t e r m i n c d t o be a c c e p t a b l e . Recent t e l e p h o n e c m u n i c a t i o n w i t h M r . Leslie D. S a n d e r s , NSSL Project S c i e n t i s t on t h i s c o n t r a c t ,
I n d i c a t e d t h a t additional d a t a of t h i s t y p e w i l l be made available to
R-AERO-YE i n the near f u t u r e b e g i n n i n g w i t h the sample of data f r o m
Play 1966.
This is a u n i q u e source 0 5 data which will p r o v i d e d e t a i l e d
rcind prof i l e clmrac t e s i s tics u s i n g f i x e d anemometers above 500 ft (150 m)
w h i c h i s t h e maximum h e i g h t of NASA'S meteorolcrg-ical tower at: KSC.
4 . An investigation is b e i n g conducred by R-AERO-YE i n t o the
p e s s i h i l i t i e s f o r o b t a i n i n g d a t a on thunderstorms at Cape Kennedy and
7 i ~ a r r i t . t : I s l a n d i n 1967 by means of radar t r a c k s . A memorandum, p r e p a r e d
by Mr. John N. Kaufman, C n i e f , R-AERO-YE, has been d i r e c t e d to M r . G a m i n
Emanuel, I-NO-R at: KSC, r e q u e s t i n g t h i s infarmation for the thunderstorm
season, Flay ~ h r o u g hSeptember. These thunderstorm radar tracks are to
b e u s e d in an e x i s t i n g i n v e s t i g a t i o n of the s t u d y of extreme w i n d s a s s o c i a t e d w i t h such storms, e s p e c i a l l y to study the w i n d p r o f i l e data r e c o r d e d
at NASA's 150-rn meteoraLagical rower f a c i l iry and ar- the various Saturn
Launch p a d s (LC 34, 3 7 , and 39). One p o s s i b l e source of the data is from
the A i r F o r c e , who o p e r a t e a weather d e t e c t i o n radar at PAF'B.
Various
personnel a t KSC have been contacted on t h i s matter, and it i s f e l t t h a t
t h e s e t h u n d e r s torm/radar tracks can be made available.
5. The s t a t u s of data acquired from NASA's 150-m meteorological
tower located at Cape Kennedy, F l o r i d a , is by m o n t h l y periods as fo2lows:
a.
Data R e d u c t i o n
-
(1) December 1965 through August: 1966
Data r e d u c t i o n
by National Weather Records Center in Asheville, N , C., is complece and
a l l m a g n e t i c t a p e s , p r i n t o u t s , and chart records have been r e t u r n e d
to R-AEKO-YIMSFC.
-
(2)
September 1966 through November 1966
Data r e d u c t i o n
by NWRC is near completion and will be s e n t to MSFC s o o n .
13)
December 1966 through February 1 9 6 7
-
Data r e d u c t i o n
by hWRC is in process.
The National Weather Records C e n t e r in Asheville, W. C.,
is r e d u c i n g these data for R-AERO-Y u n d e r government o r d e r can t r a c t
No. H-13207A.
b.
Data Analyses
-
P r i n r o u t s for fre( I ) December 1965 through my 1966
quency d i s t r i b u t i o n s of mean w i n d s p e e d s and temperatures were examined
and bad data p o i n t s s p e c i f i e d by Environmental A p p l i c a t i o n s Branch
personnel.
L i s t i n g s of these bad d a t a were sent to NWRC and the
�Computation Laboratory for correction and/or elimination.
good data f o r t h i s p e r i o d are in p r o c e s s by R-AERO-YE.
Analyses of
-
(2)
June 1966 ~hroughAugust 1966
"'Debugging" f o r t h i s
data p e r i o d is in process. L i s t i n g s of bad data points w i l l b e s e n t
t o NWRC and Compu La Lion Labura Lory for correct i o n a n d / o r e l intimation.
-
(3) December 1965 through November 1966
Numerous
analyses by R-AERO-YE f o r one year of meteoroEogica1 tower data are
i n p r o c e s s as v a l i d d a t a a r e c e r t i f i e d .
R-AERO-YE e f f o r t s to analyze magnetic- tape-recorded w i n d
p r o f i l e data axe progressing s a t i s f a c t o r i l y . This i n c l u d e s the s tat i s t i c a l p r o p e r t i e s of t u r b u l e n c e , auto- and cross-correlations, the
spectrum a £ turbulence, gust c h a r a c t e r i s t i c s , etc. Also, the analyses
of wind profile data in s u p p o r t to t h e SA-5OOF Ground Wind Loads T e s t
conducted in 1966 are c o n t i n u i n g .
6.
During t h i s p e r i o d , 123 rawinsonde f l i g h t s were made at the
Atmospheric Research F a c i l i t y . There were 35 f l i g h t s in support of
Test Laboratoryts Acoustic S t u d i e s . A t o t a l of 44 flights w e r e made i n
s u p p o r t of static tests: 1 5 flights f o r t h e F-1 engine and 29 for the
S-IB t e s t s .
There were 4 f l i g h t s conducted f o r a s p e c i a l f r o n m l s t u d y ,
and 2 flights w i t h dual-tracking data for a s y s t e m s comparison s t u d y
of the GKD equipment.
7.
The 150-m mefeorological tower at: Kennedy Space Center was
i n s t r u m e n t e d for the tower i n t e r f e r e n c e s t u d y . This program c a l l e d
f o r the ins t a l l a t i o n o f another 18-meter tower near the base of the
150-meter tower and add f t f onal wind sens a r v on the tower.
8. The A tmos pher ic Research Facility c o n t i n u e d s u p p o r t i n g Tes r
L a b o r a t o r y by p r o v i d i n g m e t e o r o l o g i c a l data and s e r v i c e to atmospherical
m e a s u r i n g and r e c o r d i n g equipment. These data and s e r v i c e s are u s e d by
Test L a b o r a t o r y f a r acaus tic s t u d i e s and static tests.
9. Renovation of the A c o u s t i c Wind Measuring F a c i l i t y was completed.
The microphone cable had b e e n damaged by personnel working in rhe a r e a ,
or by environmental c a u s e s . The r e c o r d i n g equipment, r e l o c a t e d in b l o c k house No. 21, will be operational f a r the next S a t u r n launch.
Design of a modification kit to modify M-88 Nike rocker motors
This modification makes the M-88 c m p a t i b l e w i t h launch
f a c i l i t i e s a t Kennedy Space Center. These m o t o r s a r e used f o r the NikeTomahawk-Thermos phere Program.
10.
was comple t e d
.
�I I. T h e d e s i g n f o r anemometer mounts and s i g n a l c o n d i t i a n l n g units
was f i n i s h e d ; t h c y will be f a b r i c a t e d and i n s t a l l e d on t h e 400-f o o t tower
a t Range 1.
12.
New c a b l e was installed and is b e i n g checked o u t f o r the Dynamic
h i n d s Facil i t y , which s h o u l d be operational by May 1, 1 9 6 7 .
1 3 , All equipment L t e m s , e x c e p t for the contrnl cryntaT nscillatorn,
o r d e r e d f o r t h c i o n o s p h e r i c gravity wave s t u d y have been received. The
W D C s i t e l o c a t e d near Valhermosa S p r i n g s , Alabama, has been i n s t a l l e d
except: f ~ - rt h e t I ~ r e etowers for t h e d i p o l e antennas.
N e g o t i a t i o n s on
tljc
AVCO proposal a r e b e i n g f i n a l i z e d .
14. S t a t i s t i c a l environmental m o d e l s of s o l a r flare proton events
a r e b e i n g d e r i v e d . Frobabillty values for v a r i o u s mission l e n g t h s are
b e i n g c a l c u l a ~ e dby rwo methods. The f i r s t m e t h o d assumes random d i s t r i b u t i o n of the s o l a r flares throughout the s i x y e a r s of h i g h e s t solar
a c t i v i t y and u s e s a binomial expansion t o d e t e r m i n e associated p r o b a b i l i t y
f o r various mFssion lengths. The second method assumes the d i s t r i b u t i o n
f o u n d in solar cycle 19 f o r various misston lengths, The f i r s t method
p r o v i d e d p r o b a b i l i t y values which c o u l d n o t e a s i l y be fit to a p r o b a b i l - i t y
versus f l u x curve s o t h a t large errors were i n c u r r e d In the s t a t i s t i c a l
models. The second method is now being examined to s e e f f more r e a l i s t i c
p r o b a b i l i t y values can be obtained.
15. The ionosonde located at Cape Kennedy has now been transferred
to t h e I n s t i t u t e for Telecammunications Sciences and Aeronomy (ITSA),
vrlzo has i n f o m l l y agreed t h a t MSFC w i l l get: che Ionosorrde Lor use i11
o u r i o n o s p h e r i c and S a t u r n launch programs. Following our A p r i l 25
scheduLed Nike/Tomahawk thermosphere probe f i r i n g s at Cape Kennedy, the
ionosonde e q u i p m e n t w i l l be packed and s h i p p e d to MSFG, Here, we p l a n
to van-mount the sounder equipment for use on a c t i v e programs at MSFC
a n d at Cape Kennedy. An e q u i p m e n t retrofit to t h i s sounder which will
i n c r e a s e the aquipment range a n d s e n s i t f v i t y has been proposed by ITSA.
?t appears nm t h a t t h i s r e t r o f i t will have to w a i t u n t i l i m e d i a t e
program demands have been met.
1 6 . A p r o p o s a l to m a p t h e S c u r r e n t systems i n t h e ionosphere from
9
a low o r b i t s u b s a t e l l i t e package has been p r o p o s e d by ITSA. A purrhasLng request has been i n i t i a t e d on a Phase A feasibility s t u d y of t h i s
proposal.
The basic c o n c e p t is f o r a s m a l l package to b e r c t r o - f i r e d
from a l a r g e r laboratory t y p e vehicle. The package would c o n t a i n a
s m a l l propulsion system capable 05 augmenting its L i f e t i m e in, say, a
120 km c i r c u l a r o r b i t f a r s e v e r a l o r b i t s .
The package would then measure
t h e g l o b a l S, c u r r e n t system and would provide data f o r areas p r e v i o u s l y
inaccessible:
�1 7 . A program is being s t a r t e d to determine a more realistic ( f o r
d e s i g n c r i t e r i a a n d mission s t u d i e s ) model for o u t e r zone Van Allen
p a r t i c l e s . The d a t a now being used are time-averaged data and do n o t
i n c l u d e the extreme flux-energy s p e c t r a to be encountered. I n this
program we hope to develop extreme model trapped-particle enviranrnents
and t h e i r a s s o c i a t e d p r o b a b i l i t y of encounter,
18. D a t a a r e b e i n g c o m p i l e d f o r use as natural environmental parame t e r d e s i g n s p e c i f i c a t i o n s f o r the Voyager Spacecraft Phase C contract.
It appears that the May 1, 1967 deadline will be met.
19. A revised v e r s i o n of the Lincoln-McNish solar c y c l e prediction
technique has been p~ogrammed and is now available in the P r o d u c t i o n
Group of the Computation Laboratory u n d e r the title "Solar Predictions."
This program should b e used by all personnel r e q u i r i n g p r e d i c t e d values
of the f u t u r e level of solar a c t i v i t y .
20.
Two I n d e p e n d e n t programs, DENSTY SMALL and DENSTY JACCHIA 1964,
a r e also available in t h e Production Group. The DENSTY SMALL routine
should be u s e d f o r a l l o r b i t a l lifetime predict-ion s t u d i e s ; all other
o r b i t a l dynamics analyses should use the DENSTY JACCHIA 1964 r o u t i n e .
21. Prel h i n a r y r e s u l t s aE the six Nike-Tomahawk probes launched
i n d i c a t e tlia L the m e a s ured d iurrxal varia Lion i r z Lernpera Lure is smewlw t
l a r g e r than that predicted theoretically by the JACCWU L964 model
amas phere
.
22.
The paper ent i r l e d "Atmospheric Models Relative to Orbital
L i f e t i m e Investigationst' presented a t the American Meteorological Society
National Cowerence on High A l t i t u d e Meteorology and S p a c e Weather i n
Houston, Texas, 29-31 March 1967 was very f a v o r a b l y received. Our
p h i l o s o p h y of using d i f f e r e n t model atmospheres f o r d i f f e r e n t a p p l i c a t i o n s i s i d e n t i c a l to the concept used by the U. S. A f r Force.
23. Work d u r i n g t h i s r e p o r t i n g period has been d e v o t e d ta (1) the
e s ~ a b l f s l u i t e n t01 M a r L i a r r atmospheric information essential. to the
environmental d e s i g n c r i t e r i a far the Voyager Phase C RFP, (2) the
pub1 ication of TM X-53521, "Space Environment Criteria GuFdelines for
Use in Space Vehicle Development (1967 Revision) ," (33 the completion
of TR-793-7-142, "Analytical Model of t h e Martian Surface," by Korthrop
s u p p o r t c o n t r a c t o r u n d e r contract NAS8-20082, ( 4 ) the completion of a
p a p e r e n k i t l e d "The Marbian A t m o s p l ~ e r e , " wlxich is to be g i v e n at the
A p r i l 1 0 I E S Conference in Washington, D C., and (5) the continua t t o n
of a very de ta-iled s t u d y concerning t h e theare t i c a l aspects of o b t a i n i n g
Mar tiafi amos pheric in£orma t i o n through the vacuum c h b e r s i m u l a t i o n of
t h e Nar t i a n atmosphere
.
.
�A.
F l u i d Mechanics Research O f f i c e
I.
S t a t u s of X-Beam Development
During the week of March 20, an exploratory test was pewformed on a i i v e - e n g i n e c l u s t e r i n s t a l l e d in the W F .
The crossbeam was u s e d in making s p a c e - t i m e correlations withLn the shear layer
r e g i o n s of t h e i n r e r a c t i n g plumes. A similar t e s t was also conducted
~ ! r i r i n gt h i s p e r i o d on a s i n g l e engine with shocks in the flow.
A p r e s e n t a t i o n on t h e current position a n d f u t u r e plans for
the cross-beam program was given to Dr. Johnson (R-EO-DIR) on March 1 4 ,
1 9 6 7 . A c o n r r a c r w i t h the IIT Research Insritute has been s i g n e d f o r
the continuation of the aerodynamic cross-beam t e s t programs. A l s o a
contract has been s i g n e d w i t h Colorado S t a t e U n i v e r s i t y for a CrossedBeam Weather Watch Study. Work is progressing on s c h e d u l e f o r the
assenbling of t e s t e q u i p m e n t and a s s o c i a t e d hardware f o r t h e atmospheric
f i e l d t e s t a: the Army rnereorological tower at Redatone Arsenal.
2.
O r b i t a l Aerodynamic Calculation Research
The Monte Carlo approach to the s t u d y of the shadow and
wake effects in f r e e molecular flow has yielded very interes Ling r e s u l t s
which can be incorporated into the present orbital aerodynamic c a l c u l a tion programs,
From the s t u d y of W o d i s c s at various separation
d i s t a n c e s , a s i m p l e expression f o r the divergence of t h e flow from the
hyperthermal l i m i t can be determined as a f u n c t i o n of the s p e e d r a t i o .
Quantitatively, the a n a l y s i s shows that t h e f l o w diverges from t r u e bgperthermal f l o w by approximately 2.5 degrees at a s p e e d r a t i o of 5 a n d about
1 d e g r e e at a s p e e d r a t i o 0 5 10. For some o r b i t a l c o n f i g u r a t i o n s ,
neglecting this small divergence in tF.e flow could r e s u l t in a f a c t o r of
2 e r r o r in the a e r o d y n a m i c c a l c u l a t i o n .
In t h e s t u d y of concave b o d i e s , i n c l u d i n g wedges, semic y l i n d e r s (of g e n e r a l cross-sectional shape) and concave hemispheres,
t h e most s i g i l i f icant f e a t u r e i s the deviation from the hyperthermal
s o l u t i o n s g i v e n by Schamberg, In h i s a n a l y s i s , the e f f e c t of the conc a v i t y was t o decrease t h e d r a g c o e f f i c i e n t , while t h i s s t u d y (alang w i t h
a few o t h e r s ) now i n d i c a t e s an increase in the drag c o e f f i c i e n t .
Specifi c a l l y , w h i l e ScIlamberg% a n a l y s i s anc the Monte Carlo a p p r o a c h borh
y i e l d a d r a g coefficient value of 2.63 f o r a sphere ( w i t h an accommodation c o e f f i c i e n t of 0.51, Schamberg's value for a concave hemisphere is
Less t h a n 2.63,1~7hilet h e Monte C a r l o y i e l d s 2.90.
Other parameters which
c a n b e compared, such as the number of molecules e x i s t i n g at each c o l l i s i o n and t h e f l u x along the surface, are i n agreement.
�B.
Mechanical Design Office
1. The single-component m i c r o f o r c e balance (No. 220) has been
c a l i b r a t e d and i n s t a l l e d i n the Low D e n s i t y Chamber for t e s t i n g .
The
b a l a n c e is capable of measuring 112 to 8 gm d r a g f o r c e s with an a c c u r a c y
of 2 1 1 2 p e r c e n t , A backup balance i d e n t i c a l Co number 226 has been
ordered.
2.
Two m o d e l s o f p r o p o s e d S-IVB O r b i t a l Workshop c a n f i g u r a -
t ions have been designed and f a b r t c a t e d on a rush b a s i s f o r use in
determintng p r o j e c t e d areas and area moments of inertia of the models
at various a n g l e s of a r t a c k . A modellmirror s u p p a r t f i x t u r e f o r use
in a c q u i s i t f o n of these data is b e i n g b u i l t .
3 . The following i s a partial l i s t o f additional p r o j e c t s and
t h e i r currer-t status:
4 P e r c e n t Saturn V force model and balances
-
Design
AEDC
Modification of f i v e - e n g i n e model
-
CFD
-
-
P r e s s u r e probes and s u p p o r t system
Design
Des i g n
14" wind runnel
Balance, drive systemand r e l a t e d e q u i p m e n t
f o r s l o s h farce measurements
Design
Remote c o n t r o l hardware f o r f l o o r a n d
ceiling adjusment
TTS, 14" WT
Des i g n
-
-
Temperature
-
Mismatch T e s t Section
-
Five-component balance, 112-inch 0 . D .
8-foot O . D . vacuum exhausr plenum
D r a f t ix?g
-
Drafting
-
Variable p o r o s i t y walls for TTS, 14" WT
Draf r i n g
-
Fabrication
Boom and clamps f o r meteorological t e s t i n g
on 400-foot RSA tower
Fabrication
Fins and axisymrnetric body and balance,
Fabrication
-
14" WT
-
S a t u r n V, thin s k i n heat t r a n s f e r model,
JPL
-
Fabrication
�S a t u r n IB forced oscillation model and
balance, 14'' WT
Fabrication
-
Modification of S - I B force model, 14" WT
-
Fabrication
-
Jigs for modification 05 Nike motors, KSC
Fabrication
S t r a p - o n boosters f o r S-TC model (CAL d e s i g n ) , Fabrication
CAL F l a t p l a t e model (NSL d e s i g n ) , Ames
-
Fabrication
Laser Doppler Turbulence Hardware,
Raytheon d e s i g n
Fabrication
-
0 s c i l l a t ing wake model
(Lockheed d e s i g n )
-
Cold flow stilling chamber and nozzle for
laser work
Del ivered
-
Pressure models f o r X-beam SPLTS, 14T1WT
-
Sidewall-mounted i n t e r s t a g e h i n g e model
and balance
14" WT
-
C.
Fabrication
-
Del ivered
Delivered
Aerodynamic Design Branch
1.
U p r a t e d S a t u r n TIAS-206 Aerodynamic Inves t i g a t ion
Tests have been completed to determine the s t a t i c l o n g i t u d i n a l s t a b i l i t y a n d a x i a l force characteristics for the u p r a t e d
S a t u r n I/AS-206 v e h i c l e configuration. The t e s t s were conducted at
AEDC' s s u p e r s o n i c a n d hypersonic tunnels, CAL' s t r a n s o n i c tunnel, a n d
MSFC'S 14-inch r r i s o n i c ~ u n n e lduring t h e fall of 1966. The data
obtained were analyzed and have been documented a s R-AERO-AD- 6 6 - 6 3 .
2.
Saturn
IB w i t h External Mounted Solar Panels
The mounting of e x t e r n a l s o l a r arrays has been s t u d i e d
The area of the s o l a r arrays c o n s i d e r e d is
800 square feet. The three external l o c a t i o n s being c o n s i d e r e d are
(1) the forward s k i r t : o f the S-IVB s t a g e , (2) the a f t skirt of t h e S-IVfi
s t a g e , a n d (3) t h e c o n d u i t that extends f r o m s t a t i o n 1188 forward approximately 400 i n c h e s . The c o n d u i t mount is t h e most d e s i r a b l e from the
aerodynamic c o n s i d e r a t i o n s because the maximum height is 1 2 inches as
compared t o 42 i n c h e s f o r the other external configurations.
f o r rhe Saturn XI3 v e h i c l e .
�P r e l i m i n a r y aerodynamic l o a d s on t h e s o l a r p a n e l s mounted
on the forward and a f t s k i r t s of the S-IVB s t a g e are d e f i n e d fn O f f i c e
Memo R - A E R O - A D - ~ ~ -a~n~d ,aerodynamic Loads an the conduits are p r e s e n t e d in O f f ice Memo R-AERO-AD-67-27.
3,
S a t u r n IB Vehicle
-
S t r u c t u r a l Modification
The a d d i t i o n of external
s t r i n g e r s to s t i f f e n the S a t u r n LB instrument unit has been p r o p o s e d .
T h i s w o u l d h e l p el i m F n a t e v i b r a t ianal problems w i t h the ST-124 g u i d a n c e
plarforrn e n c o u n t e r e d on past Sarurn LB f l i g h t s . This p r o p o s a l was
reviewed and found a c c e p t a b l e from a s t a t i c aerodynamic s t a n d p o i n t
( r e f e r e n c e R-AERO-AD-67-19).
4,
S a t u r n IIB/Z;M Vehicle
a.
Local Flow F i e l d P r o p e r t i e s
Local Mach numbers, p r e s s u r e s , temperatures, densities ,
and v e l o c i t i e s have b e e n computed f o r the u p p e r half of the S a t u r n I B / W
vehicle f o r f r e e stream Mach numbers ranging from 3 . 7 to 12.0.
These
data determined for both a = 0" and
= 8" Iuve been documented i n
CCSD TB-AP-46-74 a n d a r e enclosed i n R-AERO-AD-67-14.
b.
Compartment Venting
I n - f l i g h t v e n t i n g analyses of t h e S-IBIS-IVBi n t e r s rage
a n d t h e S - I B t a i l b a r r e l compartments have b e e n completed and documented in
CCSD TB-AP-66-75 (R-AERO-AD-57-12) , and CCSD TB-AP-66-76 (R-AERO-AD- 6 7 - 1 3 ) ,
respectively.
T h e s e d o c u m e n t s presenE maximum and minimum bands of
internal p r e s s u r e f o r each compartaenr.
5.
S a t u r n LR/LM w i t h Three- a n d Six-Foot: Length E x t e t s i o n s
The aerodyn~mic s t a t i c s e a b i l i t y a n d l o c a l normal f o r c e
c o e f f i c i e n t s f o r the d e s i g n Mach number and angle ot at tack r a n g e have
b e e n derermined. The configurations s t u d i e d c o n s i s t e d of (1) a 3 - f o o t
c y l i n d r i c a l e x t e n s i o n 260 inches in diameter and (2) a 6 - f o o t c y l i n d r i c a l
e x t e n s i o n 260 inches in diameter a d d e d between t h e Saturn IB v e h i c l e
IU a n d the SLA. The abme d e s i g n d a t a a r e b e i n g pl.rhlfshed in an o f f i c e
memorandum.
The perturbetion en compartment v e n t i n g d u e t o t h e i n c r e a s e
i n volume i s b e i n g d e t e r m i n e d and w i l l be p u b l i s h e d in the future.
6.
S a t u r n I E Improvement Studies
-
MSFC Wind Tunnel Tests
Data from w i n d tunnel t e s t s of several proposed S a t u r n I E
con£ i g u r a t i o n s which a r e u p r a t e d w i t h 120-inch d i a m e t e r s o l i d r o c k e t motor
s t r a p - o n u n i t s have been i n c l u d e d i n bwo r e p o r t s which are b e i n g reviewed.
�S t a t i c s t a b i l i t y , axial f o r c e a n d loads o n the 70-incli diameter S - D
s t a g e tanks a r e i n c l u d e d in these r e p o r t s .
CCSD has been f u r n i s h e d
w i t h data from these t e s t s in b o ~ ht a b u l a t e d a n d magnetic tape Eorm.
7.
~ p o l l o / ~ a c u sVn Aerodynamic Characteristics f o r
L i f t o f f Analysis
Aerodynamic c h a r a c t e r i s t L c s f o r S a t u r n V lif to£f a n a l y s e s
were e s t a h l i s h e d September 1966 in NASA
X-53517,
The data established
were for t h e c a s e o f ground wind d i r e c t e d into the l a u n c h umbilical tower
t h e r e b y s u p p o r t i n g t h e c r i t i c a l vehicle/ launch tower clearance analysis.
To further support the vehicle close-support clearance analyses resulting from g r o u n d w i n d from various directions, aerodynamic data h a v e been
p u b l i s h e d t o supplement the data of TM X-53517.
These data are presented
in Office Memo R - A E R O - A D - ~ ~ - ~The
~ . data are based on the l a t e s t available ground w i n d s experimental data.
8.
Apallo/Saturn V S t a t i c F o r c e and Pressure T e s t s at AEDC
A conference was h e l d at AEDC to d i s c u s s r e s t i n g a 4 p e r model of t h e ApollolSaturn V i n t h e AEDC 16-foot t r a n s o n i c
wind t u n n e l in September 1967. The scope of the t e s t program has been
changed to include pressure d i s t r i b u t i o n s on the a £t cyl i n d e r , shrouds,
and fins, as well as the o r i g i n a l total f o r c e measurements. Data w i l l
b e o b t a i n e d f o r angles of a t t a c k up to 14 degrees f o r Mach numbers from
0.6 to 1.4 w i t h Reynolds number variations.
cent scaled
9.
Apollol~at u r n V S - I C I S-11 I n t e r s tage Aerodynamics
The subsonic-transonic portion of t h e investigation was
c o n d u c t e d in the MSFC 14-inch TGirT from March 6 to March 2 0 , 1967. The
t e s t s were conducted over a Mach number range of 0.50 through 1.96 a n d
a n a l p h a r a n g e of 0 through 180 degrees.
Data for a few angles of
a t t a c k were obtained f o r Mach 2.74 and 2 . 9 9 f o r c o r r e l a t i o n of the
p r e s e n t t e s t method with t h a t of the previous supersonic t e s t s . Model
hardware cons is t e d of a half -model splitter-plate sys tern mounted on
the tunnel sidewall as o p p o s e d to t h e s ting-mounted model used d u r i n g
the supersonic i n v e s t i g a t i o n . Data agreement between rhe f x o s y s t m s
TlraS good for low angles of a t t a c k .
For alphas near 45 and 135 degrees,
the s p l i t r e r - p l a t e d a t a appear t o be low.
The d a t a are b e i n g analyzed and e f f o r t s are b e i n g d i r e c t e d
toward dctcrmining the causcs and magnitudes of the data discrepancies
so t h a t proper c o r r e c t i o n s can be made.
�10.
ApoPlolSaturn V Aerodynamic Force T e s t s
The a n a l y s i s report o f the m o s t recent Apollo/Saturn V aerod y n a m i c f o r c e tests has not been completed because p r e s s i n g t i m e schedules
in ather areas have allowed only minimal effort on t h i s task.
this r e p o r t s h o u l d b e r e a d y for publication In May 1967.
PI. S a t u r n V
However,
L i f t o f f Aerodynamics
The current A p o l l o / ~ a
turn V 1iftoff maneuver has c r e a t e d
a need for more d e t a i l e d informatton concerning on-pad loads caused by
ground w i n d s . Available d a t a d o n o t provide total s t a L i c loads nor
is the engine-on s i t u a t i o n considered; t h e r e f o r e , a test will he conducted in the LTV low s p e e d w i n d tunnel to determine loads on the
ApolIalSaturn V while in t h e lau~lchp o s i t i o n for both engine-on and
e n g i n e - o f f s i t u a t i o n s . Alsa, loads w i l l be determined as a function
of altitude as the vehicle r i s e s o f f t h e pad. Models and associated
t e s t h a r d w a r e w i l l . b e d e s i g n e d a n d f a b r i c a t e d by LTV.
It is estimated
t h a t the r e s u l t s of t h e program w i l l be a v a i l a b l e by August 1967.
12.
Saturn
V I a t e r f ereace Free Fin-Shroud Inves t i g a tions
The data from wind tunnel tests r a n d u c t e d to p r o v i d e
i n t e r f e r e n c e f r e e lvads VII ~ l i rSaturli V r i l l s a n d s h r o u d s have b e e n
r e d u c e d an? checked.
These data a r e b e i n g analyzed a n d a r e p o r t
s h o u l d be r e a d y by June 1967.
13.
S a t u r n V Roll I n v e s t i g a 5 i o n
The e f f e c t s o f roll angle on the s t a t i c longitudinal
s t a b i l i t y and axial f o r c e characteristics for the Apolle/Saturn V
v e h i c l e were s t u d i e d in the MSFC 14-inch TWT. A 0.3366 percent scale
model with all proruberances was used in t h i s t e s t . The d a t a were
reduced and a n a l y z e d and are available in Office Xemo R-AERO-AD-67-11.
14.
S a t u r n V Voyager Ground Wind S t a t i c Aerodynamic Loads
A n aerodynamic f oad d i s t r i b u t i o n far d e t e r m i n i n g l o a d s
d u e to ground w i n d s an the S a t u r n V Voyager has been p u b l i s h e d i n
O f f i c e Memo R-AERO-AD-67-20, d a t e d March 9 , 1 9 6 7 . The l o a d d i s t r i b u t i o n m u s t b e used in conjunction w i t h t h e a p p r o p r i a t e horizontal ground
w i n d s profile t a o b t a i n v a l i d l o a d i n g s .
15.
S a t u r n Y Improvement S t u d y
An aerodynamic analysis w i l l soon be p u b l i s h e d for an
u p r a t e d S a t u r n V v e h t c l e ~ 5 t hf o u r 120- inch seven-s egment , sol id motors
attached t o the S-IC boos tcr. TIIC a n a l y s i s is b a s e d on experimental
w i n d tunnel data o b t a i n e d f r o m the HSFC 14-inch uind tunnel.
�16.
S a t u r n V E l a s t i c Body Aerodynamics
The a e r o d y n a m i c s f o r a deflected vehicle have been d e t e r m i n e d front linearized theory coupled w i t h s t a n d a r d Apollo/Saturn V
load d i s t r i b u t i o n s .
The incremental load d i s t r i b u t i o n s d u e t o bending
m=re determined for Mach number 1.2 and a rigid body angle of a t t a c k
of 8 d e g r e e s . A bent v e h i c l e s h a p e was o b t a i n e d from R-AERO-D. T h e s e
aerodynamic d a t a will b e used by R-MRO-D t o determine t h e m a x i m u m
b e n d i n g moments f o r an e l a s t i c body.
17.
O r i f i c e Flow C o e f f i c i e n t S t u d y
The o r i f i c e flow i n v e s t i g a t i o n which s u p p o r t s t h e S a t u r n V
v e n t i n g program was i n i t i a l l y conducted in the Ames 6-foot s u p e r s o n i c
wind tunnel in November 1966. The f inaL d a t a were recetved h y Nor throp
Space Labs f r o m ARO of Ames Research C e n t e r .
These data were analyzed
a n d found to c o n t a i n many errors, most of which c o u l d be a t t r i b u t e d to
e r r o r s in the ARO data reduction program. ARO acknowledged the probLerns
by r e c h e c k i n g t h e data and making necessary changes.
Thc c o r r e c t e d data
have been received and a r e b e i n g analyzed by NSL.
S i n c e f u r ~ h e rt e s t i n g is r e q u i r e d because of the m o d e l and
ins trum~nrationproblems e n c o u n t e r e d during the f i r s t zest, a model
r e d e s i g n was i n i t i a t e d and was r e c e n t l y f i n i s h e d by NSL. Fabrication
1lril.1 begin s h o r t l y a n d is scheduled to b e completed by about June 15,
1967.
The contractor's proposal in response to the RFQ f o r
e x t e n s i o n of the p r e s e n t c o n t r a c t to cover the additional t e s t i n g at
Ames a n d a l i m i t e d program at MSFC was r e c e i v e d and approved. The
new contract e x t e n s i o n s h o u l d soon be f i n a l .
18.
Body of R e v o l u t i o n V i s c o u s Crossflow Investigation
High Reynolds number data o b t a i n e d a t LTV a r e b e i n g
evaluated. Additional h i g h angle of a t t a c k t e s t i n g began Harch 23 in
the MSFC 14-inch f a c i l i t y a n d will c o n t i n u e t h r o u g h A p r i l 17. The vapor
s c r e e n technique of o b t a i n i n g photographs of t h e Lrail i n g v o r t e x s y s tern
w i l l b e checked a g a i n d u r i n g t h i s t e s t . The two major problems in t h i s
area a r e controlling t h e p r o p e r amount of mois Lure in t h e test s e c t i o n ,
and pos i t i o n i n g t h e camera downstream such that t h e 1i g h t i n g is a d e q u a t e
a n d the viewing angle is r e a l i s r i c .
19.
Low D e n s i t y Wind Tunnel T e s t s
The E n g i n e e r i n g Phys i c s Sect i o n (R-AERO-AEP) has had a
d r a g balance f a b r i c a r e d f o r use in the MSFC Low D e n s i t y (Mach 4 ) Wind
Tunnel. This balance is capable of measuring drag loads on b o d i e s in
�t h e load range f r m one to t e n grams. This b a l a n c e will be u s e d to
measure drag loads on spheres, cylinders, d i s c s , and p o i n t e d cones t h a t
have a n i n e d e g r e e half-angle. The Knudsen number will be varied over
a w i d e range s o that data can be obtained in the continuum s L i p , trans it i o n a l , and f r e e molecule flow regimes. The Knudsen number will be
varied b y changing the w i n d t u n n e l s t a g n a t i o n pressure and by u s i n g
s e v e r a l d i f f e r e n t s i z e m o d e l s . The drag data from these tests will be
compared rrrrth similar drag measurements t h a t have been made in s i m i l a r
low d e n s i t y w i n d tunnels e x i s t i n g in the United S t a t e s .
20.
Reaction Control System (RCS) Impingement E f f e c t s on the
Lunar Module (LM)J ~ p olo
l Telescope Mount {ATM)
In a memorandum to t h e P r o j e c t s O f f i c e (R-P&VE-PT-67-M-62-D,
d a t e d F e b r u a r y 1 4 , 19671, Mr. H. G. P a u l requested t h a t LM RCS impingement e f f e c t s on the m / ~ m
be investigated. The Lockheed Missiles and
S p a c e CompanylHuntsvil l e was a l s o a s k e d to i n v e s t i g a t e t h i s problem.
E f f o r t s in the Aero-Astrodynamfcs L a b o r a t o r y have been confined to
monitoring t h e Lockheed e f f o r t . Lockheed has inves tigated t h r u s t l o s s
and h e a t i n g r a t e s d u e to RCS impingement. M r . J. D. Johnson, R-AERO-ADE,
h a s monitored the thrust loss calculations and Mr. Rochelle, R-AERO-ATB,
has monitored t h e b e a t i n g r a t e c a l c u l a t i o n s . Lockheed is p r e p a r i n g
r e p o r t s for Mr. George Hopson, R-P&E-PTD, t h a t p r e s e n t RCS plume shapes,
h e a t i n g r a t e s , and t h r u s t - l a s s e s . These reports will be completed d u r i n g
the f i r s t h a l f of A p r i l .
Meetings f o r MSFC and MSC personnel were h e l d by R - E V E on
%rch 9 and 30 to d i s c u s s t h e LM/ATM RCS impingement problem. At these
mee Lings it was decided t h a t MSFC (R-ASTR and R-?&m) s h o u l d investigate
t h e u s e of d e f l e c t o r s in conjunction w i t h retractable s o l a r p a n e l s .
21.
Orbital Aerodynamics
A s c h e d u l e has been established f a r rhe calculation of
o r b i ~ a laerodynamics f o r t h e o r b i t a l workshop and L'MIATM cluster eonfiguration. This schedule is presented in memorandum R-AERO-AD-67-18,
d a r e d March 7 , 1 9 6 1 . These c a l c u l a t i o n s are b e i n g made by the Lockheed
Missiles and S p a c e Company u n d e r NASA S u p p o r t Contract NAS8-20082 a s
d i r e c t e d in Schedule Order No. 65. To meet the s c h e d u l e , the number of
Lockhecd personnel working oc Schedule O r d e r Ha. 65 was increased to
s i x . Lockheed i s p r e s e n t l y 3 days behind s c h e d u l e . This i s p a r t l y
because of a d e l a y in c o n f i g u r a t i o n d e f i n i t i o n . During t h i s r e p o r t i n g
p e r i o d , Lockheed p e r s o n n e l have c a l c u l a t e d o r b i t a l aerodynamics f o r
several orbital workshop and LM/ATM c l u s t e r configurations . These
d a t a a r e p r e s e n t e d in the following memorandums:
�(I)
O r b i t a l a e r o d ynarnic character i s t i c s f o r t h e orb i t a P
workshop w i t h the docked mapping and survey s y s t e m
WSS) w i t h and w i t h o u t the docked c m n d and service
module (CSM), R-AERO-AD-67-24, March 15, 1 9 6 7 .
(2)
O r b i t a l aerodynamic character is t i c s f o r the c l u s t e r
arrangement of the o r b i t a l workshop, R-AERO-AD-67-25,
March 15, 1967.
(3)
Orbrtal aerodynamic character is tics f o r t h e cormnand
a n d service module, R-AERO-0-67-26,
March 15, 1967.
(4)
O r b i t a l aerodynamic characterts tics of the c l u s t e r
arrangement of the orbital workshop with and without
the docked cormand and s e r v i c e module, R-AERO-AD-67-29,
Karch 28, 1 9 6 7 .
A "shadow method" of p r e d i c t i n g aerodynamic c o e f f i c i e n t s on
an a r b i t r a r y body in the free molecular, high speed r a t i o flow regime
was fnves t i g a t e d (in-house) d u r i n g F e b r u a r y and Harch.
The "shadow m e t l ~ o d " involves measuring frontal areas from
m o d e l shadows p r o j e c t e d b y a parallel lighr beam, u s i n g t h e f r o n t a l area
in c o n j u n c r i o n w i t h empirical data to determine the drag coefficient of
the body, and resolving the drag coefficient into force and moment c o e f f i c i e n t s r e l a t i v e to a body-axis system.
The i n v e s t i g a t i o n proved the method to be satisfactory.
E f f o r t s a r e now underway to eliminate some problem areas and to etreaml i n e t h e p r o c e d u r e as much as p o s s i b l e . Although a computer program
was compiled t o c a l c u l a t e coefficients once areas are o b t a i n e d , mechani c a l integration of areas causes the p r e s e n t p r o c e d u r e to be t i m e consuming.
Two automated systems c u r r e n t l y being developed by R-AERD-RB
a n d R-AERO-AEI w i l l hope f u l l y reduce the t i m e r e q u i r e d to g e n e r a t e data.
D.
E x p e r i m e n t a l Aerophys i c s Branch
1.
14 x 14-Lnch T r i s o n i c Wind Tunnel
The following t e s t s were conducted d u r i n g the r e p o r t p e r i a d
of F e b r u a r y and March:
(a)
The i n v e s t i g a t i o n by Lockheed f o r R-AERO-AL te determine the e f f e c t of an oscillating wake s o u r c e on t h e
aerodynamic c h a r a c t e r i s t i c s of t h e S a t a r n ZB a n d V
A p o l l o c m a n d modules submerged in t h e wake was
can t i n u e d
.
�(b)
An i n v e s t i g a t i o n for AMICOM te determine the
f e a s i b i l i t y of the use of f l u i d amplifiers f o r a l t i t u d e control devices.
The t e s t was d i s c o n t i n u e d
because of model malfunctions b u t i s expected to
be resumed l a t e r .
(c)
A n inves Ligation into c e r t a i n flow phenomena associ a t e d w i t h the testing of winged configurations at
different wall porosities in the h i g h s u b s o n i c s p e e d
range. This was done in cooperation w i t h McDonnell
A i r c r a f t who f u r n i s h e d t h e model. Total r u n s :
6.
(d)
A preliminary investigation by I I T X T f o r R-AERO-AM
to determine t h e s t a t i c and a c o u s t i c pressures on
c y l i n d r i c a l and s t e p models p r i o r to o p t i c a l crassbeam measurements i n t h e special test s e c t ion.
Total suns: 52.
(c)
An i n v e s t i g a t i o n for R-AERO-AD to d e t e r n i n e the
s t a t i c s t a b i l i t y a n d a x i a l farce characteris tics of
thc S a t u r n V S - I C / S - I 1 i n t e r s t a g e ring. T o t a l runs:
139.
updated.
permit.
(£1
An investigation f a r R-AERO-AD to d e t e r m i n e t h e s t a t i c
s t a b i l i t y and axial force characteris t i c s of proposed
Saturn IB (AS-206) configurations w i t h a n d w i t h o u t
solar panel shrouds. Total runs: 37.
(g)
An investigation f o r R-AERO-AD to s t u d y the v i s c o u s
cross-flow e f f e c t s on b o d i e s of r e v o l u t i o n a c h i g h
angles of a t t a c k . T e s t is c u r r e n t l y i n progress.
The tunnel control and instrumcntacion p a n e l s a r e b e i n g
The new c a b i n e t s and panels will be i n s t a l l e d as s c h e d u l e s
Work is underway to develop a s u i t a b l e vzpor s c r e e n t e c h nique i n the tunnel. T h e technique is unique in s u p c r s o n i c blotqdot.m
wind tunnels because of d i f f i c u l t y in o b t a i n i n g t h e proper c o n d i t i o n s
in the relatively s h o r t blow time.
The t u n n e l is heavily scheduled through June 1.967.
�2.
7 x 7-Inch B i s o n i c Wind Tunnel
The BWT has been reassembled a f t e r an e x t e n s i v e cleaning
and should be o p e r a t i o n a l by May 1, 1967. The e l e c t r i c a l sysrem has
b e e n reworked a n d u p d a t e d .
3.
Thermal A c o u s t i c J e t Facility
Tests on the cold flow duct have been continuing f o r
R-AERO-AY on n o z z l e flow a n a l ys is u s i n g t h e cross -beam correlation
Lechnique.
T e s t s have been c o n d u c t e d on b o t h srngle and c l u s t e r e d
nozzle configurations.
E x ~ e n s i v eshadowgraphic photography coverage
has a l s o been made. T o t a l runs: 7 4 1 . C o n t i n u e d t e s t i n g has been
s c h e d u l e d for May 1 9 6 7 .
The he 1ium heater has undergone a major d es i g n change.
This was the d i r e c t r e s u l t of NASA i n s p e c t i o n of the u n i t .
The cont r a c t d e l i v e r y d a t e is now s e t at early summer.
4.
Hot and C o l d Flow T e s t F a c i l i t i e s
Both t h e HFTF a n d the CFTF have been i n a c r i v e d u r i n g t h i s
r e p o r Ling p e r i o d
In ger.era1, the c o l d f l o w duct of the TAJF will run
t e s t s p r e v i o u s l y associated w i t h the CFTF.
The CFTF i s held in a r e a d y
status.
.
5.
IBFF
The I m p u l s e Base Flow F a c i l i t y was s c h e d u l e d t h i s e n t i r e
p e r i o d La determine the sound i n t e n s i t y l e v e l s of t h e f u t u r e high
Reynolds number equipment d u r i n g flaw initiation time and d u r i n g normal
run t i m e .
It is d e s i r e d to keep the i n t e n s i t y b e P m 1 2 0 db SPL.
I n t e n s i t y levels observed w i t h a 1 / 2 5 s c a l e model of the
f u t u r e equipment were approximately 1 9 0 db when the m o d e l charge pressure
w a s 650 p s ig ( t h e estimated charge pressure of the f u t u r e equipment).
A1 h measurements were obtained with the model exhaus Ling to t h e
amosphere.
Dbviausly, some r e d u c t i o n in i n t e n s i t y was r e q u i r e d . A f t e r
s e v e r a l c o n s i d e r a t i o n s , discharging the model i n t o a s p h e r e and then
slowly v e n t i n g t h e s p h e r e to atmosphere was chosen a s one solution.
T n t e n s i t y l e v e l s of 1 3 5 d b w e r e recorded (peak levels for 2 miZliseconds
d u r a t i o n ) when the m o d e l exhausted i n t o the sphere.
T e s t s were n u d e to
determine if a r a d i a l e n t r y or a tangantial e n t r y i n t o the s p h e r e h a d
any effect on the i n t e n s i t y levels. Differences in i n t e n s i r y levels
based on sphere e n t r y were small; howzver, s t r u c t u r a l loads on the sphere
�resulting from t h e i n i t i a l M a s t of a i r
c r i t i c a l . The r a d i a l e n t r y b l a s t e d the
whereas t h e t a n g e n t i a l e n t r y l o a d e d t h e
p r c s e n t e d s t r u c t u r a l d e s i g n problems on
diameter)
.
(opening of the diaphragm) were
o p p o s i t e s L d e of the sphere
sphere unequally. Both c a s e s
t h e full s c a l e sphere ( 5 0 f o o t
A s a r e s u l t of the above t e s t s , a m o d i f i e d r a d i a l e n t r y
inLo t h e s p h e r e was s e l e c t e d .
The m o d i f i c a t i o n allows the sphere to
be l o a d e d e q u a l l y , t h u s e l i m i n a t i n g t5e structural p r o b l e m s .
The op tirnum flow geometry of the p r e v i o u s l y mentioned
modification i s p r e s e n t l y b e i n g s t u d i e d .
The i n t e n s i t y l e v e l a f the
f l o w with t h e modification i s expected to be less t h a n the 135 d b
o b s e r v e d earlier.
6.
Nigh Reynolds Number T e s t Equipment
Design of the h a r d w a r e is p r o g r e s s i n g s a t i s f a c t o r i l y .
PLuiDyne e s t i m a t e s t h a t d e s i g n work w i l l be completed in l a t e Kay.
P r o c u r e m e n r a c t t o n s have been i n i t i a t e d f o r the sphere and the s u p p l y
t u b e . The s e t t l i n g chamjer and a few other miscellaneous items will
be o r d e r e d s h o r t l y .
A l l procurement a c t i o n s are being h e l d in R&DO
until f u n d i n g can be arranged. D i s c u s s i o n s are underway w i t h F&DO to
determine working arrangements, l i n e s of c o m u n i c a t i s n s , a n d i r t c r f a c e
requirements necessary to f a b r i c a t e a n d e r e c t the t e s t equipment.
7.
Low D e n s i t y
Calibration suns on t h e Mach 4 low
Runs
b o t h u p s t r e a m and dormstream of the n o z z l e e x i t
i n c h e s . Resul t s from t h i s t e s t will d e f i n e the
f 1 OW and tlbz Mach number g r a d i c n .~
c o n t i n u e d w i t h the i m p a c t p r e s s u r e p r o b e .
dens l t y nozz Le have
have been complctcd
to a d i s t a n c e of 1 2
i s e n t r o p i c c o r e o f the
A p e n d u l u m - ~ y p e m i c r o f o r c e b a l a n c e (KO. 220) h a s b e e n
c a l i b r a t e d and installed in thc low dens ity w i n d t u n n e l .
R e s u l t s thus
f a r look v e r y p r o m i s i n g as d r a g forces have been r e a s u r e d on a h a l f c y l i n d e r a n d hemisphere m o d e l . P r e s e n t l y , t h e s e d a t a arc b e i n g u s e d
t o c a l c u l a t e d r a g c o e f f i c i e n t s , a n d t h e r e s u l t s a r e b e i n g compared with
theory and other published experimental r e s u l t s . Due to the size of t h e
m o d e l s (3-inch d i a m e t e r sphere, 3- inch diameter by 6 - i n c h half-cyl i n G e r ) ,
the r c s u l t s will b c takcn f r o m the t r a n s i t i o n flo~t1r e g i m e .
T h t s was;
Other m o d e l s arc b e i n g
v e r i f i e d by t h e measured experimental r e s u l t s .
f a b r i c a t e d which w i l l e x t e n d r a n g e of drag forces to b e mcasured and will
a l s o a1Lor.1 measurements t o b e m a d e ir, t h e f r e e molecular f l o w regime.
(I$e w i l l . have Knudscn numbers of 1 < Kn < 3 d u r f n g our f i r s t e x p e r h e a t s .)
�8.
Heat Transfer Fnstrumentation
The s t a t is t i c a l a n a l y s Fs c o n d u c t e d on the h e a t transfer
gages has been continued. Thus f a r , no d i s t r i b u t i o n has been found
whtch d e f i n e s t h e c h a r a c ~ e r itics
s
of the heat gages.
Ames Research C e n t e r has b e e n very i n t e r e s t e d in our
experiences and techniques concerning t h i n f i l m heat t r a n s f e r gages.
They are devziaping a shock tunnel similar to ours. We have l o a n e d
s m c i n s trumcntation items and samples of o u r h e a t transfer g a g e s .
9,
Data Reduction
Reduction
05
114 r u n s by R-AERO-AE
of the S a t u r n V a c o u s t i c
t e s t s was made by automated data handling a n d p r o c e s s i n g e q u i p m e n t .
T h i s represents 40 percent of t h e d a t a t h a t are to b e r e d u c e d to sound
p r e s s u r e levels. The r e d u c t i o n of t h e s e 12,000 a c o u s t i c measurements
was t r a n s m i t t e d to R-AERO-AU March 29.
The r e d u c t i o n program was i n t e r r u p t e d when the equipment
w a s re-shipped to AEDC March 6 f o r t h e second p h s 2 test in the s u p e r s o n i c s e c t i o n of t h e PWT. The equipment was r e t u r n e d March 17 and is
b e i n g reassembled to provide R-AERO-AU w i t h the remainder of the test
data. It: appears t h a t R-AEBO-AE will reduce all d a t a to overall s o u n d
p r e s s u r e l e v e l s , and R-COKE' will d o t h e s p e c t r a l a n d temporal r e d u c t i o n .
Data w a s r e d u c e d d i g i t a l l y f a r t e s t s r u n in the TASF, 14inch w i n d t u n n e l , a n d the Pow d e n s i t y chamber. The program to r e d u c e
t h e above m e n r i o n e d a c o u s t i c data was made f u l l y o p e r a t i o n a l . Most of
these t e s t s r e q u i r e d a u t o m a t i c p l o t t t n g .
It: is i n t e r e s t i n g to n o t e
t h a t , f o r t h e p a s t few rnonchs, over one-half of our d i g i t a l data r e d u c t i o n e f f o r t is f o r t e s t s c o n d u c t e d at s i t e s other than MSFC.
a.
General
The multiplex wide-band tape system purchased for use
w i t h t h e Saturn V 4 p e r c e n t m o d e l was used to record d a t a f r m the
14-inch tunnel. The t e s t r e q u i r i n g the s y s t e m was a study of the press u r e f l u c t u a t i o n s in the s p e c i a l t e s t sectLon f o r the crossed-beam
aerodynamic program.
The above t e s t and t h e 4 p e r c e n t a c o u s t i c d a t a r e d u c tion and t e s tFng at AEDC I-lave u s e d a b o u t all available instrumentation
manpower d u r i n g t h i s p e r i o d .
�b.
O r b i t a l Aerodynamics Scanner System
A high s p e e d d i g i t a l s y s t m has been assembled
by R-AERO-AEL for the a c q u i s i t i o n a n d determination of a vehicle's area
and area mmtents. The sys tern is based upon converting the t e l e v i s e d
image from a closed c F r c u i t t e l e v i s i o n camera i n t o a d i g i t a l measurement representation of t h e vehicle's area and area l o c a t i o n . An image
m e a s u r e m e n t is r e c o r d e d in 1 / 6 0 of a second, b u t the t r a n s f e r of the
d a t a to an IBM card for data reduction by R-AERO-AE computer complex
r e d u c e s the s p e e d to 2 m i n u t e s f o r each image r e c o r d e d , i.e., each
a t t i t u d e of t h e vehicle.
(1)
A computer program to s c a l e t h e data into area
and area moments is b e i n g debugged. The system can b e f u l l y operational
d u s ing the n e x t r e p o r t i n g period.
(2)
Purchased parts for another type of scanner
s y s t e m based upon a bar of phatacells are a r r i v i n g . Manufactured
p a r t s are expected f r o m R-ME in the next f e w d a y s .
Control c i r c u i t s
and w i r i n g d r a w i n g s are a l m o s t completed. Tt is e s t i m a t e d t h a t w i r i n g
and checkout w i l l b e completed d u r i n g t h e next t w o months.
c.
High Reynolds Number Equipment P r e s s u r e T e s t i n g
The high Reynolds number equipment is expected to
r e q u i r e a large number (50-200) of chanfiels of pressure measurements
for t y p i c a l models. E f f o r t s in d e v e l o p i n g the hardware and techniques
are l i m i t e d .
Two major problems e x i s t : Firsr, the downstream d i a p h r a g m
subjects the model and i n s trurnentatTon to the high charge p r e s s u r e , t h e n
d r o p s to a much lower running p r e s s u r e which is t h e d e s i r e d valve t o b e
r e c o r d e d . This k m p l i e s t h a t high pressure gages and equipment must be
u s e d with the problem o f r e s a l u t P o n at the low e n d , or the transducers
m u s t b e valved o f f from the high pressure.
Second, the large number of
channels d i c t a t e a scanning type of measurement f o r economic p u r p o s e s ,
i f none other. Our p r e s e n t t h i n k i n g i s t o p u t all i n s t r u m e n t a t i o n inside
the m o d e l , us ing s p e c i s l mu1 ti-channel i s o l a t i o n valves and s p e c i a l 'nigh
s p e e d s c a n n i n g valves. These items will b e m o d i f i c a t i o n s of c u r r e n t l y
available hardware. One scanner s h o u l d be a b l e t o measure p r e s s u r e every
5 or s o milliseconds; 10 ganged scanners w o u l d a c c m o d a t e 100 c h a n n e l s
i n the 5 0 - m i l l i s e c o n d f l o w time. These figures a r e v e r y reasonable f o r
the f a c i l i t y and m o d e l s i z e s i n v o l v e d .
�E.
Thermal Environment Branch
1.
Saturn V
-
S-11 Stage
The B o e i n g Company has taken over the d i r e c t i o n of t h e
multi-protuberance h e a t i n g test. A r u n s c h e d u l e has been d r a m - u p a n d
the p r o t u b e r a n c e models are b e i n g reinstrumented by the F a c i l i t i e s Branch
u n d e r the d i r e c t i o n of Herb B u s h . A d d i t i o n a l ~hermocouples a r e to be
installed on f o u r of the models, T h e t e s t p l a c e w i l l a l s o have to be
mod if i e d and the e x t e n t of m o d i f i c a t i o n is b e i n g determined. T"?e test
will b e conducted at the Langley Research Center in the f a l l .
2.
S a t u r n IB
a.
Fl i g h t E v a l u a t i o n
Because of an expansion i n scope for the f i n a l r e p a s t
of the SA-203 infrared spectrometer f l i g h t data evaluation, rhe report
has been delayed; however, F t has been approved for publication a n d
s h o u l d be d i s t r i b u t e d soon.
A few m i n o r tasks remain to be completed in preparation
for the next thermal data evaluation, Needless to say, these t a s k s are
n o t u r g e n t s i n c e the SA-204 l a u n c h has been delayed.
b.
Base and Aerodynamf c Heating
The SA- 206 maximum aerorherrnad ynamic environment was
p u b 1 ished i n r e p o r t TN-AP-67-174.
An addendum to the S A - 2 0 4 launch environment r e p o r t
(TK-AP-66-79) has b e e n pub1 i s h e d
This addendum c o n t a i n s t w o figures
.
t h a t were rnis labeled and i n c o r r e c t 1 y p l o t t e d in t h e o r i g i n a l document.
These i n a c c u r a c i e s , however, d o n o t affect the o r i g i n a l conclusions a n d
in no way j e o p a r d i z e the SA-204 launch vehicle. The o r i g i n a l c o n c l u s i o n s
were made on the b a s i s of rough p l o t s t h a t were c o r r e c t .
The SA-205 launch vehicle t h e m 1 envfronments have
been p r e d i c t e d and a r e scheduled to be reviewed. The e n v i r o m e n t s are
to b e used for p o s t - f l i g h t data comparisons and r e q u i r e d s t r u c t u r a l
temperature a n a l y s e s , and s h o u l d b e released on s c h e d u l e .
c.
5 - I B High Angle of Artack Aerodynamic H e a t i n g
The manufacturing of o u r m o d e l began in early March
a n d is progressing smoothly. Since spot welding the thermocouples to
t h e i n s i d e o f the c y l i n d r i c a l shell i s n o t the p r o b l e m i t was expected
The use
to b e , t-hat portion of the manufacturing will b e done inchouse.
of an a n a l o g computer TO r e d u c e the t z s t data is b e i n g s t u d i e d .
�' h e S a t u r n V!Voyager
thermal a n a l y s i s for t h e maximum h e a t i n g t r a j e c t o r y has been completed for the continuum flow regime a n d the
r e s u l t s will b e p u b l i s h e d soon.
l i e a t r a t e s f o r the s l i p a n d f r e e molecular flow regime h a v e b e e n calculated up to o r b i t a l ;ltituc?e.
Knudsen
numbers were c a l c u l a t e d f o r variotzs vehicle l o c a t i o a s . TIc nose s e c t i o n
was f o u n d to er?ter t h e sl i~ flaw r e g h e at an a l t i t u d e of approximately
81,000 feet and t h e e n t i r e vehicle was in t h e s l i p flow r e g i m e at a n
a l t i t u d e of 235,000 f e e t . The vehicle entered the free m o l e c u l a r flow
regime a t an a l t i t u d e range of 3 6 2 , 0 3 0 to 603,000 f e e t (depending on
the p o r t i o n of t h e v e h i c l e being cons i d e r e d ) .
The h e a t r a t e s in r h e
trznsition regime, between s l i p and free molecular f l o w , arc being
c a l c u l a t e d as a l i n e a r v a r i a t i o n of the Knudsen number between t h e i r
values a t the e x t r e m e s of the t r a n s i t i o n r e g i o n .
Completion of t h t s
l a s t calculation w l l l complete the h e a t r a t e h i s t o r y f o r the a s c e n t
phase a£ f l i g h t .
The cal c u l a t i a n s of orbital h e e t i n g d u e to radiation
a r e in progress.
A d e s c r i p t i o n of the Voyager vehicle and i t s o r b i t is
b e i n g " i n p u t " t o a Hear Flux computer program.
4.
M T s cel laneous
a.
-
eonductton
Ablation A n a l y s i s U s i n g a Lax-Wcndroff
T y p e D i f fercnce Scheme
Equa Lions have been d e r i v e d for che one-d h e n s i o n a l
heat conduction problem u s i n g a Lax-Wendreff t y p e difference scheme.
The e q u a t i o n s vill b e p r o g r a m e d to check the s t a b i l i t y a t the s u r f a c e
where scme d i f f i c u l t y was encouctered in es tab1 i s h i n g a genes21 express i o n f o r t h e s t a b i l j t y c r i t e r i a b e c a u s e o f the i n t r o d u c r i a n of c e n v t c t i v e
heat t r a n s f e r .
A n a l y t i c r e s u l t s i-ndicate an i n c r e a s e in r k e F o u r i e r
m o d u l u s of at 1 e a s t two to four times t h a t of t h e c n n v e n r i o n a l "forward
d i f f e r e n c e " scheme. T h i s p r o c e d u r e w i l l e v e n t u a l l y b e ex t e n d e d to
i n c l u d e an ablating m a t e r i a l i n an e f f o r t to iessen rhe s ~ r i n g e n t
s t a b i l i t y c r i t e r i a of the " forwzrd d i f f e r e n c e scheme , I 1
b.
Development of a n Orbital H e a t i n g Computer Progran
The e x i s t i n g HTL o r b i t a l heating c o m p u E e r progrzm is
b e i n g m o d i f i e d t o t n c r e a s c irs usefulness a n d v e r s a t i l i t y . These m o d i f i c a r i o n s c o n s i s t of f i v e additional s u b r o u t i n e s and m y be l i s t e d a5
f o l lmrrs:
(i) A n o p t i o n that w i l l allow che u s e r to d i v i d ~a
s u r f a c e of r e v o l u t i o n i n t o a n a r b i t r a r y r , s n h e r of d i s ~ s . Each d i s c i s
t h e n equally s u b d i v i d e d i n t o a n arbitrary number of s u r f a c e c l e m e n t s a n d
t h e L r c e n t r o i d s caLcu!ated.
This i n E o r m a t i o n is T e d i n t o the b a s i c
program which t h e n caI cula t e s the c o r r e s p o n d ing u n i t n u m l s a n d inci.d e n t
heat flux.
�(2)
An option f o r u s i n g o r b i t a l mzchanics f o r a n
(3)
Tables for controlling the s u r f a c e a b s o r p t i v i t y as
of incidence.
e l l i p t i c orbit.
a f u n c t i o n of t h e angle
(4)
An o p t i o n for "selec~ive" plotting of heat
f l u x v e r s u s rime.
(5) An o p t i o n f a r i n t e g r a t i n g incident heat flux
over the en t i r e v e h i c l e .
Mathematical formulation of these sodificatFons was
completed d u r i n g the p a s t two months. Computer p r o g r a m i n g of these
modif i c a t i a n s s h o u l d be c m p l e t e d soon,
c.
A n a l y t i c a l S o l u t i o n of Three-Stream Mixing
R a d i a l t e m p e r a t u r e p r o f i l e s f o r rhe three- s tream m i x i n g
were c o l s truc t c d at several axial l o c a t i o n s . A 1 t h o u g h the p r e d i c t i o n of o n s e t of a f t e r b u r n i n g appears r e a s o n a b l e , a q u e s t i o n e x i s t s as
to the v a l i d i t y of t h e i n p u t f o r the t e m p e r a t u r e and c o m p o s i t i o n .
These input v a l u e s are being checked. outs to determine the e f f e c t on the
p r e d i c t e d s t a r t of a f terburning.
case
d.
A n a l y s i s of Flow F i e l d Solutions Involving Reacting
Fluids
A h e u r i s t i c approach is being followed to u n i f y the
rechniques of t r e a t m e n t of non-equilibrium fluid flows. Included will
b e a linearization technique as a p p l i e d to t h e equations of chemical
r e a c t i o n , a a e t h o d of s o l u ~ i o nf o r the l i n e a r s e t which evolves, an
e x t e n s i o n of the procedures to two-dimensional problems, and r h ~a p p l ic a t i o n t o a f l u i d problem o f a moving s t r e a m w i t h r e a c t i o n s .
e.
Nozzle and J e t Wake Study
The u n s t e a d y equations of motfon used in the t r a n s o n i c
f l o w s o l u t i o n have been c a s t in a d i f f e r e n t form a n d reporgrammed to
h a n d l e f l o w s w i t h f u e l s t r i a t i o n s . A s u c c e s s f u l c a l c u l a t i o n of a
t r a n s o n i c f l o w f i e l d w i t h Q / F g r a d i e n t s has been m a d e . This c a l c u l a t i o n , which d i f f e r s from the supersonic a p p r o a c h previous ly r e p o r t e d ,
i n d i c a t e s t h e same t r e n d , t h e r e b y s u b s t a n r i a r i n g r h i s m e t h o d af a n a l y s i s .
Good c o r r e l a t i o n of the Rocketdyne v e r n i e r e n g i n e
measured data w i t h t h e method of characteristics has been o b t a i n e d f o r
These d a t a , which c o n t a i n d e f i n F t e O/F g r a d i e n t e f f e c t s ,
the e x i t p l a n e .
have been successfully c o r r e l a t e d .
�f.
Equilibrium Real Gas/~ormal Shock Program f o r
S t a g n a t i o n P o i n t Heating
Two s t u d i e s a r e b e i n g conducted.
The f f r s t is to
d e v e l o p c o r r e l a t i o n formulae f o r convective heating as a p p l i e d to e n t r y
into a p o s t u l a t e d Martian amosphere. Essential1 y, t h i s s t u d y involves
performing normal shock c a l c u l a t i o n s and boundary layer solutions for
t h e gas m i x t u r e u n d e r consideration. The h e a t i n g rates w i l l then be
c o r r e l a t e d on t h e b a s i s of f r e e s t r e m entry conditions. A problem
w i t h a modified v e r s i o n of t h e nonnal shock code w a s discovered when
attempting calculations w i t h the Martian atmosphere. This d i f f i c u l t y
has been resolved and work on t h e normal shock c a l c u l a t i o n s is progress i n g . The second s t u d y involves a review of t h e y l ~ y s i c sand f l u i d
mechanics of r a d i a tion-coupled blunt body flow f i e l d s
A solution,
d e v e l o p e d b y Lockheed' s P a l o A t t o Res e a r r h Laboratories , to t h e v i s c o u s
hypersonic shock layer with r a d i a E i o n coup1 ing has h e e n reviewed.
.
g.
Theoretical and Experfmental Investigation of
T e k t i t e Ablation
The g o a l of t h i s s t u d y is to evaluate s u r f a c e effects
d u r i n g ablation of t e k t i t e materials. Three experimental t e s t s u s i n g
a small L O X / I - I ~ engine for s y s tern checkout and La determine p h o t o g r a p h i c
plume geometry h a v e been complefed a: the MSFC T e s t L a b o r a t o r y . Because
oE t h e o p t i c a l p r o p e r t i e s of a LOX/H, plume, some d i f f i c u l t y was expected
with t h e p h o t o g r a p h i c measurements; however, s a t i s f a c t o r y r e s u l t s were
o b t a i n e d by u s i n g i n f r a r e d film t o photograph t h e plumes.
h. Base P r e s s u r e and Environment
The p e r t i o n s of t h i s task now b e i n g i n v e s t i g a t e d involve
:he t u r b u l e n t boundary lager growth on nozzle walls with mass injection
rnd the r e a c t i n g shear l a y e r at the plume boundary.
The Technical Data Release g i v i r - g the r e s u l t s of t h e
v i s c o u s m i x i n g analysis of a sea-level F-1 plume is complete.
Five a d d i t i o n a l analyses of sea-level v i s c o u s plumes
a r e in progress. These i n c l u d e t h e H-l e n g i n e , the S-IC r e r r o mator,
the S - I 1 r e t r o and u l l a g e motors, and the S-IV13 ullage motor. The
investigation of t h e s e s o l i d r n o t ~ r sat s e a level was prompted by t h e
t h r e a t of z c c F d e n t a 1 iglition of anf of these motors while t h e S a t u r n V
is on the pad o r in t h e V e r t i c a l Assembly B u i l d i n g .
�i.
S t a g e Separation Thermodynamics
The t u r b u l e n t flow s e c t i o n of the LMSC/WC
Real Gas
Boundary Layer Program i s b e i n g s t u d i e d e x t e n s i v e l y to ensure accuracy
of t h e method of calculation of all p r o p e r t i e s i n the boundary layer.
Two approximate relations for the s k i n f r i c t i o n c o e f f i c i e n t , based on
the Reynolds number evaluated at: reference conditions, have been
i n c l u d e d i n t h e program for c m p a r i s o n w t t h the r e s u l t s of the iteration scheme.
Results of the technique t o f i n d corrections to an
axisymnetric method-of-characteristics solution of t h e impingement f l o w
f i e l d to approximate the three-dimens i o n a l "spreading" effects of r o c k e t
exhaust plume i m p i n g i n g on a solid boundary are being c o r r e l a t e d and
studied
.
g.
A b l a t i v e Environment Analysis
This t a s k involves t h e development of a method of
anal ys is a n d r e l a t e d d i g i t a l computer program to a n a l y z e the thermal
d ecompos ition- in-depth of c k a r r i n g - t y p e ablative materials.
Also,
v a r i o u s " h o t - j o b s ' h c o n c e r n i n g a b l a t o r a p p l i c a t i o n s a r e performed.
D u r i n g t h i s month wark continued on the decomposition-in-depth program.
A technical review was held w i t h R-AERO-AT to d i s c u s s d e t a i l s of the
work to d a t e and plans f o r future areas to be i n v e s t i g a t e d .
F
.
Unsteady A e s odynarnics Branch
1.
I n f l i g h t Fluctuating Pressure and A c o u s t i c Environments
a. The s u p e r s o n i c phase (M = 1 . 6 to 3 . 0 ) of the 4 p e r c e n t
S a t u r n V f l u c t u a t i n g p r e s s u r e test conducted in t h e AEDC 1 6 - f o o t wind
tunnel was ctsmpleted on I%rch 2 1 , 1967. The s t a t i c pressure c o e f f i c t e n t s
and velocity r a t i o s f o r this test were computed on l i n e and r e c o r d e d on
magnetic t a p e .
This informa tion will be available a s soon as it can be
p l o t t e d on t h e a u t o m a t f c data p l o t t e r a t the MSFC 1 4 - i n c h wind t u n n e l .
The f l u c t u a t i n g pressure data were a l s o recorded on magnetic tape. Data
r e d u c t i o n and a n a l y s i s w i l l b e g i n on the f l u c t u a t i n g pressure d a t a as
soon as computler time and manpower are available.
b. Pre1imir.ary r e v i s e d fluctuating pressure environments
d e r i v e d from the AEDC m o d e l experiment have been g i v e n to R-P&VE-S f o r
s t r u c t u r a l response calculations.
The fluceuaring pressure d a t a r e d u c t i o n from t h e
c.
AEDC experiment is at the following s t a g e :
�Transonic:
(1)
A l l root mean s q u a r e v a l u e s have
been c o m p l e t e d .
(2)
S p e c t r u m a n a l y s i s o f seven p e r c e n t of
available data i s b e i n g c o n d u c t e d
(3)
N o c o r r e l a t l o n analyses have h e ~ n
.
however, it is p l a n n e d
to Let a c o n t r a c t o r do r h e s e a n a l y s e s .
attempted;
Supersonic:
KO data analyses have b e e n i n i t i a t e d .
d.
Task O r d e r No. 9 for Baganoff A s s o c i a t e s was written
f o r r e d u c t i o n of t h e fluctuating p r e s s u r e data on the MSFC/AYES s e p a r a t e d
flow e x p e r i m e n t . Mach numbers from 2.5 to 3.5 were of concern in t h i s
r e q u e s t for cross-psd' s a n d narrow-band t i m e c o r r e l a t i o n s .
Data from t h c
las t task o r d e r were r e c e i v e d chis week and w F l l b e combined with t h e
o t h e r s t e p - h e i g h t and shoulder-angle con£ i g u r a t i o n s i n a n attempt t o
d e f i n e t h e e n v i r o n m e n t a l characteris tics a£ t h e phenomena i n d u c i n g t h e
fluctuzting pressure environments in the various d i s t i n c t p o r t i o n s of
t h e flow in terms oE t h e flow parameters and the geometry.
2.
Launch S i t e A c o u s t i c E n v i r o n m e n t s
a . The AS-202 i n f l i g h t a c o u s t i c datz evaluation r e p o r t
has been completed and will b e d i s t r i b u t e d soon.
b . Wyie C o n t r a c t EAS8-2iO60 e n t i t l e d "Investigation of
t h e Noise G e n e r a t i o n Mechanisms of D e f l e c t e d and U n d e f l e c t e d S u p e r s o n i c
Rocket Exhaust" has been extended for a n o t h e r y e a r . An experiment
a s s o c i a t e d w i t h one o f the tasks of t h i s year's e f E o r t i s in progress.
T h i s experiment w a s d e s i g n e d to measure the n o i s e generated by various
r e g i o n s of a s u p e r s o n i c j e t .
c.
The j e t i.mpingement program f o r a c q u i s i t i o n of a c o u s t i c
d a t a i s nearing complerion.
Three more t e s t s are to be perEormed whes,
t h e p r o b l E m s c o n c e r n i n g adequate e n g i n e o p e r a t i o n a l parzrnc t e r s a r e c o r rected.
Overall sound pressure level t i m e histories have b ~ e nr u n on
t h e c u r r e n t l y available t e s t data. Spectral analyscs a r e t o bc s e l c c t e d
for c o n d u c t a n c e by R-TJXST-ICA.
T e s t s s h o u l d be c o m p l e t e d w i t h i c one
month.
d.
F u l l - s c a l e 5-2 (LOXILH:) horizontal undeflec?ed f l o w
e n g i n e t e s t s a r e to b e conducted at s t a n d number 500 CTL T e s t Laboratory.
The e n g i n e is to b e o p e r a t e d f o r 30 seconds p e r t e s t from 200,000 p o u n d s
t h r u s t dotm to 20,000 pounds t h r u s t i n s t e p s and t h e n i n a t h r o t f l a b l e
m o d e if no problems a r i s e . Nozzle expans ion r a t i o s of 2 7 . 5 : 1, 14: i , a n d
4 0 : T are te b e used in the program. C o o r d i n a t i o n w i t h T e s t L a b o r a t o r y
�is underway to a c q u i r e a c o u s t i c d a t a f r o m the engine area and from the
farfield g r o u n d plane area. These data w i l l be used to obtain the
a c o u s t i c sound source characteristics f o r t h i s undeflected engine in
the chosen aperational modes
.
e.
Acoustic d a t a from AMTF on the Bell-Cone engine n o z z l e
t e s t s a r e k i n g analyzed.
Anomalies in several t e s t s have made necessary two additional t e s t s . From pxeliminary view, the cone nozzles pro-
d u c e d m o r e Energy i n t h e higher f r e q u e n c y bands t h a n d i d the b e l l n o z z l e ;
however, more lm.7 Srequeccy e n e r g y i s observed from the b e l l t e s t s . The
OA SPL v a l u e s show less v a r i a t i o n than the s p e c t r a , s i n c e the energy
e f f e c t i v e l y s h F E t e d to a lower frequency peak value, More d e t a i l e d
analyses are being conducted.
A c o u s t i c data concerning engine clustering e f f e c t s
E i g h t c l u s t e r s with various crus ter diameters and
e n g i n e separations a r e b e i n g c o n s i d e r e d i n s u p p l e m e n t i n g similar d a t a
a c q u i r e d last: year under c o n t r a c t w i t h Martin Company.
have been reques t e d
.
S i n c e m o d e l fabrication is about one m o n t h about one
month away, a c o u s t i c tests f o r the 1120-scale S a t u r n V launch v e h i c l e
will b e g i n soon. Problems w i t h the phase accuracy have arisen because
of a n o i s y t u b e in the cathode follower, P o t t i n g of t h e tube has n o t
solved t h i s problem. Tube inadequacies are blamed for the d a t a s y s t e m
delay.
The MLV s t u d y with the four s o l i d p r o p e l l a n t s t r a p - o n uoFts will
l i k e w i s e be d e l a y e d since t h e y a r e scheduled to follow t h e a c o u s t i c t e s t s
f. High Reynolds Number Equipment (J3RNE): Tests have been
c o n d u c t e d t o determine zhe f e a s i b i l i r y of exhausting into a c l o s e d sphere.
V a r i o u s techniques of reducing t h e pressure and g l o a d i n g have been
t e a t e d in relation to exhausting rhrough a p e r f o r a t e d p i p e a r r a n g r r n ~ n t
i n t o t h e sphere. An o p t i m u m p e r f o r a t e d pipe based on t h e resulting
d i m i n i s h e d ~ c o u tsi c environments and g loading on the model s p h e r e were
s e l e c t e d . Because a£ the marginal environments w i t h r e s p e c t t o personnel
exposure criteria that are p o t e n t i a l l y r e l a t e d to o p e r a t i o n of the f u l l s c a l e f a c i l i t y , a d d i t i o n a l t e s t s a r e t o be performed on a m o d e l sphere
of a more realistic s c a l e ; the latter madel was much more massive a t i d
s i g i d because of the unscaled , thickness. A1 t e r n a t e methods of e n v i r o n mental r e d u c t i o n are to be surveyed and experimentally inves t i g a t e d if
no severe problems i n t e r f e r e ; the o t h e r methods i n c l u d e p a r t i a l a n d / o r
complete s u b m e r s i o n o f t h e sphere in an earth-like m e d i u m , a d u c t e d p i p e
arrangement in ehe form of a c o n v e n t i o n a l muffler d e s i g n , and other
f e a s ible approaches if t i m e and manpower permit.
�3.
Aeraelas t i c C h a r a c t e r f s t i c s
a.
P i t c h Damping
The new dynamic b a l a n c e system, d e s i g n e d for u s e in
TWT, has been completed a n d w i l l b e t e s r e d soon.
Arrangements a r e b e i n g m a d e t o have the data from the p i t c h damping
tests a n a l y z e d by M C u n d e r an e x i s t i n g support contract. The t e s t
is scheduled to r u n the f i r s t t w o weeks in June.
the MSFC 14-inch
b.
S t a b i l i t g Derivatives
The a n a l y s i s of a b ~ d yoE revolution in u n s t e a d y f l o w
is complete a n d a r r p o r l r entitled "A L i n e a r i z e d C h a r a c t e r i s t i c s Method
for S u p e r s o n i c FLOW Pas t Bodies Q£ Revolution Performing Bending Oscill a t i o n s " w i l l b e p u b l i s h e d soon. The i n v e s t i g a t o r s i n this s c u d y were
D. L i u , b o t h of Lockheed. A linearized c h a r a c t e r is L ics: inti Lliod Ilas been ou L l i n e d for supersonic ilow p a s L £ l e x i b l e
b o d i e s of revolution which p e r f o r m l ~ wfrequency b e n d i n g o s c i l l a t i o n s
This approach i s an e x t e n s i o n of previous work by Oswatitsch and
Erdmann (1954) and P l a t t e r a n d Sherer ( 1 9 6 7 ) f o r r i g i d b o d i e s t o t h e
c a s e of e l a s t i c b o d i e s .
This extension r e q u i r e s a reformulation of t h e
vhole problem in a w i n d - f i x e d c o o r d i n a t e system,whereas t h e previous
approaches p e l r m i t t e l l t h e use of body-fixed c o o r d i n a t e s , A s s h o w n b y
Hoffman and P l a t z e r (1966) a T a y l o r - s e r i e s e x p a n s i o n has to b e p e r formed i n w i n d - f i x e d c o o r d i n a t e s to o b t a i n a c o r r e c t formulation of
t h e boundary conditions at: t h e o s c i l l a t i n g b o d y , t h u s g r e a t l y complicating t h e r z s u l t i n g e x p r e s s i o n s . Furthermore, i n t h e w i n d - f i x ~ dformular i o n t h e e q u a t i o n f o r the o s c i l l a t i n g body s u r f a c e c e a s e s to a p p l y in
t h e n e i g h b z r h o o d o f rhe apex caus i n g compl i c a t i o n s in formulating
g e n e r a l l y val i d s t a r t i n p c o n d i t i a n s
M. F. P l a t z e r a n d
.
.
4.
Panel F l u t t e r
a. An investigation of n o n l i n e a r oscillations of a t h r e ~ dimensional. F l u t t e r i n g platc i n underway u s i n g thc E. H. Dowel1
analytical method for S a t u r n IB vehicles 204 to 2 0 7 . The p r o b l e m of
two- a n d three-dimensional p l a t e s i n a h i g h s u p e r s o n i c f 1ow ilndergoing
l i m i t e d oscillations has b e e n s t u d i e d by Dowell up t o t h e p l a t e l e n g t h
a n d w i d t h r a t i o of two.
The present: s t u d y involves t h e a p p l i c a t i o n of
ow ell's method to l a r g e r characteristfc v a l u e s which e x i s t for t h ~
S a t u r n IB v e h i c l e ,
b . A l l of the d a t a frcm t h e wavy-wall p a n e l i l u t t e r t e s c s
c o n d u c t e d in t h e dmes Research c e n t e r ' s 2 by 2- Eoor t m n s o n Fc w i n d
tunnel bavc been r e c e i v e d by NSFC, and f u r t h e r d a t a r e d u c t i o n w i l l b e
c a r r i e d o u t in the near f u t u r e .
�5.
S a t u r n V Grou rid W-ind s
Data r e d u c t i o n for the f u e l e d w e i g h t condition i s c o n t i n u i n g to p r e d i c t full-scale b e n d i n g moments for t h r e e vehicle s t a t i o n s
and d e f l e c t i o n s at t h e damper c o n n e c t s t a t i o n versus w i n d velocity.
E I r . Moore of PGtW r e q u e s t e d t h i s i n f o r m a t i o n to q u a l i f y t h e damper
reconnect c a p a b i l i t y .
D u r i n g the i n i t i a l phase of these data analyses, it was
observed t h a t t l ~ tr e s t d a t a from the u p p e r model measurement s t a t i o n
c o n t a i n s poss i b l y two higher f r e q u e n c i e s superimposed on the f i r s t
cantilevered frequency. It is surmtsed t h a t t h e s e h i g h e r f r e q u e n c i e s
a r e s e c o n d and t h i r d cantilevered f r e q u e n c i e s ; however, because of d a t a
r e d u c t i o n and Computation L a b o r a t o r y scheduling problems, t h e s e d a t a
have n o t bcen cornplerely analyzed. 4 q u i c k look, however, i n d i c a t e s
t h a t t h e deflections at t h e damper s t a t i o n d u e to rhesc h i g h e r f r e q u e n c i e s
will b e small compared t a the d e f l e c t i o n s p r o d u c e d by t h e f i r s t mode f r e q u e n c y , A t p r e s e n t a p r e l i m i n a r y report c o n t a i n i c g p r e d i c t e d b e n d i n g
moments a ~ deflcctians
d
based upon t h e f i r s r mode o n l y is being m i t t e n
and will b e fallowed by a f i n a l r e p o r t c o n t a i n i n g rhe h i g h e r f r e q u e n c y
data when a v a i l a b l e .
VI.
A S T R O D Y N M C S AND GUIDANCE THEORY DIVISION
A.
S c i e n t i f i c Advisory Office
1.
In-House
(a) A discuss i o n of a papcr by Chen and Yates w i l l appear
in the ASPE Basic E n g i n e e r i n g along w i t h t h e p a p e r .
( b ) A p a p e r e n ~ i t l e d "on ~kamura's Uniqueness Theoremti has
been accepted for p u b l i c a t i o n by the Proceedings of the American Math
S o c i e tly.
(c)
The p a p e r , "Eps i l o n - F i x e d S t a b i l i t y and Vector Liapunov
Functions, " has been subrnFtted to the Proceedings of the .4merican M a t h
S o c i e t y . In the p a p e r necessary and s u f f i c i e n t c o n d i t i o n s are obtained
f o r an i n i t i a l c o n d i t i n n set to correspond to s o l u t i o n s bounded b y a
f i x e d bound.
The concept is extended to v e c t o r Eiapunov f u n c t i o n s where
suf fLc i e n t c o n d i t i o n s a r e o t tained
.
( d ) The p a p e r , '%n t h e Equivalence of C e r t a i n S t a b i l i t y
P r o p e r t i e s , " c l a r i f i e s some of the known stability d e f i n i t i o n s and
shotcs t h e r e l a t i o n w i t h the right-hand s i d e s .
�(el Concepts in f i n i t e s t a b i l i t y are under c o n s i d e r a t i o n , and a comprehensive unified summary of the r e s u l t s is b e i n g
completed. Necessary and s u f f i c i e n t c o n d i t i o n s a r e o b t a i n e d f o r finite
s t a b i l i t y , and v e c t o r Liapunov f u n c t i o n s are shown to b e extremely
us e f u 1.
(George a n d Gund ers on)
2.
Contracts
a.
Brown U n i v e r s i t y ( C o n t r a c t MS8-11264)
I n f a n t e is c o n t i n u i n g h i s work on the s t a b i l i t y of
t i m e varying systems. He is now c o n s i d e r i n g equations b y averaging t h e m
through a Liapunov f u n c t i o n and exploFting the Wazewski i n e q u a l i t y . h
few p r o m i s i n g results have been o b t a i n e d .
Meyer is c o n t i n u i n g l z i s research on he e x i s t e n c e of
global L i a p u n o v f u n c t i o n s . At present it seems 1:kely t h a t some of
t h e r e s u l t s obtained f o r two-dimensional sys terns can be c a r r i e d over
to the n-dimens i o n a l Mors e-Smale s y s terns.
Weiss is working on a cmprehens i v e t h e o r y of c o n t r o l l a b i l i t y f o r nonlinear ttme-varying d i f f e r e n t i a l s y s t e m s which c o n t a i n
delays. One of the main r e s u l t s w i l l be of the following form: R non1inear delay-differential s ys tern is controllable w i t h r e s p e c t to all
i n i r i a l f u n c t i o n s in a neighborhood of t h e origin of a given f u n c t i o n
space B if its " f i r s t variation" is completely controllable with r e s p e c t
to B.
Combining t h i s r e s u l t w i t h a n a p p r o p r i a t e theorem on s L a b i l i t y
u n d e r perturbing forces will p r o d u c e a global controllab i L i t y c r i t e r i o n
for a large class of delay-differential systems, These r e s u l t s are
expected to s t i m u l a t e research on o p t h a 1 c o n t r o l f o r s u c h s y s t e m s f n
i ~ h i c hthe t a r g e t set is in a Banach space rather than in Euclidean s p a c e .
Miller i s c o n r i n u i n g h i s work on weak solutions of
n o n l i n e a r h y p e r b o l i c p a r t i a l d i f f e r e n t i a l e q u a t i o n s . This inwes t i g a r i o n
is directed toward f i n d i n g c x i s t e n c e and uniqueness theorems in e q u a t i o n s
w i t h more than two i n d e p e n d e n t variables.
b.
Drexel I n s t i t u t e ( C o n t r a c t M S 8 - 2 0 3 4 7 )
Most of our e f f o r t s d u r i n g F e b r u a r y a n d & r c h were
devoted to attempts t o prove a theorem conjectured in t h e m o n t h l y r e p o r t
f o r J a n u a r y . Only limited p a r t i a l r e s u l t s have been o b t a i n e d . These
v i l l b e announced l a t e r .
�c.
G e n e r a l P r e c i s i o n Aerospace ( C o n t r a c t NAS8-20026)
Work has been c o n t t n u i n g in the develaprnentz of the
d i g i t a l programs t h a t w i l l normalize a time-dependent H a r n i l t o n i a n to
second order.
The p r e s e n t s t a g e of t h e development is in the area of
us ing t h ~
characteris t i c matrix of the related l ir.ear d i f r ' e r e n t i a l equat i o n to o b t a i n the r e q u i r e d p e r i o d i c transformation matrix g i v e n b y
F l o q u e t Theory.
3
(Dearman)
Optimization Theory Branch
1.
Sacurn V / ~ o ~ a g eShroud
r
Study
A m ~ m o r a n d u mdocumenting preliminary r i g i d body c o n t r o l
responses a n d a s s o c i a t e d b e n d i n g moments f o r t h e S a r u r n VlVoyager
( 4 5 foot c y i i n d r i c a l payload) w i t h a t t i t u d e control sys tern w i l l soon
b e p u b l i s h e d . The memorandum p r e s e n t s d a t a f o r u s e in shroud d e s i g n ,
e x t e n d i n g e a r l i e r s t u d i e s and i n c l u d i n g seven t i m e p o i n t s a l o n g t h e
f i r s t s t a g e t r a j e c t o r y f ~ the
r d e s i g n w i n d c o n d i t i o n s , 95 p e r c e n t a r c h
w i n d p r o f fie, and maxfmum wFnds f o r currently p l a n n e d miss i o n s ,
December 95 percent wind p r o f i l e .
Future e f f o r t s will be d i r e c t e d
toward establishing c a p a j i l i t y of various s h r o u d l e n g t h c o n f i g u r a t i o n s
to tiriths tand g i v e n w i n d c o n d i t i o n s . This information w i l l b e u s e d i n
launch p r o b a b i l i t y s r u d i e s
.
2.
Analytic R e d u c t i o n of Optimal Trajectory Problem
A computer program u s i n g a newly discovered transformation
which r e d u c e s the determination of an o p t i m a l vacuum f l i g h t t r a j e c t o r y
t o the s o l u t i o n of n i n e f i r s t o r d e r d i f f e r e n t i a l e q u a t i o n s i n s ~ e a dof
twelve and the i s o l a t i o n of two unknowns i n s t e a d of f i v e w i l l be comp L e t e d soon. This program s h o u l d c o n s i d e r a b l y reduce rhe t i m e r e q u i r e d
to compute an optimal trajectory. At: present an e f f a r ~to check the
new program a g a i n s t an e x i s t i n g program is underway. An i n s t a b i l i t y in
t h e i s o l a t i o n p r o c e d u r e which is used to s a l v e the two-point boundary
value p r o b l e m has been e n c o u n t e r e d .
The i s o l a t i o n scheme works corr e c t l y for c e r t a i n problems b u r founders on others. Improvements on
he i s o l a t i o n scheme a n d other component parts ~f the over-all program
are under study.
An attempt t o m o d i f y the analytical equations used in
this program to a more convenient form is b e i n g m a d e . No new integrals
of the s y s t e m have been found and p r e s e n t work is d i r e c t e d toward t h e
d i s c o v e r y of a c a n o n i c a l transformation which i n c o r p o r a t e s t h e k n o m
t h r e e integrals i n t o Lhe Harniltonian by direct e l i m i n a t i o n of variables
c o n j u g a t e t3 the momenta represented by these i n t e g r a l s .
�3.
Voyager S p a c e c r a f t A t t i t u d e C o n t r o l
S t u d i e s are p r e s e n t l y i n progress on functional d e s i g n
of t h e a t t i t u d e c o n t r o l s y s t e m for t h e Voyager spacecraft. Modes of
c o n t r o l b e i n g investtgated i n c l u d e a c q u i s i t i o n of c e l e s t i a l r e f e r e n c e s ,
maneuvers p r e p a r a t o r y t o m o t o r l i r i ~ ~ g sand
,
c r u i s e u r l i m i t cycle operation.
Disturbance t o r q u e s to b e con; i d e r e d i n i n t e r p l a n e t a r y fl i g h r
a n d Mars o r b i t have been computed and g a i n s , t h r u s t e r size, e t c . , are
b e i n g parameterized t o minimize f u e l consumption and d e m o n s t r a t e a d e q u a t e
performance u n d e r time and a c c u r a c y requirements a £ the m i s s i o n . T h e
r e s u l t s of t h i s p r e l F m i n a z - y p h a s e of the s t u d y w i l l be p u b l i s h e d a t t h e
end af A p r i l .
4,
Reusable L a u n c h V e h i c l e Control
A paper e n r i t l e d " C o n t r o l S y s t e m s f o r R e u s a b l e Launch
Vehicles" has b e e n p r e p a r e d for p r e s e n t a t i o n at tlre SAE Space Technology
Conference to be h e l d on May 9-12 at Palo Alto, C a l i f o r n i a .
The paper
c a n c l u d e s t h a t t h e r e a r e apparently no c o n t r o l requirements f o r t h i s
class of v e h i c l e w h i c h demand development of new rechnology a r e a s ; howe v e r , s e v e r a l a r e a s of r e u s a b l e v e h i c l e d e s i g n can d i r e c t l y b e n e f i t h y
early integration of c o n t r o l capabilities.
a.
S a t u r n VlVoyager Load R e l i e f
Objective:
To d e v e l o p an e f f e c t i v e load r e l i e f
c o n t r o l system f o r S a t u r n V/Voyager.
T h e c o n t r a c t o r made an oral p r e s e n s a t i o n of the r e s u l t s
o f t h e c u r r e n t s t u d y on F e b r u a r y 14. The f i n a l r e p o r t has bcen a p p r o v e d
a n d copies w i l l soon b e d i s t r i b u t e d . Work on t h e s t u d y e x t d n s ion, w h i c h
\#:ill apply t h e control t e c h n i q u e to t h e current 4 5 - f o o ~paylozd conf i g u r a t i o n a n d c o r r e c t t w o d e f i c i e n c i e s o f the o r i g i n a l c o n t r o l s y s t e m ,
has been delayed p e n d i n g the r e l e a s e o f funds.
b.
Development of T o l e r a n t C o n t r o l System
Objective:
To develop centroll~rswhich max~rnizc thc
t o l e r a n c e to veh iclc and environmental parameter v a r i a t i o n s .
The technical s t u d y is complete and t h e F i n a l r e p o r t
d r a f t has b e e n r e v i s e d . R e s u l t s of the s t u d y i n c l u d c t h e development
o f a b a s i c s y n t h e s i s t e c h n i q u e u s i n g a h y b r i d computer s i m u l a t i o n nncj
the a p p l i c a t i a n of t h i s s y n t h e s i s t e c h n t q u e in s e l e c t i o n o f a controller
to meet s p e c i f i e d c o n d i t i o n s . The controller was r e l a t i v e l y s i m p l e i n
concept, m e t the general requirements, a n d a p p e a r e d to b e relarively
tolerant to paramctcr variations.
�Thc synthesis rechnique needs f u r t h e r development
in b r o a d e n i n g the class of c a n d i d a t e c o n t r o l s y s tems u n d e r c o n s i d e r a tion, and in inregraring f l e x i b l e vehicle requirements into the program.
Yo funds a r e available to e x t e n d the c o n t r a c t .
6.
mortlr American A v i a t i o n ( l A S 8 - 2 1 0 7 7 )
Objective:
To e x t e n d t h e c a p a b i l i t y of a quas i-1 i n e a r i z a t i n n t e c h n i q U P f o r computing f i n i t e - t h r u s t: optimal trans f e r s
.
T h i s is a new contract exrending the work o f c o n t r a c t
SAS8-20238.
D u r i n g t h e first r e p o r t i n g p e r i o d of c o n t r a c t 1JAS8-21077,
m o d i f i c a t i o r l s were i n i t i a t e d to rewrlte t h e existing quasl-llnear orbit
transfer program in F o r t r a n R f o r u s e on the IBM 360 s y s tern.
The program
for s inglr center, t h r e e - d i m e n s i o n a l transfers is a n t i c i p a t e d ta advance
t o c h c c k o u t s t a t u s w i t h i n three months.
7,
Corncll Aeronautical Laboratory (NAS8-18054)
Oh j u c t ive: To d e t e r m i n e the Eras i b i l i t y of applying a p timl
c o n t r n l theory to tile s ynthcs i s of lau5ch vehf che c o n t r o l sys tems
.
Because of some p r o m i s ing new developments which have arisen
in the c o u r s e o f thc investigation ( e . g m r a m o r e d i r e c t formulation of
t h e s t o c h a s t i c o p t i m a l c o n t r o l p r o b l e m ) , it has been necessary to proceed
a t a slower r a t e than was o r i g i n a l l y e n v i s i o n e d to achieve good u t i l i z a tion of t h e new r e s u l t s . To complete the work originally i n t e n d e d t o
b e accompPished under khis c o n t r a c t , the contractor has requested a
na-cos t e x t e n s i o n of three months ( t o J u n e 30, 1967).
8,
Sys rems 'I'echnology,
Lnc.
(XAS8-11419)
Objective:
To d e t e r m i n e the L i m i t a t i o n s of conventional
c o n t r o l s y s t e m s f o r v e h i c l e s e x h i b i t i n g a l a r g e amount of F n t e m o d a l
coup l ing
.
The d r a f t of the final r e p o r t on t h i s c o n t r a c t , which was
due l a s t December, was r e c e i v e d on March 30 a n d i s b e i n g r e v i e w e d .
Objective: Te s t u d y the a p p l i c a t i o n of the S a t u r n V j V o y a g e r
l o a d r e l i e f s y s t e m a n d other l o a d r e l i e f s y s t e m s t o the S a t u r n V/Apollo.
Work on t h i s c o n t r a c t was i n i t i a t e d or March 2. E f f o r t s
f a r have b e e n d i r e c t e d toward collection and preparation of thc i n p u t
d a t a ( t h e v e h i c l e u s e d in t h e s t u d y will be chc SA-505), preparation of
a s t u d y p l a n a n d schedule, and definition of c o n v e n t i o n a l c o n t r o l l e r s to
be u s e d in t h e s t u d y , b o t h as c a n d i d a t e s and =or comparslson of performanct.
w i t h a d v a n ~ e d cuntroll e r s .
so
�10, N o r t h r o p S c h e d u l e O r d e r No. 26
a.
A n a l y t i c Design of Vehicle Control Systems
Objective:
To i n v e s t i g a t e a n a l y t i c a l d e s i g n techniques
for l i n e a r systems.
A s w a s p r e v i o u s l y r e p o r t e d , t h i s work i s being t e r m i n a t e d
b e f o r e completion of a l l a s s i g n e d tasks because of the w o r k load r e q u i r e d
on Voyager.
A t e r m i t a l r e p a r t a n the r e s u l t s of L11e s t u d y t o d a t e
has been t r r i t t e n and is b e i n g reviewed.
b.
C o n t r o l and Separation S t u d i e s of t h e Saturn V/Voyager
O b j e c t i ~ e : To i n v e s t i g a t e load r e l i e f systems f o r t h e
S a t u r n v l ~ o y a g e ra n d t o provide separation dynamic s t u d i e s f o r the
Voyager s h r o u d d e s i g n s t u d y .
Checkout of the program developec f o r s i m u l a t i o n of
"over-the-nose" s h r o u d separation has been c m p l e t e d and s e l e c t e d c a s e s
have been run w t t h t y p i c e l values of various parameters o f m o t i o n .
11.
Narthrep Schedule O r d e r S o . 35
To d e s i g n and assess the p e r f o m a n c e o f a t t i tude control s y s t e m s f o r t h e Voyager xhich o p e r a t e d u r i n g p r o p u l s i v e
Objective:
maneuvers.
This s c h e d u l e o r d e r was i n i t i a t e d d u r i n g this r e p o r t i n g
C o n t r o l systems are to b e d e s i g n e d functionally for b o t h t h e
period.
l i q u i d a n d sol i d s p a c e c r a f t configurations. S t u d y of the pertinent phase
B documentation, formulation of the s t u d y approach, and p r e p a r a t i o n of
the necessary computer programs has been comple red. Performance of
attitude/attitude-rate s y s t e m s d u r i n g t h e arrival d a t e separarion maneuver
is b e i n g analyzed.
C.
A s trodynarnics Branch
1.
I n t e r p l a n e t a r y T r a n s i t Studies (In-Rouse)
a. Work has been completed on the extraction a£ a sing1.e
p r e c i s i o n , power series integration, n-body deck from t h e d o u h l e p r c c i s i ~ n
versior.. Work is contFnuing on the s t u d y of a " b e s t " i s o l a t i o n
r o u t i n e f o r u s e in both o f t h e s e d e c k s . In c o n j u l c tion w i c h t h i s , a
program f o r t h e IBM 1130 has been written, coded, and checked o u t which
�c r ~ r n i j l l t c . , o r b i t ~ lp a r m e t e r s a r , d t h e a s s o c L a t e d v z i u e s of B a T a n d E.R at
: I ; ~ r ias functions o l t h e injection c o n d i t i o n s at: e a r t h .
A KASA technical memorandum rghicli p r o v i d e s a sampl c.
V0q'agc.r trajecrory f o r u s e in p r e l i m i n a r y d e s i g n work is in r e p r o s c l c t i o n
The r e p o r t c o n t a i n s an cxplana t i o n of t h e process tlut w a s u s e d in the
s i . l c . c ~ i o nof he tra j i s c t o r y , problems i n v o i v e d w i t h i t s ger,ern t i o r , ,
and zr22s of f u t u r e s t u d y which n e e d co b e explascd in o r d e r to provide
b c t t c r sarnpte trajectories.
I n the meantime, work has been i n i r i a t e d to
p r o v i d e t h r e e trajectories f o r each of the four Launch o p p o r t u n i t i e s :
1973, 1 9 7 5 , 1 9 7 7 , a n d 1979. The t r a j e c t o r i e s will, i n general, be t a k e n
one from t h e b e g i n n i n g , one near the middle, a n d one from t h e end o f a
l a u n c h p e r i o d w i t h i n each o p p o r t u n i t y . I t is p l a n n e d to p u b t i s h t h e s e
t r a j e c t o r i e s in four reports c o r r e s p o n d i n g to the f o u r l a u n c h opportunities
( 3 t r a j e c t o r i e s in each r e p o r t ) .
b. E x t e n s i v e checks a r e b e i n g m a d e of "he AV requirements
for separatian of a r r i v a l d a t e s and for b r a k i n g into o r b i t and o r b i t
t r i m maneuvers. The effects of Mars o b l a t e n e s s on Voyager t y p e o r b i t s
a r c a l s o be'lng s t u d i e d .
c.
C e r t a i n m i n o r modifications have b e e n incorporated into
the Marshall Interplanetary C o n i c Trajectory Program.
These m o d i f i c a t i o n s , which a r e concerned p r i m a r i l y w i t h the o u t p u t capab i l i t i e s o f
t h e program, w i l l p r o v i d e t h e u s e r a more complete d e s c r i p t i o n of the
generated trajectory. Work continues on the incorporation of an autonm t i c p l o t t i n g routine i n t o t h e Marshall Interplanetary Conic Trajectory
Program w h i c h will e n a b l e mechanical plotting of graphs resulting from
t h e g e n e r a r i a n of s e l e c t e d trajectory parameters.
d.
Energy requirements for trans-Mass inject ion and arrival
as functions of l a u n c h d a t e arc b e i n g p r e p a r e d for graphical p r e s e n t a t i o r
2
S u p p o r t Contract
a.
Cislunar Orbit Studies
A l 1 c i s l u n a r p e r i g e e s t a b i l iza t i o n s t u d i c s havi. hc t.r:
c o m p l c r e d a n d t h e r e s u l ~ sa r e p r e s e n t l y being corr,piled into a c m n r c hensive, three-part report which w i l l i n c l u d e :
s t a b i l i z a t i o n Sy o~tini
i n g the l a u n c h time, t h e p e r i o d , a n d the i n i t i a l e a r t h - m o o n p r o b e n n g l r
s t a b i l i z a t i o n b y u s i n g a t r a n s v e r s e velocity i n c r e m e n t at a p o z e e ; a n d
s t a b i l i z a t i o n by u s i n g b o t h transverse and r a d i a l velocity incremeazs
at a p o q e e .
�b.
Interplanetary Transit Studies
The m o d i f i e d v e r s i o n of the Harshall Interplanetary
Conic Trajectory Program for b o t h powered and unpowered f l i g h t s has been
complete1 y checked o u t a n d is operational for direct Ear th-Mars-Ear th
miss i n n s a n d for e i t h e r Venus-Mars-Earth or Earth-Mars-Venus t r a j e c t a r i e s
f o r t r a n s f e r s u s i n g e i t h e r option 1, 2 , o r 3 ( c o n s t a n t C3, s t r a i g h t run
or minimum C3) for the f i r s t l e g of t h e trajectory and o p t i o n 1 or 3 f o r
t h e s e c o n d leg. F u r t h e r additions te the deck are b e i n g made so t h a t t h e
final v e r s i o n will allow t h e u s e of any combination of o p t i o n s 1, 2 , and
3 for c a l c u l a t i n g the i n d i v i d u a l s i n g l e leg t r a j e c t o r i e s t h a t a r e used
in d , e t e r m i n i n g the trajectory requirements for s o u n d - t r i p f l y b y or swingby
m i ss ions
.
The study o f the in-flight velocity impulse r e q u i r e d t o
a c h i e v e an eight-day separation of a r r i v a l times f o r t w o Saturn V vehicles
d e p a r t i n g e a r t h an a trajectory LO Mars has been comple r e d .
Work is nearing completion on the generation of l a u n c h
o p p o r t u n i t y graphs f o r t h e years 1 9 7 3 , 1975, 1977, a n d 1979. By p l o t t i n g
and cross-plotting data generated by the JPL conic program, t h e completed
g r a p h s w i l l show all p o s s i b l e launch p e r i o d s available d u r i n g each
opportunity
each opportunity b e i n g d e f i n e d by r ~ s t r i c t i o n sof the
declination n f t h e outgoing asymptote, the. l a u n c h energy (C,),
a n d the
a r r i v a l hyperboltc excess velocity at Mars.
-
A study of various f l i g h t parameters f o r the type I1
Earth-Mars t r a j e c t o r i e s in the 1973-1979 time p e r i o d has b e e n i n i t i a t e d .
The r e s u l t s of t h i s s t u d y w i l l be t h e p r e s e n t a t i o n of these parameters
as functions c ~ f t h e l a u n c h d a t e s d i s t r l ' h r i t e d 1 5 d a y s to ~ a c hs i r i ~n f t h p
departure d a t e s that allow minimum energy t r a n s f e r .
Parameters t o b e
c o n s i d e r e d i n c l u d e : arrival date, flight time, declination, righr
ascens ion o r the d e p a r t u r e and arrival asymptotes relative to the central
p l a n e t ' s equator and equinox, c~mmunication d i s t a n c e at a r r i v a l , d e p a r t u r e e n e r g y , h y p e r b o l i c excess s p e e d at a r r i v a l , i n c l i n a t i o n of the flight
plane t o t h ~e r l i p t i c , t.he angl P between She depart- us^ asympt-ote a n d
rhe s u n ~ e a r ~vhe c t o r , and the angle between the a r r i v a l a s y m p t o t e and
t h e Mars-sun v e c t o r ,
D.
G u i d a n c e Theory Branch
1. S u p p o r t C o n t r a c r S t u d i e s
a.
Power S e r i e s S o l u t i o n for I n i t i a l Lagrange Multipliers
The energy, momentum, and transversal i t y cond iti o n s ,
expanded in t h i r d - o r d e r T a y l o r s e r i e s , have been expressed e x p l i c i t l y
i n terns oi the Lagrange multipliers.
Computer programs have been coded
�f o r evaluating the c o e f f i c i e n t s of the mu1 t i p l i e r s in these s e r i e s , and
t h e y a r e p r e s e n t 1 y o p e r a t i o n a l f o r the energy a n d two transversal ity
c o n d i t i o n s . Work continues on the coding and "debugging" of programs
f o r the o t h e r s e r i e s c o e f f i c i e n t s .
b.
Quasi-Optimal Guidance S t u d y
Various cut-of f surfaces are b e i n g inves t i g a ~ e d i n
c o n j u n c t i o n with the quasi-optimal guidance scheme. The ( r , v , 0) cut-a£ f
s u r f a c e has been checked out; the (r ,v, 2 , i) and (r ,v,3, i, n> s u r f a c e s a r e
be in^ checked o u t .
Energy-angular momentum ( C s , C1) and energy-angular
m o m e n t u m inclination (C3, Cl, i) surfaces are b e i n g formulated,
c.
Voyager Project S u p p o r t S t u d i e s
Work has been inf t i a t e d to c a l c u l a t e S a t u r n V/ Voyager
a s c e n t t r a j e c t o r i e s w i t h an escape energy of 32.5 km'/sec2
at l a u n c h
a z i m u t h from 45 to 115 degrees (in 5-degree increments) e a s t of n o r t h .
These trajectories w i l l then b e run (by in-house personnel) from e a r t h
p a r k i n g o r b i t to Mars to simulate Voyager trajectories.
A m o d i f i e d form of the lunar hypersurface has been u s e d
for t a r g e t i n g of Mars t r a j e c t o r i e s . A 100 km out-of-plane p e r t u r b a t i o n
of the injection point in parking o r b i t r e s u l t e d in only a 3000 km error
in the m i s s d is tance at Mars.
2.
Contracts
a.
Boeing
-
Rendezvous Guidance
The f i n a l r e p o r t ? m s been received.
b.
Lockheed
-
Rendezvous Guidance
The contract is being renewed and there was no work
done d u r i n g t h i s p e r i o d .
c.
Uand e r b i l t U n i v e r s i t y
Work is c o n t i n u i n g on o b t a i n i n g s u f f i c i e n t c o n d i t i o n s
f o r the Mayer form of the extended Balza problem. The work of B l i s s and
Hes t e n e s on the s i n g l e s t a g e Mayer problem has been s t u d i e d . It i s
h o p e d that the Mayer form of the extended Bolza problem can be t r a n s formed such t h a t it becomes a s i n g l e stage Maycr problem.
�d.
General P r e c i s ion
For the low-thrus t g u i d a n c e problem, the f e e d b a c k g a i n s
d o not produce a s i g n i f i c a n t increase in a c c u r a c y over the open-Loop
approach when o n l y t h e energy at c u t o f f i s s p e c i f i e d . The reason for
this is t h a t t h e open-loop g u i d a n c e gives fairly good r e s u l t s when only
the t e r m i n a l e n e r g y fs s p e c i f i e d ; thus to f u r t h e r test the approach, an
a d d i t i o n a l c o n s t r a i n t such a s the r a n g e angle is b e i n g added to the
guidance s i m u l a t i o n .
3.
In-House Studies
a.
Voyager S t u d i e s
A terminal g u i d a n c e s e n s i t i v i t y s tud y for t h e Voyager
mission has been completed and the results a r e being p u b l i s h e d . A
s t u d y was performed to determine the AV needed to accomplish the
separation of arrival t i m e of the two s p a c e c r a f t a t firs f o r a l l t h e
launch o p p o r t u n i t i e s . In t h i s s t u d y , c o n i c approximations were used;
however, a check c a s e was computed on the JPL space d e c k t o v e r i f y that
c o n i c approximations were s u f f i c t e n t f a r the s t u d y .
A computer program h a s been developed which c a l c u l a t e s
the m i n i m u m change in v e l o c i t y (AV) needed to t r a n s f e r from a s p e c i f i e d
approach hyperbola to a s p e c i f i e d o r b i t about Yars. R o t a t i o n of p e r i aps is of tb.e p a r k i n g o r b i t away from t h e p e r i a p s i s a £ the approach
hyperbola is c o n s i d e r e d in o r d e r to determine the AV p e n a l t y incurred
by placing the p e r i a p s i s of t h e parking o r b i t near one of the terminators
b.
Various forrnulations of the bas ic Fletcher-PoweP I
m i n i m i z a t i o n technique have been t r i e d on a set of t e s t f u n c t i o n s t o
f i n d one y i e l d i n g t h e h i g h e s t rate of convergence. Good convergence
rates have been achieved b u t the ultimate s p e e d i s n o t b e l i e v e d to
have been reached. The generalized secant m i n i m i z a t i o n t e c h n i q u e has
b e e n shown to be 2 to 4 times f a s t e r than Newton-Raphson when c m p a r c d
on the b a s i s of function evaluations. A mod if i e d s e c a n t t e c h n i q u e is
now b e i n g ~ p p l i e dto the two-point boundary value p r o b l e m a r i s i n g in
t h e calculztion of op titnal t r a j e c t o r i e s .
c. To fur=l-ler i n c r e a s e the s p e e d of the o p r i m a l t h s u s t coast-thrust program t h e completely g e n e r a l closed-form s o l u t i o n f o r
t h e s t a t e vzriables and t h e Lagrange multipliers across a c o a s t arc
have been a d d e d .
�d.
E f f o r t has been e x p e n d e d i n s t u d y i n g t h e approaches to
rhe s o l u t i o n of the boundary val.ue problem which involves c o n v e r t i n g the
boundary value p r o b l e m to a d i f f e r e n t l a 1 e q u a t i o n and i n t e g r a t i n g the
d i f f e r e n t i a l e q u a t i o n to o b t a i n a solution. This approach s h o u l d a d d
more speed and e f f i c i e n c y when more difficult problems with switching
f u n c t i o n s are attempted.
VIL.
DYNAMICS AND ETIGHT M E C W T I C S DIVISION
A.
Multi-Projects
-
Dynamics and Control
A e r o e l a s t i c Load Growth: This s t u d y i s b e i n g made to determine
t h e o r i g i n of rhe unexplained external body moments observed during the
Saturn 1 Elock 11 f l i g h t s . These e x t e r n a l moments which arc necessary
to mainrain the r e c o r d e d f 1 i g h t c o n d i t i o n s are s ignif i c a n t l y Large
( 1 0 0 , 0 0 0 to 700,000 N-MI and have provoked much speculation as to t h e i r
cause.
A s t a t i c a e r o e l a s t i c load growrh a n a l y s i s o f rhe S a t u r n I
Block II vehicles has tentatively shown tmnat t h e aeroelasric e q u i l i b r i u m
l o a d i n g induces a n aerodynamic moment which has not p r e v i o u s l y been
i n c l u d e d in f l i g h t mechanics.
Comparisons between t h e observed £1i g h t
test unexplained moment and t h i s a e r o e l a s t i c moment i n d i c a t e good agreem e n t in magnitude a n d d i r e c t i o n for a l l f l i g h r s in both p i t c h a n d yaw.
These f i n d t n g s , a l o n g w i t h a method for i n c l u d i n g aeroelastic l a a d
growth in the p r e s e n t six-degrees -of -freedom trajectory simulation
programs ( w i t h minor r e v i s i o n s ,are b e i n g documented in a technical
r e p o r r to be completed soon.
(DD)
>
B.
Saturn V
I.
M i s s ion P r o f i l e
S-IVB L u n a r Impact S t u d y : At the reqaest of NASA H e a d q u a r t e r s , a s t u d y is in p r o g r e s s to evaluate t h e probability of S-ITJB
1u n a r impact for t h e l u n a r m i s s ion. The two primary ob sect ives of the
s t u d y a r e to determine rhe maneuvers r e q u i r e d t o assure no l u n a r i m p a c t
a n d t o determine t h e f e a s i b i l i t y of performing a maneuver to cause l u n a r
i m p a c t w i t h i n a c e r t a i n area on the moon. This s t u d y s h o u l d be complete
by A p r i l 15. ( ~ ~ . 1 / 3 o e i n g )
-
a.
Guidance Backup for T r a n s l u n a r I n j e c t i o n
Several documents have been r e c e i v e d from Bellcomm a n d
MSC which d e s c r i b e the NIT c r a s s - p r o d ~ c t s t e e r i n g e q u a r i o n and the
Lambert solution to the conic time c o n s t r a i n t problem.
The separate
�p o r t i o n s have b e e n v e r i f i e d , b u t an o v e r a l l c l o s e d l o o p evaluation of
the guidancz backup system has n o t y e t been made. A performance and
a c c u r a c y s t u d y of the backup g u i d a n c e system will b e made i n the f u t u r e
from the s t a n d p o i n t t h a t t h i s is a backup system t o be u s e d in an
emergency only.
(DG)
b.
Launch Vehicle Lunar Targeting
Using a p a t c h conic program developed f o r MSC by TRW,
a year's l u n a r t a r g e t i n g is being s t u d i e d . The s t u d y is b e i n g made t o
d e t e r m i n e the e f f e c t on the hypersurface across a year's launch
opportunities.
(DAM/Boeing)
3.
Dynamics arid C o n t r o l
a.
Dynamic T e s t R e s u l t s
The c o r r e l a t i o n of dynamic t e s t r e s u l t s with theor e t i c a l p r e d i c t i o n s showed a large l o c a l effect on the r a t e gyro package which was mounted on the cold p l a t e . The evaluation of these data
has l e d to an u p d a t i n g of the d e s i g n data f o r f u t u r e S a t u r n V vehicles
A m o r e d e f i n i t i v e s t r u c t u r a l damping v a l u e can be p r e d i c t e d , as well
as the l o c a l influences on the r a t e g y r o package. The r e s u l t s a £ t h e
data evaluation of Ll~edyrxamlc t e s t t l l ~ d L t s impact: on d e s i g n data are
b e i n g p u b l i s h e d in R-AERO-DD-21-67.
@DS)
b.
503 Res i d u a l P r o p e l l a n t s
S e v e r a l s t u d i e s have been made for the translunar
E l i g h r S-IVB p o r t i o n .
The f a c t that L O X v e n k a n d n o t a l i g n e d through
the v e h i c l e center of g r a v i t y r e s u l t s in Large slosh waves t l m t r e q u i r e
e x c e s s i v e t i m e f o r damping. The solution to t h i s problem is a nonp r o p u l s i v e LOX vent and a p r o p u l s ive LH, vent. The propulsive LHvent is required to k e e p the l i q u i d s e t t l e d a n d ta maintain c o n t r o l .
(DDD)
c.
S a t u r n V L i f t - O f f ?lotion
A d d i t i o n a l l i f t - o f f motion d a t a have been generated
f o r 5 n c l u s i o n w i t h t h a t previously documented i n s u p p o r t of t h e swing
These data are published in Memo R-AERO-DCC- 1 67,
arm redes ign
F e b r u a r y 8 , 1967 and Fn Memo R-AERO-DCC-~-L~. (DC)
.
-
�4.
P r o j e c t I n f o r m a t i o n Applicable to Many Vehicles
a.
S a t u r n V Current Performance
V e h i c l e c u r r e n t performance, which was updated ir
F e b r u a r y and March, was r e l e a s e d in confidential memorandum R-AERODAP-15-67 d a t e d March 1 6 , 1967. During February, t h e AS-501 and 502
v e h i c l e s were r e i n s t a t e d into the c u r r e n t performance. Payload f o r
AS-503 i n c r e a s e d over January by 613 pounds. Vehicles AS-504, 505, and
5 0 6 e s t i m a t e d payload c a p a b i l i t y was 518, 5 4 9 , a n d 1308 pounds, r e s p e c t i v e l y , above the p r o j e c t e d payload.
This was due p r i m a r i l y to new
d r a g data f o r AS-503 and s u b s e q u e n t v e h i c l e s . For vehicles AS-501 and
5 0 2 , there was no change from February to March.
Payload increased f o r
A S - 5 0 3 over February by 24 pounds.
Payload decreased from February to
March f o r v e h i c l e s AS-504, 505, and 5 0 6 and were 135, 143, and 1 2 3 6
pounds, r e s p e c t i v e l y , above the p r o j e c t e d payload. The payload change
was d u e to weight changes. The performance was based on 1 9 6 7 February
and Narch c u r r e n t w e i g h t s and was transmitted to I n d u s t r i a l Operations.
(~~PIBoeing)
b.
A t t i t u d e Timelines for Vehicles 5 0 1 through 504
SSR-108, " S a t u r n V Parking O r b i t and P o s t I n j e c t i o n
A t t i t u d e Time L i n e s , " was released 2-9-67.
The report p r o v i d e s a summary of c o a s t flight v e h i c l e a t t i t u d e requirements and a t t i t u d e angles
which s a t i s f y t h e r e q u i r m e n t s .
The report covers Sat-urn V vehicles
SA-501 t h r o u g h SA-504 b u t is n o t up to date. ( ~ A P / ~ o e i n g )
5.
Project I n f o r m a t i o n Applicable to I n d i v i d u a l Vehicles
a.
SSR-126 AS-503 Excess Propellant Elimination Methods
Evaluation
The amount of excess propellant left in the S-IVB at
This amount of propellant c o n s t i t u t e s a
c o n t r o l problem if it cannot: be s e a t e d d u r i n g docking. Twelve methods
injection i s 7 8 , 6 0 0 pounds.
oF reducing the excess S-IVB p r o p e l l a n t to t h e
i n v e s t i g a t e d , two of which are considered more
others:
( I ) early S-I1 engine: cutoff and (2)
propellant through the 5-2 engine during c o a s t
b.
d e s i r e d amount were
feasible than the
e x p u l s i o n of excess
flight. (DAP/Boeing)
AS-504 Reference Trajectory Documentation
Development of the SA-504 reference trajectory is cont i n u i n g on s c h e d u l e . A 1 1 out-of - o r b i t targeting i s o l a t i o n s and t r a j e c t o r i e s t h r o u g h o r b i t a r e complete; f i f t y percent of the o u t - o f - o r b i t
t r a j e c t o r i e s a n d twenry-five percent: of t h e space t r a j e c t o r i e s have
been v e r i f i e d . One book of the f i v e under development has been prepared.
(DAPI ~ o i neg )
�I. P r o j e c t I n f o r m a t i o n Applicable t o Many Vehicles
a.
AAP C u r r e n t Performance
Current performance d u r i n g February a n d March for U P - I ,
2 , 3 , a n d 4 l a u n s l ~v e h i c l e s was d i s t r i b u t e d in memorandums R-AERO-DAP-9- 67
(February 1 6 , 1967) and R-AERO-DAP-14-67
@arch 1 4 , 1 9 6 7 ) . During
F e b r u a r y , U P - I , 2 , 3 , and 4 p a y l o a d s increased 1987, 2 4 2 , 1981, a n d
9540 pounds, r e s p e c t i v e l y , over January.
This was d u e ro w e i g h t , p r o p u l s i o n , e n g i n e m i x t u r e ratio s h i f t t i r r ~ e arid m i s s i o n altitude change. For
>larch, t h e p a y l o a d s for U P - 1 , 2, and 4 decreased from February by 3 4 6 ,
4 7 , and 9361 pounds, respectively. This was due to weight: a n d S-IVB
mains t a g e o x i d i z e r change p l u s m i s s i o n a l t i t u d e change fuw AAP-4. U P - 3
showed an i n c r e a s e in payioad from February of 45 pounds d u e primarily
to weight d e c r e a s e .
The c u r r e n t performance w a s transmitted t o I n d u s t r i a l
Opera t i o n s .
(DAP/Chrys Per)
2,
Project I n f o m tion A p p l icab Le to Znd i v i d u a l Vehicles
AS-2071 208 Preliminary A b o r t and Alternate Miss ion
SLudies
AS-207 / 208 p r e l i m i n a r y a b o r t and alternate m i s s i o n
s t u d i e s (TN-AP-66-132, and TN-AP-66-133) have been r e c e i v e d E r m C h r y s l e r
.
(DAPJ C h r y s l e r )
1. Project A b l e
This s t l ~ d yhas been t e r m i n a t e d . A f i r a l r e p o r t on the conclus i o n s and r e c m e n d a t i o n s d e a l ing w i t h f 1 i g h t mechanics has been
d i s t r i b u t e d as memorandum R-AERO-DM-5-67.
(DAO)
a.
M P - 1 and SAAP-2 P r e l i m i n a r y Reference T r a j e c t o r y
A l l analyses have bccn c o m p l e t e d f o r t h e U P - 1 l a u n c h
v e l i i c l e p r e L i m i n a r y r e f e r e n c e t r a j e c t o r y (TN-AP-67-18A) and was submitred
to MSFC on March 24, 1967. A r e p o r t (TN-AP-67-148) documenting the l a u n c h
vehicle p r e l i m i n a r y r e f e r e n c c t r a j e c t o r y f o r the U P - 2 m i s s i o n is b e i n g
reviewed p r e p a r a t o r y to t r a n s m i t t a l f o r r e p r o d u c t i o n .
(DAP)
�b.
Mission Timeline T r a d e Study
A s t u d y is i n progress t o e s t a b l i s h the t r a d e - o f f resulting f r o m t h r e e different crew duty cycles assumptions as they affect t h e
arnounr. of experiment: time available on t h e 56-day A D 4 m i s s i o n .
Three
d i f f e r e n t scheduling philosophies w i l l be used to es tab1 i s h t h e b e s r
way to combine the Am and biomedical experiments.
(~AHJLockheed)
3.
O r b i t a l Workshop
a.
AAP-1 O r b i t a l Workshop Pass i v a t i o n
A preliminary inves t i g a r i o n to m i n i m i z e perturbations
to i n i t i a l injection orbit due to passivating the S-IV3 workshop is
n e a r i n g completion. The i n i t i a l o r b i t u n d e r study is 250 nautical m i l e s
c i r c u l a r . R e s i d u a l s r e p r e s e n t i n g the + 3 0 , nominal, and - 3 values
~
are
being s t u d i e d
.
Injection i n t o an e l l i p t i c a l o r b i t and circularizing
at the proper a l t i t u d e by the passivation i m p u l s e is b e i n g investigated.
This method y i e l d s the minimum perturbations from the t a r g e t o r b i t ; howe v e r , these p e r t u r b a t i o n s a r e acceptable. (DAP)
b
.
Orb ital Workshop A t t i t u d e S t u d i e s
A r i g i d body a n a l y s i s of the a t t i t u d e h i s t o r y of t w o
uncontrolled orbiting cluster configurations has been documented in
memo R-AERO-D-7-67. The s t u d i e s c o n s i d e r e d the c o n f i g u r a t i o n planned
f a r the 23-day p r i m a r y m i s s i o n and the c o n f i g u r a t i o n af rhe 6-month
orbital s t o r a g e p e r i o d .
The r e s u l t s , which are very p r e l i m i n a r y , were based on
f i r s t e s t i m a t e s of aerodynamics far the workshop. Various i n t t i a l values
were assumed f o r the a t t i t u d e and angular rates of the configurations
investigated.
The r e s u l t s of these studies show t h a t the motion of
rhe vehicle is s t r o n g l y dependent on the i n i t i a l c o n d i t i o n s , and even
when t h e s e c o n d i t i o n s are known reasonably well a small amount of
u n c e r t a i n t y in the angular rates is sufficient to change the vehicle
motion c o n s i d e r a b l y .
F r a a this prel-kminary a n a l y s i s , it was concluded that,
unless the v e h i c l e is s t a b i l i z e d in a g r a v i t y g r a d i e n t condition by u s e
of external c o n t r o l forces, the motion of the v e h i c l e is likely r o
d e v e l o p a random tumblfng motion which w i l l continue far the d u r a t i o n
of t h e f l i g h t .
@C)
�4.
Cluster
a.
Mission Profile
(1) P r e l irninary Miss i o n Prof iEe Documentation
A report (TN-A?-67-173) d o c u m e n t k g the p r e l i m i n a r y
f l i g h t p r o f i l e s for U P - 1 , 2, 3 , and & l a u n c h vehicles was received by
WSFC February 17, 1 9 4 7 . (DAP/ChrysPer)
(2)
UP-3/AAP-4 Mission P r o f i l e s
Baseline m i s s t o n profiles f o r UP-3/AAF-4 have been
p r e p a r e d u s i n g the co-orbital rendezvous scheme. Two c a s e s are under consideration:
(a) separate rendezvous of t h e zM/Am and CSM with the works h o p and ( b ) rendezvous of a c o u p l e d LMIATM-CSM to workshop. These
profiles were p r e s e n t e d at the A T 4 Q u a r t e r l y Review in early Farch.
(DAO)
(3)
1969 AAP M i s s i o n Praf iles
Mission profiles have been m a d e a n d r e v i s e d w i t h
l a t e s t l i f e t i m e data for missions AAP-5, 6 , 7, and 8. These p r o f i l e s
assume the use of four 90-day CSM's to achieve a year in space by r e u s i n g
t h e o r b i t a l workshop and ATM from the 1 9 6 8 c l u s t e r m i s s i o n . (DAD)
(43
1969 AAP M i s s ion D e c i s i o n L o g i c
Effort is being expended to produce a 1969 mission
d e c i s i o n l o g i c nefmork. Work on t h i s task has progressed for one month.
The b a s i c goal of the overall 1969 mission is t o k e e p men in space cant i n u o u s l y for one y e a r w i t h periodic replacement and exchange of crews.
The S-TVB Orbital Workshop is to f u r n i s h a space scation environment
for t h e crews who will perform various experiments. A preliminary version
of the d e c i s i o n l o g i c f o r this complex m i s s i o n has b e e n completed and i s
to b e p r e s e n t e d Lo the Mission P l a n n i n g Task Force at NASA H e a d q u a r t e r s ,
IJashington, in e a r l y A p r i l . This d i s p l a y has been k e p t as g e n e r a l zs
p o s s i b l e w i t h o n l y a feu r e s t r i c t i n g ground r u l e s , such a s t h e p o s s i b l e
a v a i l a b i l i r y of a n o t h e r O r b i t a l Workshop a n d ATM.
In the present v e r s i o n ,
a nominal path i s d e t a i l e d w i t h the various b r o a d d e c i s i o n s ar-d a c t i o n s
necessary to c a r r y o u t the planned m i s s ion. In a d d i t i o n , off-nominal
d e c i s i o n and action routes are i n c l u d e d which p r o v i d e p o s s i b l e alternatives
when there i s an off-nominal occurrence. In t h i s preliminary v e r s i o n ,
several paths are prematurely terminated because of Lack of manpower and
time, and mare expansion is needed before completion. It i s f o r e s e e n :hat
the f i n a l v e r s i o n of t h i s d e c i s i o n l o g i c w i l l c o n s i s t of a vast number of
d e c i s i o n s and a c t i o n s resembling a PERT network. The use of such a n e t m r k when coupled w i t h a m i s s i o n success p r o b a b i l i t y a n a l y s i s can be
developed i n t o a nominal and alternate mission design tool. Further
�i* ~ C ~ L O U T C a
P r~l a l y s i s psograa ( h z s d r . r z r ~ , s c L e d u l e , and
iu; l y d e v e i o p e d s y s t e m c o u l d b e ~ s r r as
l
a SASA H e a d q u a r t e r s
r u t u r c s p a c c program planning tool. (DAD)
LTJII;,!
L ~ J:
rncjnkyl,
~ it l h
ttic
.
Dynamics and C o n t r o l
(11
Clus ter S tructural Dynamics
Work is underway ac Lockheel. Huntsv$?te, u n d e r
s u p p o r t contract to d e v e l o p computer programs f o r the s h o r t term
d y n a m i c r e s p o n s e of p l a n n i n g o r b i t a l w o r ~ s h o p - c l u s t e r c o n f i g u r a t i o n s ,
A g e n e r a i m z ~ h c m a t i c a l model far calculating l i n e a r vibrarion charact e r i s t i c s a n d r e s p o n s e of the c l u s t e r s is b e i n g formulared. A p a r t i a l
c h e c k o u t of t h e d i g i t a l program r.:as s u c c e s s f u l Ly p e r Eclrmed , Routines
t;.hich g e n e r a t e s t i f r ' n e s s , damping, and mass c o e f f i c i e n t s a n d asszmble
rhem into matrices f o r the overall s y s t e m were s u c c e s s f ~ l l yr u c , znd
routines which c m p u t e n a t u r a l f r e q u e n c i e s a n d modes f o r t h e s y s t e m
zre being debugged.
(DDS/Lockheed)
(2)
Csmbincd hTorkshop/~i?!S ~a tionkecping
Docurnenta L i o n of a p a r t k u l a r s o l u r i o n to the
soft terher stationkeeping p r o b l e m -has b e e n d i s r r l b u t e d a s memorandum
3 - X R O - D A D - 2-67.
In t h i s solution, an i m p u l s e is i m p a r t e d t h r o u g h t h e
t e t h e r e v e r y 3 112 o r b i t s to compensate f a r the aerodynamic d r a g
dcccleration.
The d i f f e r e n t i a l e q u a t i o n s of motion f o r the W.I/
A D 1 were w r i t t e n in a c o o r d i n a t e s y s t e m fixed in the ~iroskshop. Assuming
t h a t the d r a g d e c e l e r a t i o n is a c o n s t a n t , a closed form s o l u t i o n to
t h e s e equations was found.
Another p a r t i c u l a r s oLut i o n to t h e so?t t e t h e r
p r o b l e m has b e e n found which does noE e x h i b i t t h e o s c l i l a t i o n s in t h e
r a d i a L a n d t a n s e n t i a l d i r e c t i o n s found i n t h e p r e v i o u s s o l u t i o n .
This
w i l l g r e a t l y r e d u c t . t h e accuracy n e c e s s a r y f o Y the magnitude and t h i n g
o f t h e p u l l s on the techcr. A l s o t h e magnitude o f t h e p u l l s was only
v e r y ~ ~ ~ c a kdependent
ly
upon t h e d i f f e r e n c e in drag dzcelera~ions between
' L ~ F~.:orkshop and S l / I Z T X .
On t h e s u b j e c t of t e t 5 e r r e t r i e v a l , t c t n t e r e s t i n g conccpt was found in the L i t z r a t u r e wherein a t h i r d m a s s i s e x t e n d e d
o n a n o t h e r t e t h e r f r o m rhe body S e i n g r c c r i e v e d . The r a t e of recrfeval
is c o n t r o l l e d in s u c h a manner t h a t most of t h e angular m o m e n t u m is
p u n p e d i n t o the t h i r d mass rrhicll may b e d i s p e r s e d of a f t e r retrieval
o f t h e GI,
(DAO)
�(3)
Rigid Body Response of O r b i t i n g S p a c e c r a f t
Thc b e h a v i o r of an ear t h - o r b i t i n g v e h i c l e when
subjected ro an impul.sive farce such as encountered in docking maneuvers
h a s been documented and d i s t r i b u t e d in Memo No. R-AERO-DCA-1-67. The
o n l y restoring t o r q u e c o n s i d e r e d to act on the v e h i c l e was hat r e s u l t i a g
from the gradient in the earth's gravitational field with altitude. The
a n a l y s i s was r e s t r i c t e d t o m o t i o n i n the o r b i t p l a n e o n l y .
Presented in the memo are the e q u a t i o n s t h a t
d e s c r i b e t h e maximum value of impulsive t o r q u e t h a t the vehicle can s u s t a i n b e f o r e tumbling occurs. Numerical examples were p r r s e n t e d far t h e
s p e c i a l case in which the vehicle has no i n i t i a l a n g u l a r v e l o c i t v .
The
i n e r t i a and mass parameters u s e d f o r the numerical examples are t y p i c a l
f o r the S-IVB workshop c l u s tcr configuration.
(DC)
5.
Odyssey
An estimate of the propellant and b u r n time r e r l u i r e d to
t r a n s f c r t : ~ e p r o p o s e d O d y s s e y p a y l o ~ dpackage f r o m a 240 hl. c l r c u l a r
~ r b i tto a 160 Ian by 1750 h e l l i p s e u s i n g a c l u s t e r of 4 C - 1 e n g i n e s
has b e e n dscumented
(DAO)
.
E m General Methods
-
Dynamics and C o n t r o l
Design C r i t e r i a for C o n t r o l of Space Vehicles: Two monographs
w e r e received in f i n a l farm: (1) "Component Dynamics" by J . G. R o l l a n d
Collette and (2) " A t t i t u d e C o n t r o l DurFng Launch" by A r t h u r L. G r e e n s i t e .
In t h e f i r s t monograph t h e t h r e e b a s i c f u n c t i o n s to b e c o n s i d e r e d f o r
the operation of a c o n t r o l s y s t e m a r e d i s c u s s e d :
(1) s e n s i n g , ( 2 ) s i g n a l processing and ( 3 ) a c t u a r i o n . E q u a t i o n s are d e v e l o p e d f o r the motion of
gyroscopes and accelerometers. T y p i c a l schematics and flow charts which a r c
m a d e for the actuating elements are discussed in d e t a i l .
The s e c a n d
monograph discusses t h e usual s t a b i l i z a t i o n t e c h n i q u e s a s well a s the
i n l l u e n c e o f v a r i o u s n o n l i n e a r i t i e s . A l l of the influencing f e a t u r e s
(Elexibility,propel l a n t s l o s h i n g , e t c . ) a r e c o n s i d e r e d in the t r e a t m e n t
of the p r o b l e m . The a i m , as with a n y a n a l y s i s , i s to formulate t h e
s i m p l e s t m o d e l that w i l l a c c o u n t for a i l significant phenomena.
Two o t h e r monographs were r e c e i v e d : " ~ t t i t u d e C o n t r o l in S p a c c f '
and "Adaptive Control
These have been reviewed.
(DCAIOA)
."
�I
FLIGHT TEST A X A T 2 S T S D I V I S I O N
A.
Special Projects Office
A p r e s e n t a t i o n on the s t a t u s of p l a n n i n g and p r e p a r a t i o n
f a r S a t u r n V f l i g h t t e s : e v a l u a t i o n was g i v e n by Mr. L i n J b e r g to the
Saturn V Program O f f i c e on F e b r u a r y 14, 1967. The m a s t s i g n i f i c a n t
problem d i s c u s s e d was the i m p a c t on f l i g h t evaluation of nearly s i m u l taneous S a t u r n IB and S a t u r n V l a u n c h e s , a n d acce?tance tes t i n p . T h i s
i m p a c t is not$ b e i n g investigated by the FEWG and will again be p r e s e n t e d
to t h e p r o g r a m o f f i c e during A p r i l . It now appears t'nat the i m p a c t en
computer c a p a b i l i t y at MSFC, S l i d e l l , DAC, and SLID w o u l d not b e s c r i o u s ,
b u t the i m p a c t : on manpower f o r analyses at: DAC, ~ ~ C / M i c h o u dand
,
IBM may
be a signiiicant problem.
The S a t u r n V F l i g h t T e s t Evaluation i s a b o u t 90 p e r c e n t
cornpletc a n d s h o u l d be p u b l i s h e d by A p r i l 10, 1967.
FEVG-Payf oad organizatiirna 1 e f f o r t s h a v e continued d u r i n g
t h i s p e r i o d . The second g e n e r a l meeting Ims b2en h e l d , a n d t h e second
d r a f E af t h e PEWG-Payload P l a n h a s b e e n completed. This document contains
the ovcrall scopc and f u n c t i o n for the g r o u p applicable to all payloads.
The f i r s t d r a f t of the Eirst m i s s t o n p l a n document, A A P - ~ I A A P - payload
~
evaluation plan, i s nearing completion. Otherwise, the development of t h i s
working g r o u p is proceeding along the same l i n e s as for the S a t u r n IB and
S a t u r n V Launch v e h i c l e s .
3.
Seminar
Plans for a seminar on "~nvironment-Induced O r b i t a l Dynamics"
s p o n s o r e d by Aero-As trodynamfcs L a b o r a t o r y t o b e h e l d at XSFC on June 6
and 7 , a r e e s s e n t i a l l y c o m p l e t e .
The four technical s e s s i o n s are:
a.
Mechanics of O r b i t a l Decay
b.
Aerodynamic C o e f f i c i e n t P r e d i c t i o n Methods
c.
Amospheric Models
�The p l a n s are to l i m i t the group to 7 0 to 80 i n v i t e d p a r t i c i p a n t s s o
that a seminar atmosphere may be o b t a i n e d .
The purposes for t h e
seminar a r e to ( a ) h i g h l i g h t the degree of s o p h i s t i c a t i o n of the
t e c h n o l o g y , (b) improve the i n t e r f a c e s between the d i s c i p l ines i n v o l v e d ,
(c) p o i n t the d i r e c t i o n f o r advancing the technology, and (d) develop
i n t e r e s t and s u p p o r t for i n d i c a t e d programs.
B.
Tracking and O r b i t a l A n a l y s i s Branch
1.
Saturn V/Voyager
A memorandum (R-AERO-FT-4-67] on the S a t u r n V/Vayager t r a c k i n g and communications coverage for the launch phase and the earth-pasking o r b i t s f o r various i n c l i n a t i o n s was d i s t r i b u t e d .
The coverage of
the t r a n s f e r trajectory and Mars o r b i t w i l l be analyzed at some l a t e r
time when trajecrory p r o f i l e s are available.
Parametrkc o r b i t a l L i f e t i m e studies b e i n g c o n d u c t e d for a
Mars o r b i t i n g s a t e l l i t e w i l l be expanded to include the Voyager s p a c e c r a f t i n v a r i o u s Mars o r b i t s ,
2.
Saturn V
L e t t e r s have been t r a n s m i t t e d to t h e Boeing Company Listi n g the various s i t e s a n d i n s t r u m e n t a t i o n to b e used i n the AS-501,
AS-502, and AS-504 t r a c k i n g and telemetry a n a l y s Fs d o c u m e n t s ,
The AS-501 t r a c k i n g a n d telemetry a n a l y s i s document on the
operational Era j e c t o r y lzas been received f r m TBC and is b e i n g prepared
for dis tribution.
The Boeing Company w a s requested t o a p p r o x i m a t e t h e A S - 5 0 1
S I C t r a j e c t o r y a n d determine the s e p a r a t i o n angle and d i s Lance from t h e
t i m e of S-IVB/SC separation t o 5 hours flight t i m e (near apogee) u s i n g
the Ascension I s l a n d s t a t i o n c o o r d i n a t e s . This s e p a r a t i o n information
was r e q u e s t e d by I-YO-R to help d e t e r m i n e beacon requirements acd
assignments f o r the Ascension I s l a n d s t a t i o n .
received from TBC and t r a n s m i t t e d LO I-MO-R.
3.
The i n f o r m a t i o n 'has been
Saturn 13
Letters have been t r a n s m i t t e d to CCSD 1is t i n g the v a r i o u s
s i t e s and i n s trumentation to be u s e d in the AS-204 (LM m i s s i o n ) , AS-205,
AS- 206, AS-208, and S M - 1 tracking and telemetry analys is documents.
The p r e d i c t e d o r b i t a l lifetime f o r the S - I ~ J B / X s t a g e s on
the d u a l AS- 2 0 5 / ~ S -208 m i s s i o n was d i s tr Fbu t e d in memorandum R-AERO- FT13-67.
�A request: was made to MSC through M r . Crernin, Go-Chairman,
G&P Subpanel for the A S - 2 0 6 o p e r a t i o n a l s p a c e c r a f t t r a j e c t o r y to b e
sent to R-AERO-FT as soon as p o s s i b l e . I-MO has stressed t h e f a c t t h a t
t h e s e p a r a t i o n angle and d i s t a n c c information would be e s p e c i a l l y h e l p f u l in t h e AS-206 m i s s i o n s u p p o r t planning.
Tracking and telemetry i n f o r m a t i o n o n the AS-206 "specialt'
o r b i t a l trajectory has been transmitted to Mr. Sims, R-AERO-P, in
memorandum R-AERO-FT-21-67. This t r a j e c t o r y , which w a s done by CCSD
under direction of J. C r a f t s , R-AERO-lW, i n c l u d e s passivation impulse.
Tracking end telemetry information on t h i s trajectory was a l s o done by
CCSD.
P r c l irninary tracking and communieatiana s c q u i s -ition a n d
l o s s times based on the AS-205 operational trajectory were recelved
from CCSD on Marc11 14, 1967. These data have been s u p p l i e d to ASTR
Lab and F&VE Lab to meet t h e i r contractual deadlines. This information
is necessary to complete the AS-205 F l i g h t Program p r e p a r e d by IBN
f o r d e l i v e r y to KSC.
Studies are p r e s e n t l y underway to establish the l i f e t i m e
of t h e S-IVB on the new AS-204 mission assuming char p a s s i v a ~ i c r nis
performed. A l i f e t h e of at l e a s t one o r b i t is required a f t e r the
passivation. Studies to identify the attitude of rhe S-IVB during
passivation to guarantee rhis lifetime are b e i n g carried on. I n a d d i tion, the separation d i s t a n c e between the LM and the S-IV13 on the new
AS-204 m i s s i o n will be e s t a b l i s h e d . This s t u d y will be performed from
S-IVBJLY separation to at l e a s t one o r b i t a£ ter the S-TVB passivation,
A magnetic tape of t h e LM trajectory a£t e r s e p a r a t i o n from t h e S-IVB i s
being f o r ~ m r d e dby MSC f o r u s e i n t h i s srudy.
P r e l i m i n a r y tracking and communications a c q u i e ition and
l o s s times b a s e d on the AS-208 Preliminary Operational Trajectory were
r e c e i v e d from CCSD on Yarch 2 1 , 1967.
.
AAP
A n o f f i c e m m n o r a n d u m , R-AERO-FT-11-67, entitled "Power
FL i g h t a n d Orbital Tracking and Communications Coverage for l i p r a t c d
S a t u r n I Nominal Trajectories in ar, 80 x 200 N.M. Elliptical and a
200 N.M. Circular Polar O r b i t , " has been d i s t r i b u t e d .
S t u d i e s have been perfarmed to determine the o r b i t a l decay
and l i f e t i m e of SIA panels releasec from 'chc 5-IVB. The panels were
assumed t o b e released from the S-IVB with no energy impaxted to then.
They would then d r i f t away f r o m the S-IV13 p r i m a r i l y d u e to atmospheric
drag f o r c e s . These d a t a were analyzed for the workshop mission with
t h e S-IT9 in a 480 krn circular orbit. A d d i r i o n a l information used in
t h e a n a l y s i s is a s fallows:
�(a)
Mass of the f o u r p a n e l s ranged from 252.20 kg to
294,83 kg.
(b)
Aerodynamic parameters for various o r b i t a l o r i e n t a t ion:
nose-on AC,,
= 3.68 m2; b r o a d s i d e , C$i. = 4 8 . 3 3 m2; tumbling, C+ = 30.79 m2, (R-AERO-A d a t a ) .
A r e p e a t presentation on the s u n i n t e r f e r e n c e problem of the
S y s t e m was given to A s t r i o n t c s personnel on
F e b r u a r y 10, 1 9 6 7 .
LM Relay C m u n i c a t i o n s
P r e s e n t MSFC e f f o r t s on the CM r e l a y experiment have b e e n
completed a n d r e s u l t s g i v e n to NASA Headquarters
OTDn. personnel.
-
.
P r e l h i n a r y STADAN tracking t i m e l i n e s were given to Plr L l v ,
R-ASTR-IR, on the AlIM m i s s i o n . As t r i o n i c s Lab is invcs t i g a t i n g the use
of t h e STADAN network to return t h e large amounts of experimental d a t a
that: will b e c o l l e c t e d on the Am m i s s i o n , A memorandum documenting
t h e s e t h.e 1i n e s is b e l n g prepared.
The o r b i t a l analysis r e l a t e d to the Odyssey 1 experiment
w a s presented to Aero-Astrodynamics L a b o r a t o r y p e r s o n n e l on March 8 ,
1967.
This p r e s e n t a t c o n i n c l u d e d a d i s c u s s ion o n the Baker-Kunn camera
s y s t e m , O r b i t Determinatian u s i n g Saker-Nunn camera data, and an e r r o r
a n a l y s i s on t h e proposed Odyssey I experiment.
5.
L i f e t i m e and O r b i t a l Analysis
Mr. Bensan made a presentation on the E a r t h O r b i t a l L i f e time Program to a p p r o x i m a t e l y 25 MSC personnel on F e b r u a r y 1 7 , 1967.
M S C personnel were very e n t h v s i a s t i c a b o u t r e c e i v i n g and u s i n g t h i s
program. P l a n s have been made for the use ef t h e Lifetime program in
conjunction w i t h r e a l time m i s s i o n o p e r a r i o n s . MSC a l s o expressed t h e i r
d e s i r e s to i n c o r p o r a t e t h e atmospheric model (1962 U. S . S t a n d a r d s h i f t c d
f o r s o l a r h e a t i n g effects) into all r e a l time computer programs. I; F7aS
p o i n t e d o u t that the model has been v e r i f i e d u s i n g aerodynamic parame t e r s r e c e i v e d from R-AERQ-A. It was M S C f s i n t e n t i o n to r e q u e s t R-AERO-A
to s u p p l y them w i t h s imilar a e r o d y n a m i c data on a l l m i s s i o n c o n f i g u r a t i o n s .
Mr. Fleischman r e t u r n e d to WSC on F e b r u a r y 23 and 24 with
CSC programer r e s p o n s i b l e f o r t h e lifetime program, to
d e l i v e r the l i f e t i m e program, to make s u r e it was operable o n NSC corn-
Mr. Boykin,
p u t e r f a c i l i t i e s , a n d to i n s t r u c t XSC personnel a b o u t i t s use a n d
f lexibilities
.
�A memorandum lms been prcpared to Mr. Yarbrough, R-COMP-RDS,
to authorize transmirtal of t h e Lifetime Program to E e l Lcomm af W a s h i n g t o n ,
D. C., who had r e q u e s t ~ da copy of t h i s pragram.
A confract w i t h Honeywell o f M i n n e a p o l i s ta inves tigate t h e
feas i b $1ity of us i n g linear p r o g r a m i n g in s ched ul i n g exper iments for t h e
APlP m i s s i o n has been s i g n e d . The c o n t r a c t w i l l d e r e r m i n e if 1inear psog r a m i n g can b e incorporated in the sequencing O p t i m i z a t i o n A u t o m a t i c
Program (SOAP) as a second s c h e d u l i n g methad.
S t u d i e s are being made to e s t a b l i s h e l l i p t i c o r b i t s which
will p r o v i d e i n c r e a s e d l i f e t i m e f o r the proposed SAh-1 through S k i - 4
m i s s i o n s . These s t u d i e s are being performed over various i n c l i n a t i o n s
a n d w l l l r e f l e c t performance capabiliries s u p p l i e d by K-MKO-HA.
C.
F l i g h t E v a l u a t i o n Branch
1.
Saturn I 3
a.
General
A meeting was a t t e n d e d to d f s c u s s s l e d t e s t s of the
trap-down) g u i l a n c e s y s tern. A t t e n d i n g were represents tives
from Holloman A D , ASTR, COMP-RRM, and AERO-FF.
Holloman personnel were
concerned with what t e s t dara t h e y were expected to f u r n i s h MSFC and i f
any analysis of rhe guidance system was expected. It was d e c i d e d thar
Bolloman would f u r n i s h MSFC with the r a w telemetry tape of the g u i d a n c e
measurements v e r s u s time a n d processed space-time d a t a of the track
system. R-ASTR and AEBO-FFR w i L l perform the system analyses. C W - R
will r e d u c e the telemetry.
SD-53
(s
A package of data showing angular acceleration data
seen by t h e S-LB c o n t r o l s y s t e m has been p r e p a r e d for A s t r i o n i c s Lab.
I n s t r u m e n t s analyzed were the p i t c h , yaw and r o l l rate gyros f o r A S - 2 0 1 .
Data were o b t a i n e d by passing the measured a n g u l a r v e l o c i t y data t h r o u g h
a d i g i t a l derivative f i l t e r . The roll rate gyro i n d i c a t e d the l a r g e s t
accelerarions reaching 1200 d e g / s e c 2 peak-to-peak at: 63 seconds Range
Time. Maximum a c c e l e r a t i o n s m e a s u r e d near body bend Tng f r e q u e n c i e s
were 13'/sec2 peak-to-peak at 4 H e r t z . A power s p e c t r a l d e n s i t y a n a l y s i s
of the data i n d i c a t e d t h a t most o f the c o n t r r i b u t i o n s to t h e h i g h total
r a t e were d u e to i n d i v i d u a l frequency components c e n t e r e d between 10
and 25 Hertz.
2.
Saturn V
a.
Lift-off C o n t r o l
A s i m p l i f i e d stabFLity a n a l y s i s of the AS-501 c o n t r o l
s y s tern was performed t e e v a l u a t e the u s e of i , and 9,; g u i d a n c e g a i n s
�to a l l e v i a t e the LUT clearance problem. With t h e p r e s e n t A, and A l
c o n t r o l gains and c o n t r o l filters, the s t a b i l i t y m a r g i n with :,L and d l
i n c l u d e d i n the s y s t e m was r a t h e r r e s tsicted. The range on the g a i n s
was d e t e r m i n e d to be approximately the f o l l o w i n g :
Sample runs w i t h a .34-degree thrust m i s a l i g n m e n t i n d i c a t c d that a
2.5
2.7 meter r e l i e f in d r i f t can b e o b t a i n e d w i t h t h e p r e s e n t l y
dcf i n e d control s y s tern.
-
b.
L i f t - o f f Motion
An a i r scaop t a r g e t camera has been r e q u e s t e d f o r
504 to observe a i r scoop motion r e l a t i v e to the s o f t r e l e a s e
mechanism. An a d d i t i o n a l t a r g e t camera has been requested for AS-5025 0 4 . These a d d i t i o n a l cameras w i l l r e s u l t in a b e t t e r definition of
v e h i c l e motion d u r i n g the i n i t i a l phase of f l i g h t (2 s e c ) . T h i s
r e q u e s t is contained in Memo No. R-AERO-FF-15-67, " L i f t o f f T a r g e r
Camera S u p p o r t R e q u i r e d for S a t u r n V" dated F e b r u a r y 24, 1 9 6 7 .
AS-501
-
c.
E f f e c t s of S-IVB I g n i t i o n Weight Error
There appeared t o be a problem e x i s t i n g for the f l i g h t
s i m u l a t i o n s e c t i o n s in determining the propulsion s y s t e m performances
f o r S - I C and S-IT s t a g e s 0 5 the S a t u r n V f l i g h t vehicles. The S - I C
and 5-11 s t a g e c o n t r a c t o r s asked if t h e r e was a way in w h i c h they c o u l d
p r o c e e d with p o s t f 1i g l ~ t . a n a l y s i s o f p r o p u l s ion sys tems p e r f onnance w i t h o u t waiting f o r the f i n a l vehicle i n i t T a l mass, The f i n a l mass will not
be d e t e r m i n e d u n t i l a l l of the S-IVB 2nd b u r n and v e n t i n g data have b e e n
reviewed. n i s may require most of the time allowed the f l i g h t simulation sections f o r t h e i r a n a l y s i s . A f t e r s t u d y i n g the e f f e c t s of a mass
error on an u p p e r s t a g e to the s tage b e i n g evaluated , it becomes
apparent t h a t a mass error of t h i s nature would be i d e n t i c a l in e f f e c t
to a d r y weight error on the s t a ~ eb e i n g evaluated. Many s t u d i e s have
been m a d e of t h e e f f e c t s of a d r y weight error on p r o p u l s i o n system
p e r f onnance o b t a i n e d b y E l i g h r simulation rechniques
These s t u d i e s
showed that: the p r o p u l s i a n sys tern performance would have the correcl:
r a t i o of thrust-ro-mass flow r a t e b u t the levels of magnitudes of thrust
a n d propellant flow rates would be in error b y zhe same percentage as
t h e e r r o r in initial mass of the v e h f c l e being evaluated. It was t h e r e f o r e concluded that flight s i m u l a t i o n sections of T B C a n d TJM could
p r o c e e d with p o s t f l i g h t evaluations w i t h an assumed i n i t i a l mass as soon
a s they receive the recons e r u c t e d p r o p u l s Lon performance and the observed
mass p o i n t trajectory. Once the final mass is o b t a i n e d , rhe f l i g h t
s i m u l a t e d t h r u s t and propellant f l o w r a t e averages can be s h i f r e d b y
.
�the same percentage as t h e change i n i n i t i a l mass, Ir was a l s o s u g g e s t ~ d
t h a t a s u b - g r o u p to t h e F l i g h t : Evaluation Working Group (FEWG) b e forrntcr
of the c o n t r a c t o r a n d Marshall p r o p u l s i ~ nand weights group representatives.
T h i s s u b - g r o u p would meet as r e q u i r e d to work out i n c o n s i s t e n c i e s
in mass h i s t o r y of the e n t i r e v e h i c l e .
d
.
Powered F l i g h t PQS t f light Trajectory Techniques
The MARLOCK program, which is one a £ t h e maFn t o o l s in
postflight E r a j e c t o r y cons t r u c t i o n , has been e x t e n s iveLy mod if i e d . To
a v o i d c o n f u s i o n , t h i s u p d a bed program has been renamed Guidance and
T r a c k e r Evalua~ion (GATE).
The r e s u l t s of Con t r a c t Bo. NAS8-20249 with
G c r r c r a l Dynamics a1ong r,rith the T r a c k e r E r r o r Model S t u d y b e i n g perfom,;-d
at Y S Y C p r o v i d c d the following i n f u r m a t i o n t h a t was essentiaL b e t o r e
t h e s c n o d if i c a c ions could be i n i t i a t e d :
(I)
The guidance error model c o e f f i c i e n t s and ;he
t r a c k e r error model coef f i c l e n t s are r e l a K i v e l y
u n c o r r e l a t e d (correlation c o e f f i c i e n t s of . 2 1 a r
less).
(2)
The s y s t e m a t i c e r r o r s in a c t u a l radar d a t a can be
r e p r e s e n t e d b y a n error m o d e l which has b e e n
t r u n c a t e d down to LO terms.
$3)
A rruncated t r a c k e r error m o d e l can r e p r e s e n t t h e
systematic e r r o r regardless of the r e l a t i o n s h i p
between the flight path of the vehicle and the
l o c a t i o n of t h e t r a c k e r s i t e .
This program uses t h e Kalman f i l ~ e tro d e t e r m i n e a
"bes t - e s timate" f i t of the teleme t e r e d guidance v e l o c i t y d a t a to he
t r a c k i n g data b y s o l v i n g f o r up to 18 guidance e r r o r model c o e f f i c i e n t s
a n d up to 10 C-Band r a d a r e r r o r model c o e f f i c i e n t s f o r e a c h radar sit€-.
By a p p l y i n g t h e guidance error model c o e f f i c i e n t s b a c k to t h e celenetered
guidance d a t a ,
smooth continuous t r a jeceory rcsul cs . T h i s has b e e n
successfully rricd on SX-203 dara. Although t h e mdthod c o n L i n ~ e sto b e
s o r u t r w l l a t s ~ r i ist i v e tu the clloict: oL L i l e trLror c u c - E f i c i e n t s CQ b e s o l v e d
for, the v z r i a n c e s p l a c e d o n the coefficients, a n d the w c i g h f s p l a c e d on
t h e t r a c k i n g d s t a , i L still produces ex cell en^ r e s u l t s .
Extensive
inves Kiga t i o n a n d analysis are b e i n g perforned a; o r d e r t 3 a c t i r ~it11 1
capabilities a f t h i s program can be accurately u t i l i z e d on AS-501.
A p a p e r un t h i s s u b j c c t e n t i t l e d "Towered r i i g h r T r a j e c t o r y D e t e r m i n a t F o n Techniques as Applied t o S a t u r n V vehiclts" IIZS b e e n
a c c e p t e d f o r p r e s e n t a t i o n a t the A m G u i d a n c e , C o n t r a L and F i i g h t
Dynamics Conf e r e n c c in Huntsville in Augus t. A r ~ u g hd r a f t of t h i s
paper w i l l be completed in t h e very near f u t u r e .
�e.
Orbir Detcrmina t i o n w i t h V c n ~ i n g
h p r o c e d u r e has been i m p l e m e n t ~ d to p c r f o r n a n c
detelrmination of thc p a r k i n g orbit on S a t u r 2 17 v e h i c l e u s i n g p o l )
nomials o b t a i n e d from t h e tulemetered g u i d a n c c d a t a which w i l l in
all n o n - g r a v i t y forces f e l t by t h e v e h i c l e . These d a t a w i l l be 0
rect e s c c p t for acce~crometcrbias in each componcnt. I n t h e p r o r
implemented, considerable e f f o r t is s p e n r processing t h c g u i d a n c e
and p r e p a r i n g accel e r a t i o n polynomials f o r ezch componcnt of t h e
g u i d a n c e coot-dFnatc system. The O r b i t Carrcction Program (OCP) rri
transform t h e s e accelerations t o t h e g e o c e n t r i c i n c ~ s r i a ! coordinat6
s y s tern (Apollo S t a n d a r d C o o r d i n a t e S y s tern No. L.) a n d a d d rhem c!irec
t o the Cetirel L equa Lions of notion. The c a p a b i l i t y to s o l v e for the
b i a s e s in t h e g u i d a n c e accelerations has a l s o b e ~ nfrnplenented.
Th
p r o c e d u r e h a s bccn successfully c h c c k ~ d o u t on t h c S A - 2 0 3 d a t a . Tht
acceleration b i a s e s o b t a i n e d f r m t h i s progrzm si~ouiclb e h e l p f u L iil
t h e g u i d a n c e error a n a l y s i s . MSC will implement a s i m i l a r procedure
f o r t h e i r p o s t f l i g h t o r b i t cletermination. YSC, who will u s e the
guidance acceleration polynomials o b t a i n e r l by MS'FC, are a l s o consid?:
i n g s o l v i n g Eor the b i a s e s i n a similar f a s h i o n . If t h i s is done, i t
should help c o n s i d e r a b l y in the trajectory c o o r d i n a t i o n between MS?C
a n d MSC.
3.
Contracts
a.
-
Boeing Company Contract NAS8-5608,
Schedule i
Emergency Detection S y s t e m
T h e r e s u l t s of a s p e c i a l s ~ u d yr c q u e s t (SSR-117
a s s i g n e d undcr C o n t r a c t KAS8-5608, Schedule 1 1 , P a r t V , E x h i b i t LAUZ,
Task 1 . 0 . ) were r e c e i v e d from TBC. The p u r p o s e of this s t u d y was t o
determine t h e i m p a c t of rcmoving t h e fins from the S a t u r n V Paunch
v e l l i c l c f r o m s t a b i l i t y , E l i g h t dynamics, a n d crnergcncy ~ l c t e c r i o n sys tcm
viewpoints
The c o n c l u s i o n reachecl i s t h a t Sins a r e r e 1 u i r i l 3 . ! i i E l >
f i n s rrrnovrrt, n e i t j ~ e rc o n t r o l g a i n a c l j c l s h e n t nor t!lr u ? e of c o n t r o l
accelcromcter can p r o v i d e s u f f i c i e n t s t a b i l i t y m r y i n s :or a ma1 f u n -t i a n v e h i c l e ; and i n g e n e r a l , f o r malfunction f l i g i ~ : , ; L J d < t l 1 3 c a l
vehicle loss cs waulcl occur w i t h o u t impravcmcna: is:
~ . ~ ~ cin2
' - r n time
.
.
h.
C l u s t e r e d E n g i n e Performance
TEC has i n i t i a t e d four d i f f e r s n t : proqrams whLi.3 will
b e u s e d by t h e i r f l i g h t s i m u l a t i o n s e c t i o n t o deternixe t h e cltls t e r c d
engines analysis f o r the S - I C s t a g c of thc S a t u r c 1' vehicles. The
f i r s t progran is v e r y simple and c a l c u l a t e s o n l y t h e t o r a l e f ? c c t i v ~ f o r c e a c t i n g on t h c v e h i c l e and t h s t o % l vehicie r a s s v c r s u s r i m e .
Thc second and third programs are t h e PISFC Tra j ~ c c o r yX p n i i c a ~ i o n
Me thod (TAM) a n d s i x - d e g r e e s -of freedom Leas t s q u a r e s program,
r e s p e c t i v e l y . The f o u r t h program, o r i g i n a t e d by T C 5 , u s e s t h e
-
�t e l e m e t r y d a t a as t h e basic data types a n d combines them in an o p t i o r r a l
f a s h i n n t n n h t a i n r m p a r i s o n s between the d e r i v s d data s e t s .
This
program only being considered a n d has noE yet been p r o g r a m e d .
D.
F l i g h t Mechanics Branch
A re-work of the AS-204 m i s s ion w i t h t:?e 206 s p a c e c r a f t
The S-TB rilt program, S - I m g u i d a n c e p r z s e t t i n g s , and end c o n d i t i o n s of flight w i l l b e availnble fur deliver::
to R-XSTR on A p r i l 1 4 , 1 9 6 7 .
The range s a f e t y and a b ~ r at n d altern:-,
m i s s i o n documents will be complete b y June 1, 1967. Work on meetizg
t h r~l ~ i7 . v ~ r ydate f o r s u p p o r t i n g rhe 204 m i s s i o n will take priori;.?
over a l l other work.
(Dl) has been i n i t i a ' e d .
Tnc revised r e f e r e n c e trajectory f o r 205 has b e e n d i s t r i ' n u ted h y R-AERO-FMR- 52-67, d a t e d F e b r u a r y 13 1967 - The r a n g e
s a f e t y 2nd d i s p e r s i o n a n a l y s i s have been reviewed and f o u n d a c c e p r able. These do cum en:^ s h o u l d be d i s t r i b u t e d by A p r i l 1 4 , 1967.
The f i n a l AS-205 operational t r a j e c t o r y has been
completed.
The AS-208 preliminary o p e r a t i o n a l trajectory which
presents d a t x f o r t h e f i r s t and second o p p o r t u n i t i e s Fs a l s o complete.
R-P&VE-E" l a s requested t h a t t h e PU (valve o f f the s to a )
s h i f t time be moved from 280 to 250 seconds on AS-208 to p r o v i d e a
higher w e l i a b i l i t y of g e t t i n g t h r u s t slopes c a l l e d o u t by rhe guic2. x c e
r e s t r i c t i o n guidelines.
Concurrence to t h i s proposal l r a s g i v e n .
R ~ c e n t l y , a decision was made t o l-iave t h e AS-2'35 l a u n h
v e h i c l c c a r r y a Block I1 spacecraft on a m i s s i o n simi1, r to t h e 0171
8 5 - 2 0 4 m i s s i o n . Work will b e g i n shortly to s u p p o r t th s effort,
The AS-206 d i s p e r s i o n a n a l y s i s r c p o r t :bzs bczn d i s t r l i l u r ~ d
by memorandzlm R-AERO-FM-49-67, F e b r u a r y 9, 1 3 6 7 .
Tne rasge s a f ~ t y
a n a l y s i s is pub1 ished i n R-AERO-FMR-57-67, F e b r u a r y 2 3 , i 9 ~ 7 . The
f i n a l operational, t r a j e c t o r y document: has b e e n r c t u ~ n c d L Q C C S 3 fo-re-publication. IL Td2s "accepter?, when cormnents are i n c o r p o r a ~ e d . "
A d r a f t of the a b o r t and alternate m i s s i o n document r e L e i v e d from
CCSD i s b e i n g reviewed.
S e v e r a l t r a j e c t o r i e s have been generated r o s u p p a r t E
p o s s i b l c passtvation c x c s c i s c on AS-206.
LC
�The AS-201 preliminary operational t r a j e c r o r y r e p o r t is
b e i n g s h i p p e d from CCSD.
The S - I B tilt and end c o n d i t i o n s of f l i g h t have b e e n
r e c e i v e d on AS-209.
These v e h i c l e s were targeted to the 2051208
rendezvous end c o n d i t i o n s .
5.
Orbital D e b r i s
Memorandum R-AERO-FM- 25-67, "Debris Hazard A n a l y s i s
P r i o r i t y , I f was p u b l i s h e d in response to " ~ e b r i sk z a r d A n a l y s i s f o r
O r b i t a l Reentry," I-MO-3-67, J a n u a r y 5 , 1967.
A draft of the final r e p o r t an S a t u r n IB Risk Hazard,
received from Lockheed, appears K O b e a c c e p r a b l e .
A new s t u d y c o n t r a c t covering March 31, 1967 through
March 3 1 , 1 9 6 8 t o analyze o r b i t a l d e b r i s problems r e l a t e d to S a t u r n IB
and S a t u r n V l a u n c h v e h i c l e s has been a p p r o v e d .
The Boeing Company' s f i n a l operational Era jectory document
has been r e v i e w ~ d . It has been found s a t l s f a c ~ o r yif they re-submit t h e
docurnenc correcting many a d m i n i s t r a t i v e e r r o r s .
Several of the S - I n AS-501
b y R-AERO-FMT to v e r i f y Boeing results.
and h i g h m i x t u r e r a t i o d i s p e r s i o n s . The
mately 9200 pounds of f l i g h t performance
d i s p e r s i o n c a s e s have been r u n
Of most concern were S-IVB ].ow
low MR c a s e r e q u i r e d approxireserve.
A p r e s e n t a t i o n prepared f o r D r . Geissler on opfrational
l u n a r rargeting and p~sformancereserve requirements for S a t u r n V AS-501
was g i v e n by M r . Gerald W i t t e n s t e i n of R-AERO-MT.
MSC has b e e n s u p p l l e d with the d a t a t h a t they r e q u e s t e d
f o r Q = 1 PSF.
They have also been s u p p l i e d S-IVB t h r u s t h i s t o r y for
their simulations.
A s p e c l a 1 work r e q u e s t has b e e n generaLed Lor TBC to perlorm
an S-IVB l u n a r i m p a c t p r o b a b i l i t y s t u d y and the AS-502 two-opportunity
problem.
The f i n a l ground r u l e s for AS-502 r a n g e s a f e t y have been
agreed upon.
�A rough d r a f t of the AS-502 abort and a l t e r n a t e m i s s i o n
documene has been r e c e i v e d from TBC.
T h i s has been reviewed a n d
comments made in a memo.
Red limit l i n e s f o r AS-502 have been e s t a b l i s h e d between
TEC, KSC (Range), and R-AERO-FNT.
The AS-SO2 u p d a t e d guidance presettings from TBC have been
r e v i e w e d and found s a t i s f a c t o r y .
The AS-502 p r e l i m i n a r y o p e r a t i o n a l trajectory document
r e c e i v e d from TBC is b e i n g v e r i f i e d . The trajeckory has been v e r i f i e d
and is a c c e p t a b l e .
The AS-502 final operational trajectory g r o u n d r u l e s have
been a g r e e d upon.
U s i n g 502 data a n d sample 5 0 4 rargzting, operational
t a r g e t i n g p r o c e d u r e s for LLM e f f o r t are being established.
R-AERO-FMT has received a copy of t h e s o u r c e deck of the
j o i n r s p a c e program s o t h a t m o d i f i c a t i o n s can be made for f u r t h e r
a u t o m a t ion.
9.
M i s c e l laneous
The required Cape t a p e parameters have been p r o g r a m e d
in Fartran IV f o r R-AERO-FMT' s 6-D MARWS s i m u l a t i o n .
A copy of t h e S a t u x n V plot deck has been given to the
Boe ing Company.
�W i l h o l d , G. A * , "S-TVB Forward S k i r t Panel F l u t t e r w i t h Respect to
t h e S a t u r n V Vehicle Series ,I1 Office Memo R-AERO-RU-67-6, J a n . 25,
1967.
Walkex, R. W., " P r e d i c t e d Drag C o e f f i c i e n t a n d C e n t e r of Pressure
Needed in Conducting D r i f t S t u d i e s f o r the Saturn V Vehicle at
Launch," O f f i c e Memo R-AERO-AU-67-10,
Feb. 1 7 , L967.
Schutzenhofer, L. A . , "Prelftninary, F l u c t u a t i n g Pressure Data from
the AEDC 4 P e r c e n t Saturn V Model E ~ p e r i m e n t , ~Office
'
Memo R-AEROAU-67-12, Feb. 21, 1967.
Reed, T. G., "Accuracy of the Ground W i n d s , Wind Tunnel Model ~ a t a , "
O f f i c e Memo B-AERO-AU-67-15, Feb. 2 4 , L967.
" ~ c o u s t i c a lE f f e c t s Produced by V a r i a t i o n of C l u s t e r
C o n f i g u r a t i o n , " O f f ice Memo R-AERO-Au-67-16, Feb, 2 4 , 1967.
G u e s t , S.,
Schutzenhofer, I,. A , , "Preliminary, One-third Octabe Fluctuating
Pressure Spectrums f r o m the AEDC 4 P e r c e n t Saturn V Model E x p e r i ment," Office Memo R-AERO-RU-67-19, March 1, 1 9 6 7 .
Walker, R. W., '"redicted R e s u l t a n t : Bending Moments due to Graund
W i n d s f o r Saturn IB (AS-206) Unfueled and Fueled Weight CondFti~ns,~'
O f f i c e Hem0 R-AERO-AU-61- 24, March 8, 1967.
Walker, R. Id., "Extrapolation of Saturn D Graund Winds Wind Tunnel
Test: Data to a Wind Magnitude of 100 Knots," R-AERO-AU-67-29,
March 2 0 , 1 9 6 7 .
G u e s t , S . , f I B l a s t Overpressure vs D i s t a n c e from a Propellant Loaded
S - I C a n d S-I1 S t a g e Separately P o s i t i o n e d in he S-IC S t a t i c T e s t
S t a n d (MSFC F a c i l i t y 4 6 7 0 ) , " Off ice Memo R - A E R O - A L ! - ~ ~ - ~ ~March
,
27,
1967.
Rochelle, W, C., "Review of Thermal R a d i a t i o n from L i q u i d and S o l i d
Propellant Rocket Exhausts,'QASA 'I1M X-53597, Feb. 20, 1967.
McCarter, James W., "Analog SirnuPation of 21-11 S t a g e P r o p e l l a n t
U t i l f z a t i o n System," NASA TM X-53580, Feb. 2 3 , 1 9 6 7 .
Worley, R. Eugene, W. L. Brady, and George F. YcDonough, "Preliminary
A n a l y s i s of a Cablc R e t r i e v a l Technique for the T e t h e r e d Am Workshop,'
NASA TM X-53583, March 1, 1967.
�BIl3ZIOGRAPITY {Continued)
13.
Glasgow, Robert M., " S t a t i c Aerodynamic Characteristics of the
Aborted Apollo-Saturn V Vehicle," NASA TH X-53587, March 9, 1 9 4 7 .
14.
Duncan, J. Reynolds, "Preliminary S a t u r n VJVoyager T r a j e c t o r y f r o m
E a r t h to Mare," NASA TN X-53588, Maxch 10, 1 9 b 7 ,
15.
Scissum, J e a n e t t e A . , "'Survey of Solar Cycle P r e d i c t i o n Models ,"
KASX P
I X-53593, March 30, 1967.
16.
S h e a t s , 5 . I?. , "Trajectory A p p b i c a t t o n Nethod ," Aero-As tradynarnics
Internal Note No, 1-67, March 21, 1967,
�APPROVAL
7,
=
I
7,
7
, 1
--
E.
D. Geisslcs
D i r e c t o r , Aeso-As trrodynamics L a b o r a t o r y
D ISTRIBETION
R-AERO-DIR
D r . Geissler
Mr. Jean
R-AERO-R
Nr. B u t l e r (4)
Mrs. High towcr
R-AFRO-P
(8)
R-AERO-D (16 )
R-AERO-A ( 2 0 )
R-AERO-G (20)
R-AERO-Y
R-AEIIO-F
R-AERO-X
R-DIR
(5)
(8)
(2)
.
PAO, Mr. R u r t t
MS-H,
I-V-P,
I-V-P
Miss Jerre1.l ( 3 )
Harold P r i c e
Mr. Jennings
R-AERO-T
Mr. von Puttkamer
Mr. Murphreo
Mr. C m i n g s
Mr. Dickey
N r . Heybey
Mr. L a v e n d e r
Mr. J a n d ebeur
Dr. iiu
D r . Krause
�
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000041
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: February - March 1967."
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George C. Marshall Space Flight Center
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1967-04-01
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1960-1969
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Saturn Project (U.S.)
NASA space programs
Project management
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Progress reports
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Saturn V Collection
Box 21, Folder 22
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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Text
AERO-ASTRODWICS LABORATOTY
BIMONTHLY PROGRESS REPORT
P
I?
December 12. 1966
7
.
- \
.
INDEX
Page
I
............................
PROJECTS OFFICE ...........................................
ADVANCED STUDIES' OFFICE ...................................
AEROSPACE ENVIRONMENT DIVISION ............................
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ................
A . O p t i m i z a t i o n Theory Branch ............................
B . Astrodynamics Branch ..................................
C . Guidance Theory Branch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
D . S c i e n t i f i c A d v i s o r y Committee . . . . . . . . . . . . . . . . . . . . . . . . .
AEROPHYSICS DIVISION ......................................
A . F l u i d Mechanics R e s e a r c h O f f i c e .......................
B. M e c h a n i c a l Design O f f i c e ..............................
C . Aerodynamic Design Branch .............................
D . E x p e r i m e n t a l A e r o p h y s i c s Branch . . . . . . . . . . . . . . . . . . . . . . .
E . Thermo Environment Branch .............................
.
TECHNICALAND SCIENTIFIC STAFF
.
11
.
111
.
v.
IV
VI
.
F
VII
.
.
DYNAMICS AND FLIGHT MECHANICS DIVISION . . . . . . . . . . . . . . . . . . . .
A . Multi-Projects
B
Saturn V
C
S a t u r n IB
D
S a t u r n A p o l l o A p p l i c a t i o n Program
E. Other P r o j e c t s
F
General
.
.
.
VIII
Unsteady Aerodynamics Branch . . . . . . . . . . . . . . . . . . . . . . . . . .
.
........................................
.............................................
......................................
.....................
........................................
...............................................
.
FLIGHT TEST ANALYSIS DIVISION .............................
A . S p e c i a l P r o j e c t s O f f i c e ...............................
B . F l i g h t E v a l u a t i o n Branch ..............................
C . F l i g h t Mechanics Branch ...............................
D . T r a c k i n g and O r b i t a l A n a l y s i s Branch ..................
1
9
13
16
18
18
22
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�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
December 1 2 , 1966
I.
TECHNICAL AND SCIENTIFIC STAFF
A.
M r . Lavender
1.
A p o l l o T e l e s c o p e Mount
A c t i v i t y c e n t e r e d on t h e combined AS 209-212 ATM/OWS e f f o r t .
P r e s e n t a t i o n s were g i v e n t o D r . M u e l l e r on October 7 and October 20.
The MSFC e f f o r t h a s b e e n s u c c e s s f u l . Our recommendations have b e e n
a p p r o v e d i n c l u d i n g t h e unmanned l a u n c h o f t h e OWS, t h e m u l t i p l e docking
a d a p t e r , r e s u p p l y module, and t h e L,M/ATM.
The f i r s t r e l e a s e of G e n e r a l
System O p e r a t i n g Requirements f o r t h e S a t u r n - A p o l l o
Specification
A p p l i c a t i o n s Combined M i s s i o n O r b i t a l Workshop/Apollo T e l e s c o p e Mount,
d a t e d November 28, h a s b e e n p r e p a r e d by T e c h n i c a l Systems O f f i c e , R-TO.
M r . Teague, R-AERO-P, w i l l now assume t h e AERO p r o j e c t e n g i n e e r i n g
r e s pons ibj.1 i t i e s f o r t h e combined m i s s i o n .
-
2.
P r o j e c t Able
Mid- t e r m p r e s e n t a t i o n s were g i v e n by t h e f i v e c o n t r a c t o r s
on O c t o b e r 4-7 a t MSFC and t o NASA H e a d q u a r t e r s on October 11. M r .
C a r t e r , R-AS, gave a summary p r e s e n t a t i o n t o DOD on October 26. F i n a l
p r e s e n t a t i o n s were g i v e n by t h e c o n t r a c t o r s on November 15-17. An
e x e c u t i v e b r i e f i n g t o D r . von Braun was g i v e n November 9. F i n a l r e p o r t s
a r e due from t h e c o n t r a c t o r s i n e a r l y December. An MSFC r e p o r t i s
planned t o e s t a b l i s h o u r p o s i t i o n .
P r o j e c t Thermo
During a P r o j e c t Thermo s t a t u s b r i e f i n g b y P&VE t o D r .
von Braun and t o p MSFC t e c h n i c a l management on O c t o b e r 3 , 1966,
D r . v o n Braun s u g g e s t e d t h a t a n i n v e s t i g a t i o n b e made on combining t h e
P r o j e c t Thermo o r b i t a l o p e r a t i o n w i t h t h e S-IVB workshoplATM combinat i o n . R-P&VE-A ( w i t h R-AERO' s a s s i s t a n c e ) i s i n v e s t i g a t i n g v a r i o u s
P r o j e c t Thermo m i s s i o n o p e r a t i o n s modes, i n c l u d i n g t h e one s u g g e s t e d by
D r . von Braun. We i n t e n d t o r e p o r t t h e r e s u l t s o f t h i s i n v e s t i g a t i o n
t o D r . von Braun a t a n e a r l y d a t e .
On O c t o b e r 1 7 , 1966, a P r o j e c t Thermo s t a t u s b r i e f i n g
( s i m i l a r t o t h e one g i v e n t o D r . von Braun) was g i v e n t o OMSF. The
r e c e p t i o n was q u i t e f a v o r a b l e . A follow-on b r i e f i n g t o D r . G. E.
Mueller is a n t i c i p a t e d i n t h e n e a r f u t u r e .
�The t h i r d c o n t r a c t i n t e r f a c e m e e t i n g was h e l d i n November
between MSFC, DAC, and GAEC. The Phase C f i n a l d e f i n i t i o n i s due t o
b e g i n i n March 1967 and w i l l r e q u i r e i n c r e a s e d i n - h o u s e p a r t i c i p a t i o n .
4.
ESMRO (Experiments f o r S a t e l l i t e and M a t e r i a l Recovery
from O r b i t ) S t u d y C o n t r a c t NAS8-18119 (R-AS-VO)
On September 28, 1966, R-COMP-RDS t r a n s f e r r e d t h e Sequenci n g O p t i m i z a t i o n A u t o m a t i c Program (SOAP) f o r a s t r o n a u t time1 i n e
a n a l y s i s and t h e I t e r a t i v e S o l u t i o n Program ( o r b i t a l t r a n s f e r ) , a s
a u t h o r i z e d i n R-AERO-FT-37-66, d a t e d August 31, 1966, t o Emerson
E l e c t r i c Company (EEC;' s u b c o n t r a c t o r t o B a l l B r o t h e r s R e s e a r c h Corporat i o n on t h i s s t u d y ) . EEC w i l l u s e t h e s e programs, and a n y EEC improvements a r e t o b e r e t u r n e d t o MSFC a t t h e end o f t h e s t u d y .
On O c t o b e r 7 , 1966, R-COMP-RDS t r a n s f e r r e d t h e FORTRAN I V
Cowell Program (SOAP l o a d i n g program) and t h e s u n and moon ephemeris
t a p e ( a s a u t h o r i z e d i n R-AERO-FT-46-66, d a t e d September 30, 1966) t o
EEC. T h i s m a t e r i a l supplements t h e e a r l i e r t r a n s m i s s i o n t o EEC.
An ESMRO midterm program r e v i e w b r i e f i n g was h e l d a t MSFC
on November 8 , 1966. Most r e c e n t a c t i v i t y h a s b e e n d i r e c t e d toward
p l a n n i n g a v i s i t t o t h e u n s u c c e s s f u l OAO s a t e l l i t e .
B.
Mr.
Cummings
1.
S t a t i s t i c a l Data P r o c e s s i n g
Cons i d e r a b l e c o o r d i n a t i o n and d e t a i l e d i n v e s t i g a t i v e work
was r e q u i r e d t o overcome t h e problems a s s o c i a t e d w i t h c a l i b r a t i o n s i g n a l s
and r e c o r d i n g c o n v e n t i o n s on t h e m a g n e t i c t a p e s c o n t a i n i n g t h e a n a l o g
d a t a from D r . F i s c h e r , I I T . However, once t h i s was s t r a i g h t e n e d o u t ,
t h e d a t a p r o c e s s i n g proceeded a s p l a n n e d . The c o r r e l a t i o n s o b t a i n e d
w e r e , i n g e n e r a l , v e r y low a s D r . F i s c h e r had t o some e x t e n t a n t i c i p a t e d .
The p r e s e n t program performed w e l l i n d e t e c t i n g t h e s e small c o r r e l a t i o n s .
The c o m p l e t e s e t o f d a t a h a s b e e n c o m p l e t e l y p r o c e s s e d and r e t u r n e d i n
good c o n d i t i o n t o D r . F i s c h e r .
2.
Computer Program E v a l u a t i o n
The t e s t c a s e s which h a v e p r e v i o u s l y b e e n m u t u a l l y a g r e e d
upon by a l l concerned p a r t i e s as n e c e s s a r y t o a d e q u a t e l y e v a l u a t e t h e
c o n c e p t s , a p p r o x i m a t i o n s , and a s s u m p t i o n s c o n t a i n e d i n t h e computer p r o gram p r e v i o u s l y p r e p a r e d by R-COMP-RRV and R-AERO-AM a s d i s c u s s e d i n
t h e September 1966 monthly p r o g r e s s r e p o r t w i l l s t i l l n o t b e completed.
R e s u l t s of t h e r e m a i n i n g r e q u e s t e d r u n s a r e needed t o f i n i s h t h e
e v a l u a t i o n and t o document t h e s e new t e c h n i q u e s and t h e i r r e l a t i v e
performance a s compared t o more c o n v e n t i o n a l t e c h n i q u e s .
�3.
Program f o r S p e c t r a l Decomposition
The f i r s t c u t o f a computer program f o r t h e s p e c t r a l
d e c o m p o s i t i o n of c r o s s - c o r r e l a t i o n f u n c t i o n s , a s o b t a i n e d from t h e p r o gram d i s c u s s e d i n i t e m ( 2 ) above f o r t h e p i e c e w i s e e s t i m a t i o n o f c o r r e l a t i o n f u n c t i o n s , h a s been d e v e l o p e d and i s b e i n g w r i t t e n up a s t h e b a s i s
o f a programming r e q u e s t t o R-COMP-RRV.
The w r i t e - u p w i l l c o n t a i n t h e
p e r t i n e n t e q u a t i o n s , t h e l o g i c a l f l o w c h a r t s , and v e r y d e t a i l e d sample
c a s e s which w e r e c a r e f u l l y c h o s e n and e v a l u a t e d t o s e r v e a s a s p e c i f i c
check o f a l l p r e s e n t l y c o n c e i v e d major a s p e c t s o f t h e program. A r o u g h
d r a f t o f t h i s document was f i n i s h e d b e f o r e t h e l o s s o f M r . Q . D. P e a s l e y
t o R-RP-N.
4.
S c a n n i n g Geometry
The i n i t i a l i n v e s t i g a t i o n s o f t h e g e o m e t r i c c o n s i d e r a t i o n s
i n v o l v e d i n t h e e x p e r i m e n t a l s e t - u p and t h e s c a n n i n g o p e r a t i o n s f o r t h e
v a r i o u s p l a n n e d c r o s s e d - b e a m e x p e r i m e n t s h a s b e e n o n l y p a r t i a l l y comp l e t e d and e v a l u a t e d .
The r e m a i n i n g work h a s b e e n l a i d a s i d e f o r t h e
e a r l y and t i m e l y i n v e s t i g a t i o n o f o t h e r problems o f o u r p r o p o s e d measurement o f a t m o s p h e r i c w i n d s .
5.
N o n - S t a t i o n a r y Winds
A sequence o f experiments i s being planned f o r s i m u l a t i o n
on t h e IBM 7094 computer t o i n v e s t i g a t e a n d / o r d e t e r m i n e t h e v a r i o u s
t y p e s o f l i m i t a t i o n s t h a t may be r e q u i r e d i n a p p l y i n g o u r p r e s e n t l y
a v a i l a b l e and p l a n n e d programs t o t h e s t a t i s t i c a l d e t e c t i o n and m e a s u r e ment o f n o n - s t a t i o n a r y wind d a t a . A s e t o f c l e a r p o s i t i v e r e s u l t s from
t h e s e e x p e r i m e n t s may n o t be o b t a i n e d , b u t i f t h e y a r e , much t i m e and
expense w i l l be saved i n p r e p a r i n g f o r o u r atmospheric t e s t s ; i f n o t ,
t h e n we w i l l have g a i n e d , a t l e a s t , needed i n s i g h t i n t o s e v e r a l o f t h e
c h a r a c t e r i s t i c s and a r e a s o f g e n e r a l i t y t h a t must be b u i l t i n t o t h e f u t u r e
programs f o r s u c h n o n - s t a t i o n a r y measurements.
C.
D r . Heybey
Some o f t h e more i m p o r t a n t p o i n t s which have emerged from t h e
s t u d y o f e a r l i e r p a p e r s o n t h e crossed-beam method a r e l i s t e d below.
1. The method, i n p r i n c i p l e , c a n employ any form o f e n e r g y t h a t
c a n be b u n d l e d i n t o beams and u n d e r g o e s l o s s e s when t h e s e p a s s thro-ugh
a medium w i t h o u t a f f e c t i n g i t t h e m s e l v e s .
The beams may be c r e a t e d o u t s i d e t h e medium o r t h r o u g h p h y s i c a l p r o c e s s e s ( r a d i a t i o n ) i n s i d e i t . I n
t h e l a t t e r c a s e , d e t e c t o r s o n l y a r e needed.
The e n e r g y e m i t t e d may i n
c i r c u m s t a n c e s t r a v e l o n c u r v e d p a t h s whose c o u r s e i t m i g h t be d i f f i c u l t
t o assess.
I f i t d o e s n o t , t h e s t r a i g h t l i n e o f s i g h t m a y be t a k e n a s
t h e a x i s o f t h e beam.
The method r e m a i n s a p p l i c a b l e s i n c e i t d o e s n o t
c a l l f o r t h e knowledge o f t h e s o u r c e i n t e n s i t y .
�2.
The i n t e n s i t y l o s s p e r u n i t l e n g t h o f t r a v e l i s t a k e n a s
proportional t o the local intensity.
The p r o p o r t i o n a l i t y f a c t o r , o r
e x t i n c t i o n c o e f f i c i e n t , K , w i l l depend o n t h e n a t u r e o f b o t h t h e e n e r g y
employed and t h e medium t r a v e r s e d .
It i s r e q u i r e d t h a t any f l u c t u a t i o n s
i n t h e magnitude o f K a r e c a u s e d by f l u c t u a t i o n s i n t h e medium a l o n e
( a b o u t w h i c h o n e w a n t s i n f o r m a t i o n ) . A c a r e f u l c o n s i d e r a t i o n must be
g i v e n i n any i n s t a n c e t o p o s s i b l e e n e r g y f l u c t u a t i o n s of t h e s o u r c e .
3 . It i s assumed t h a t , a t any i n s t a n t , t h e s t a t e o f t h e medium
i s t h e same o v e r a g i v e n c r o s s s e c t i o n o f t h e beam (which t h e r e f o r e must
be n a r r o w , s t r i c t l y s p e a k i n g , o f d i f f e r e n t i a l w i d t h ) .
One c a n t h e n
d e f i n e ( b u t n o t m e a s u r e ) t h e t e m p o r a l mean v a l u e , i?, o f K a t a g i v e n
" s t a t i o n " o f t h e beam.
I n d e r i v i n g t h e m a t h e m a t i c a l a p p a r a t u s t h e major
a s s u m p t i o n i s made t h a t t h e i n t e g r a l o v e r t h e d i f f e r e n c e , k = K = I?,
t a k e n a l o n g t h e beam l e n g t h , i s a l w a y s much l e s s t h a n u n i t y .
This
a p p e a r s a s w a r r a n t e d i f t h e ( p o s i t i v e and n e g a t i v e ) d e v i a t i o n s o f K
from t h e t e m p o r a l mean a r e s m a l l a t e v e r y s t a t i o n , a s c a n be e x p e c t e d ,
f o r i n s t a n c e , i n boundary l a y e r o r f r e e - j e t t u r b u l e n c e . More d o u b t f u l
i s t h e a p p l i c a t i o n of t h e c u r r e n t mathematics t o w i l d l y f l u c t u a t i n g ,
e . g . , s e p a r a t e d o r r o c k e t exhaust flows.
4. The t i m e - r e c o r d produced o n t h e d e t e c t o r s i d e e x h i b i t s
t h e e x t i n c t i o n c o e f f i c i e n t f l u c t u a t i o n s superimposed by t h o s e g i v e n o u t
by t h e i n s t r u m e n t a t i o n .
The t e c h n i c a l problem o f e x t r i c a t i n g s i g n a l
from n o i s e c a n be t a k e n a s s o l v e d i n a t h e o r e t i c a l i n v e s t i g a t i o n .
5 . M a t h e m a t i c a l l y , two beams, 1 and 2 , a r e c r o s s e d by m u l t i p l y i n g t h e l i n e i n t e g r a l s o v e r k a l o n g t h e two p a t h s .
P h y s i c a l l y , t h e two
beams c a n be a l l o w e d t o t r a v e l a t some d i s t a n c e from e a c h o t h e r (no
actual crossing taking place).
The beam d i r e c t i o n s a r e c o n v e n i e n t l y
a l i g n e d p a r a l l e l t o two a x e s o f a r e c t a n g u l a r C a r t e s i a n s y s t e m .
It i s
assumed t h a t t h e s h o r t e s t c o n n e c t i o n between t h e beams ( p a r a l l e l t o t h e
t h i r d a x i s ) d e f i n e s c o o r d i n a t e d p o i n t s ( o r r a t h e r v o l u m e s ) o n t h e beams.
The p r o p e r p l a c i n g o f t h e t h r e e a x e s i s a t h i n g t o ponder i n e v e r y
experimentation.
It i s , o f c o u r s e , n o t n e c e s s a r y t h a t t h e y a r e m u t u t a l l y
orthogonal.
6 . I f t h e beam d i r e c t i o n s a r e d e s i g n a t e d by x l and x,,
t e m p o r a l c o v a r i a n c e o f t h e two i n t e g r a l s can be w r i t t e n a s
the
�p r o v i d e d a n exchange i n t h e s e q u e n c e o f i n t e g r a t i o n p r o c e s s e s i s l e g i t i mate.
T h i s f o r m u l a i s t h e main r e s u l t of t h e c u r r e n t m a t h e m a t i c a l
development.
The f a c t o r of p r o p o r t i o n a l i t y l e f t u n w r i t t e n h e r e i s t h e
wroduct o f t h e t i m e - a v e r a g e d i n t e n s i t i e s measured a t t h e d e t e c t o r s i d e .
The v a l u e of R can b e found e x p e r i m e n t a l l y ; i t w i l l v a r y when t h e beams
a r e d i s p l a c e d . The a v e r a g i n g o f t h e (kl, k 2 ) - p r o d u c t b e g i n s a t a f r e e l y
c h o s e n t i m e t + c and i s c o n t i n u e d u n t i l t h e r e s u l t , from a c e r t a i n T o n ,
remains v i r t u a l l y c o n s t a n t .
( I f t h i s could n o t b e a c h i e v e d , t h e p r e s e n t
method would b r e a k down.)
I n g e n e r a l , t h e v a l u e of R, f o r a g i v e n beam
c o m b i n a t i o n , w i l l depend on t h e c h o i c e of t9:.
So w i l l a n y p h y s i c a l
q u a n t i t y e l i c i t e d from i t . The b e s t one c a n hope f o r i s t h a t i t w i l l
v a c i l l a t e w i t h i n t h e e r r o r m a r g i n i n h e r e n t i n t h e measurement and t h u s
can b e a s s i g n e d a s u i t a b l e c o n s t a n t v a l u e . O t h e r w i s e , one may a r r i v e
a t a mean v a l u e by a v e r a g i n g o v e r t 9 ~ .
7 . The c o v a r i a n c e , Rk of t h e ( k l , k,) - p r o d u c t , i . e . , t h e
i n n e r ( l i m i t - ) i n t e g r a l i n t h e e x p r e s s i o n f o r R, c a n b e w r i t t e n i n form
of a ( q u a d r u p l e ) F o u r i e r i n t e g r a l . The i n t e g r a n d i n i t i s t h e mathem a t i c a l e x p r e s s i o n of a p l a n e wave; t h e i n t e g r a t i o n g o e s o v e r a t r i p l y
i n f i n i t e s e t of wave numbers (and o v e r t i m e ) .
Those m a t h e m a t i c a l waves
h a v e a l l c o n t i n u o u s l y d i f f e r e n t v e l o c i t i e s , d i r e c t i o n s , and a m p l i t u d e s .
It i s n o t w i s e , I b e l i e v e , t o a s s i g n them p h y s i c a l r e a l i t y , a s sometimes
seems t o b e done ("The t u r b u l e n t m o t i o n c o n s i s t s of p l a n e waves . I r ) . With
d i f f e r e n t beam c o m b i n a t i o n s , t h e d i f f e r e n t v a l u e of Rk w i l l be d e s c r i b e d
by a s y s t e m of waves w i t h d i f f e r e n t a m p l i t u d e s . One i s t h u s f a c e d w i t h
i n f i n i t e l y many s e t s of i n f i n i t e l y many p l a n e waves o f v a r i e d c h a r a c t e r .
I t i s n o t i m p o s s i b l e t h a t some of t h e waves can b e g i v e n p h y s i c a l s i g n i f i c a n c e , b u t t h i s must be d e m o n s t r a t e d b y a r g u m e n t a t i o n i n d e p t h .
The v a l u e s o f Rk and R c a n be made d i m e n s i o n l e s s by a s u i t 8.
On i n t e g r a t i o n
a b l e n o r m a l i z a t i o n , l e t us c a l l them
and R* t h e n .
o v e r t h e beam l e n g t h s and t h e c o n n e c t i n g l i n e , one o b t a i n s t h r e e c h a r a c t e r i s t i c l e n g t h s c a l e s . As l o n g a s t h e f l u c t u a t i o n s a r e u n c o r r e l a t e d ,
t h e c o v a r i a n c e Rk w i l l b e z e r o .
The i n v e r s e of t h i s s t a t e m e n t i s n o t
g e n e r a l l y t r u e ; a nonlinear r e l a t i o n s h i p can e x i s t then.
Excluding t h i s
p o s s i b i l i t y , one may s a y t h a t t h e c o r r e l a t i o n volume w i l l be c o m p a r a b l e
i n s i z e t o t h e volume d e l i n e a t e d by t h e t h r e e l e n g t h s c a l e s , a l t h o u g h ,
i n comparing them, one m u s t u s e t h e m e a s u r a b l e q u a n t i t y R* i n s t e a d o f R;.
I n t h i s way one can judge how f a r t h e m e t h o d ' s o r i g i n a l o b j e c t i v e h a s
been achieved:
t o e l i c i t local information without disturbing the
medium.
I n t h e c a s e of s e p a r a t i o n beams, t h e c o r r e l a t i o n volume w i l l
e n v e l o p t h e s h o r t e s t s t r a i g h t c o n n e c t i o n between them.
I f the l a t e r a l
l e n g t h s c a l e s a r e of m i n u t e s i z e , t h e r e e x i s t s a c o r r e l a t i o n more o r
l e s s c o n f i n e d t o t h e two e n d p o i n t s of t h e c o n n e c t i n g l i n e .
In his
r e p o r t s , D r . F. K r a u s e s e t s up s u f f i c i e n t c o n d i t i o n s i n w h i c h , i n t h e
c a s e o f t u r b u l e n t f l o w , s u c h a t w o - p o i n t c o r r e l a t i o n c a n b e o b t a i n e d whcn
t h e l a t e r a l s c a l e s a r e n o t s m a l l . W i t h medium-sized l a t e r a l s c a l e s ,
i s o t r o p i c t u r b u l e n c e must b e s t i p u l a t e d . W i t h l a r g e l a t e r a l s c a l e s ,
t h e r e i s a m a t h e m a t i c a l c o n d i t i o n w h i c h i s a p p l i c a b l e t o o t h e r phenomena
a s w e l l , b u t may n o t a l w a y s b e s a t i s f i a b l e i n p h y s i c a l r e a l i t y .
RE
RE
�D r . Liu
D.
1.
V e h i c l e Dynamics
The dynamics o f a s p a c e v e h i c l e due t o t h e v i b r a t i o n s of
i t s e l a s t i c e l e m e n t s , mass t r a n s l a t i o n s , d o c k i n g , e t c . , a r e b e i n g
s tud i e d
.
2.
High Speed B a l l o o n Dynamics
S t u d y on u s i n g a l a r g e b a l l o o n f o r t h e r e c o v e r y of a
The i n t e r a c t i o n between t h e l a r g e
r e u s a b l e r o c k e t s t a g e is under way.
e l a s t i c d e f o r m a t i o n o f t h e b a l l o o n and t h e aerodynamic p r e s s u r e r e s u l t s
i n a v e r y c o m p l i c a t e d dynamic problem.
The o b j e c t of t h i s work i s t o
d e t e r m i n e t h e s i z e , maximum s t r e s s , and t h e s p e e d of t h e b a l l o o n .
E.
M r . von P u t t k a m e r
1.
Advanced Launch V e h i c l e T r a j e c t o r y R e s e a r c h (Nor t h r o p C o n t r a c t S .O. 1 5 )
a.
Rocket P r o p u l s i o n Models
The computer r o u t i n e p r e v i o u s l y developed t o s i m u l a t e
t h e f l i g h t of v e r t i c a l l y launched t w o - s t a g e r o c k e t v e h i c l e s , t h e VTOo n l y program, h a s b e e n u p d a t e d .
S p e c i f i c a l l y , t h e sequencing of p r i n t
s t a t e m e n t s and t h e program l o g i c used f o r p r i n t - o u t c o n t r o l have been
improved.
Some f u r t h e r s t r e a m l i n i n g was done i n t h e p r o c e s s .
I n g e n e r a l , t h e development o f t h e VTO-only, HTO-only,
and HTO-sonic boom computer programs h a s b e e n e s s e n t i a l l y completed.
The r e s p e c t i v e d e c k s have been r e c e i v e d from t h e c o n t r a c t o r , a n d a r e p o r t
i s b e i n g p r e p a r e d t o document a l l t h r e e programs u n d e r a s i n g l e c o v e r .
b
.
A i r b r e a t h e r P r o p u l s i o n Model
Logic h a s b e e n added t o t h e K T O - a i r b r e a t h e r program
t o s i m u l a t e t h e c o n s t a n t dynamic p r e s s u r e p h a s e o f t h e l a u n c h t r a j e c t o r y . A s u b r o u t i n e t o c a l c u l a t e t h e i n l e t d u c t p r e s s u r e behind t h e
o b l i q u e f u s e l a g e s h o c k h a s b e e n programmed and added.
Rather than
u s i n g g a s dynamic t a b l e s , t h e shock-wave a n g l e 8 i s computed from a
c u b i c e q u a t i o n i n s i n 2 8 , r e q u i r i n g t h e Mach number and t h e e f f e c t i v e
a n g l e - o f - a t t a c k , which a l s o h a s t o a c c o u n t f o r t h e wing sweep a n g l e .
The P ~ ~ - s u b r o u t i nwe i l l a l s o be needed i n f u t u r e i n v e s t i g a t i o n s o f t h e
e f f e c t of t h e p r e c o m p r e s s i o n f i e l d on p r o p u l s i o n performance.
�The a d d i t i o n o f t h i s s u b r o u t i n e t o t h e HTO-airbreather
d e c k h a s caused t h e program t o exceed t h e SDS-930 s t o r a g e c a p a c i t y .
C o n s e q u e n t l y , t h e c o n t r a c t o r h a s b e e n d i r e c t e d t o change t h e program
o v e r t o r u n on t h e CDC-3200 computer which h a s c o n s i d e r a b l y l a r g e r
s t o r a g e t h a n t h e SDS-930.
Logic w i l l b e added t o h a n d l e t h e t r a n s i t i o n
from t h e c o n s t a n t - q - p h a s e t o t h e c o n s t a n t - d u c t - p r e s s u r e p h a s e .
The
l a t t e r phase w i l l t h e n b e programmed.
Because o f a change i n p e r s o n n e l p e r f o r m i n g t h e cont r a c t e d e f f o r t , a h o l d h a s developed i n t h e e f f o r t s under c o n s i d e r a t i o n .
2.
Advanced Systems and M i s s i o n S t u d i e s
a.
Solar-Electric
were h e l d w i t h
e f f o r t s and t o
and t r a j e c t o r y
S o l a r - E l e c t r i c Mars P h o t o Miss i o n
Our s u p p o r t o f R e s e a r c h P r o j e c t s L a b o r a t o r y i n t h e
Mars P h o t o M i s s i o n s t u d y h a s made p r o g r e s s . M e e t i n g s
RPL p e r s o n n e l on 10114 and 10126 t o c o o r d i n a t e o u r
p l a n f u r t h e r i n v e s t i g a t i o n s i n t o t h e f l i g h t mechanics
s i t u a t i o n of t h i s m i s s i o n .
The work performed d u r i n g t h e r e p o r t i n g p e r i o d i n c l u d e d
two-dimensional p l a n e t o c e n t r i c ( s p i r a l - t y p e ) c a l c u l a t i o n s and t h r e e d i m e n s i o n a l h e l i o c e n t r i c low- t h r u s t C. 0 . V. o p t i m i z a t i o n w i t h o u t E a r t h
and Mars, by AERO-GG (Causeyl Ingram), a t t i t u d e c o n t r o l a n a l y s e s and
o r b i t a l maneuvering and s t a t i o n - k e e p i n g s t u d i e s , a s w e l l a s s o p h i s t i cated three-dimensional c a l c u l a t i o n s o f Earth-to-Mars low-thrust t r a j e c t o r i e s i n c l u d i n g e f f e c t s o f p l a n e t s , s u n , p l a n e c h a n g e s , e t c . , by
AERO-GS (Schwaniger/Galloway/~uncan). N o r t h r o p , under t h e m i s s i o n
s u p p o r t c o n t r a c t , h a s p r o v i d e d some p r e l i m i n a r y Mars o r b i t - k e e p i n g
r e q u i r e m e n t s and l o w - t h r u s t two-dimensional t r a j e c t o r y r u n c h e c k i n g
o u t o l d e r EOS d a t a .
On November 29, t h e f i f t h c o o r d i n a t i o n m e e t i n g between
AERO and RPL t o o k p l a c e . Most of t h e f i n a l r e s u l t s w e r e p r e s e n t e d and
d i s c u s s e d i n c o n s i d e r a b l e d e t a i l . Of p a r t i c u l a r i m p o r t a n c e t o t h e
f u t u r e f a t e of t h e s o l a r - e l e c t r i c photo-mission concept is a p p a r e n t l y
t h e p o l i t i c a l s i t u a t i o n posed by Voyager.
Consequently, t h i s p o i n t
was d i s c u s s e d e x t e n s i v e l y . A l s o , Aero L a b o r a t o r y recommended emphati c a l l y t h a t RPL'S c o n c e p t n o t be based e x c l u s i v e l y on a n u p r a t e d
S a t u r n I B v e h i c l e (260" s o l i d ) , b u t t h a t f u r t h e r i n v e s t i g a t i o n b e cond u c t e d assuming t h e s t a n d a r d v e r s i o n o f t h e S a t u r n IB. T h i s and o t h e r
s u g g e s t i o n s by Aero a r e b e i n g c o n s i d e r e d by RPL.
Our s u p p o r t of RPL i n t h e s t u d y under d i s c u s s i o n h a s
b e e n t e m p o r a r i l y t e r m i n a t e d , w h i l e a p r e s e n t a t i o n t o D r . v o n Braun
( p l a n n e d f o r mid-December) is b e i n g p r e p a r e d .
�b.
J u p i t e r Fly-By M i s s i o n s
On October 11, f o l l o w i n g a n i n v i t a t i o n by J . von
P u t t k a m e r , members o f t h e F o r t Worth D i v i s i o n of General Dynamics gave
a p r e s e n t a t i o n on t h e i r p a s t and c u r r e n t work i n t h e a r e a o f advanced
p l a n e t a r y p r o b e s t o i n t e r e s t e d Aero-Astrodynamics p e r s o n n e l .
GD/FW
h a s r e c e n t l y f i n i s h e d a s t u d y of " J u p i t e r Fly-by M i s s i o n s " f o r JPL and
is p r e p a r i n g f o r t h e b i d on t h e upcoming Advanced P l a n e t a r y Probe (APP)
s t u d i e s , which w i l l be c e n t e r e d on J u p i t e r f l i g h t s , m u l t i - p l a n e t f l y b y
u l t i m a t e l y - t h e g a l a c t i c m i s s i o n . The d i r e c t i o n o f
m i s s i o n s and
t h e s e e f f o r t s w i l l be t a k e n o v e r by Goddard Space F l i g h t C e n t e r .
-
The s t u d y team, which i n c l u d e d D r . L a r r y Hove,
D r . Vernon Lee, D r . F r o s t , and M r . J o n e s , u n d e r t h e d i r e c t i o n of
D r . Ted Webb, h a s i n v e s t i g a t e d f o u r d i f f e r e n t s p a c e c r a f t d e s i g n c o n c e p t s ,
t h r e e of w h i c h u t i l i z e t h r e e - a x e s s t a b i l i z a t i o n w h i l e t h e f o u r t h f e a t u r e s
s p i n s t a b i l i z a t i o n . Launch v e h i c l e s c o n s i d e r e d r a n g e from ATLAS/Centaur/
HEKS t o S a t u r n V and S a t u r n V/Centaur.
Using what a p p e a r s t o b e a cons e r v a t i v e a p p r o a c h , GD/FW conducted a r e l i a b i l i t y a n a l y s i s and d e r i v e d
" p r o b a b i l i t y of m i s s i o n s u c c e s s " e s t i m a t e s which a r e g e n e r a l l y below
0.01 f o r t o t a l m i s s i o n a c h i e v e m e n t (Mariner I V Y u s i n g t h e same e v a l u a t i o n p r o c e d u r e s , had 0.11 e x p e c t e d m i s s i o n s u c c e s s p r o b a b i l i t y ) .
c.
SAE Launch V e h i c l e and M i s s i l e s Committee
On O c t o b e r 6 , a t t h e a n n u a l m e e t i n g of t h e SAE Launch
V e h i c l e and M i s s i l e s Committee i n Los A n g e l e s , C a l i f o r n i a , i t was
d e c i d e d t h a t t h e SAE 2nd Space Technology C o n f e r e n c e , t o be h e l d on
May 9-12, 1967, i n P a l o A l t o , C a l i f . , c l o s e t o t h e Ames R e s e a r c h C e n t e r ,
would h a v e t h e t i t l e "Low C o s t O r b i t a l T r a n s p o r t a t i o n . "
It would b e
co-sponsored by B r i t a i n ' s " B r i t i s h I n t e r p l a n e t a r y S o c i e t y , " F r a n c e ' s
" S o c i e t e F r a n c a i s e d ' As t r o n a u t i q u e ," Germany's "Deutsche Gesel l s c h a f t
f u e r R a k e t e n t e c h n i k und Raumfahrt," and I t a l y ' s " A s s o c i a z i o n e I t a l i a n a
Razzi," w i t h Eurospace, Junkers, Dassaul t A v i a t i o n , B r i t i s h A i r c r a f t
Corp., Rolls-Royce, B r i s t o l - S i d d e l e y , ERNO, and S o c i e t a T r a n s p o r t i
M i l l i s t i c i and o t h e r s b e i n g r e p r e s e n t e d .
R e p o r t s w e r e g i v e n by t h e
s e s s i o n chairmen on t h e p a p e r s s u b m i t t e d f o r c o n s i d e r a t i o n . While
t h e d e a d l i n e f o r a b s t r a c t s u b m i t t a l h a s a l r e a d y p a s t , M r . von P u t t k a m e r ,
who w i l l b e c h a i r i n g t h e s e s s i o n on "Far Term Advanced Launch V e h i c l e s ,I1
proposed t h a t a p a p e r on " C o n t r o l Systems of Advanced Launch V e h i c l e s f '
b y B l a i r and Redus o f AERO-G b e i n c l u d e d i n t h e s e s s i o n on "Pacing
Technology I m p l i c a t i o n s . "
M r . von Puttkamer a l s o recommended i n c l u s i o n
o f a p a p e r by H. Wuenscher of R-ME-DIR i n t h e s e s s i o n on " P a r t i a l l y
R e c o v e r a b l e Systems," a c c e p t a n c e o f which is c e r t a i n .
A s a p o s s i b l e l o c a t i o n f o r t h e 3rd Space Technology
Converence i n 1968, Langley R e s e a r c h C e n t e r was t e n t a t i v e l y s e l e c t e d .
�d.
Hypersonic A i r c r a f t Technology
A d e t a i l e d r e p o r t e n t i t l e d "On t h e C u r r e n t S t a t u s of
H y p e r s o n i c A i r c r a f t Technology'' was d i s t r i b u t e d on a l i m i t e d b a s i s .
e.
Advanced Systems T e c h n i c a l Reviews
Technical reviews a t t e n d e d during t h e r e p o r t i n g period
i n c l u d e d " H y p e r s o n i c A i r c r a f t B r i e f i n g , " by t h e McDonnell Company,
" P r o p u l s i o n A c t i v i t i e s a t A e r o j e t , " by t h e A e r o j e t Corp. , "Over t h e
H o r i z o n , B o o s t and R e e n t r y , ' I by N o r t h American, "Apollo Lunar Landing
Symposium," by MSC/HOUS
t o n , and "Nuclear Rocket Programs , I 1 by Rocketdyne.
A l s o , d u r i n g t h i s p e r i o d , two p r e s e n t a t i o n s were g i v e n
t o Aero L a b o r a t o r y on t h e " S o l a r - E l e c t r i c Mars P h o t o Mission" and on
A e r o j e t ' s in-house a c t i v i t i e s .
R e p o r t s e v a l u a t e d i n c l u d e d t h e r e p o r t of t h e Ad Hoc
Subpanel on R e u s a b l e Launch V e h i c l e Technology, "Performance P o t e n t i a l
of LH2-Fueled A i r b r e a t h i n g C r u i s e A i r c r a f t " and "Design Cons i d e r a t i o n s
o f R e u s a b l e Launch V e h i c l e s . "
11.
PROJECTS OFFICE
A.
The S a t u r n V Sys tems E n g i n e e r i n g I n c e n t i v e C o n t r a c t
The n e g o t i a t i o n s w i t h t h e Boeing Company (TBC) on t h e Sys tems
E n g i n e e r i n g Documentation (Task 8.0) p o r t i o n o f t h e i n c e n t i v e c o n t r a c t
i n which t h e Aero-Astrodynamics L a b o r a t o r y was l e a d l a b o r a t o r y w e r e comp l e t e d d u r i n g t h e week o f November 1 4 , 1966. The n e g o t i a t e d p l a n i n c l u d e s
motivating incentives i n the following areas:
(1)
F l i g h t v e r i f i c a t i o n - r e q u i r e s accuracy i n systems
i n t e g r a t i o n and c o m p u t a t i o n .
(2)
Schedule
r e q u i r e s prompt d e l i v e r y t o e x i s t i n g o r
revised schedules.
(3)
-
Performance - r e q u i r e s q u a l i t y p r o d u c t i o n o f a d e q u a t e
s o f t w a r e f o r S a t u r n V program.
The s u c c e s s f u l n e g o t i a t i o n s of t h e i n c e n t i v e p l a n c u l m i n a t e s a n
The m a j o r d i f f i c u l t i e s
extensive e f f o r t i n d r a f t i n g an acceptable plan.
e n c o u n t e r e d were ( 1 ) program f l e x i b i l i t y , ( 2 ) a d d i t i o n a l manpower r e q u i r e d
t o manage a n i n c e n t i v e c o n t r a c t o f t h i s t y p e , and ( 3 ) p o s s i b l e d e t e r i o r a t i o n of e n g i n e e r i n g working r e l a t i o n s between MSFC and TBC. The p l a n
�h a s been c o n s t r u c t e d t o minimize t h e a d v e r s e e f f e c t o f t h e above items
i n o r d e r f o r t h e S a t u r n V Systems E n g i n e e r i n g e f f o r t t o c o n t i n u e smoothly
and e f f e c t i v e l y .
The g r e a t e s t a d d i t i o n a l burden on t h e l a b o r a t o r i e s
r e s u l t i n g from t h i s i n c e n t i v e c o n t r a c t w i l l be i n t h e form of added
paper work i n c o n n e c t i o n w i t h r e c o r d i n g and m o n i t o r i n g of i n d i v i d u a l
TBC documents, added m o n i t o r i n g of s c h e d u l e s of b o t h Government
F u r n i s h e d Data (GFD) and TBC document d e l i v e r i e s
.
B.
A p o l l o / S a t u r n V Recycle C a p a b i l i t y
A p r e s e n t a t i o n was g i v e n a t t h e Management Council Meeting of
November 22, 1966, on t h e c u r r e n t s t a t u s of t h e A p o l l o / S a t u r n V Recycle
C a p a b i l i t y f o r t h e f i r s t l u n a r l a n d i n g m i s s i o n . MSFC, KSC, MSC and
Bellcomm p e r s o n n e l p a r t i c i p a t e d i n t h i s e f f o r t . A d r y - r u n of t h i s p r e s e n t a t i o n g i v e n t o MSFC p e r s o n n e l on November 1 6 , 1966, i s b r i e f l y
summarized as f o l l o w s :
-
2 112-hour
(1) It a p p e a r s t h a t "holding" w i t h i n t h e
l a u n c h window and l a u n c h i n g b e f o r e c l o s i n g of t h e window w i l l pose no
b i g problem.
I f t h e countdown i s q u i t e c l o s e t o l a u n c h , a r e c y c l e t o
L-15 m i n u t e s may be r e q u i r e d .
(2) Recycle from one l a u n c h o p p o r t u n i t y t o t h e s u b s e q u e n t
one w i l l r e q u i r e a b o u t 48-53 h o u r s , a n d e f f o r t w i l l b e expended t o g e t
t h i s time t o 48 h o u r s o r s l i g h t l y l e s s .
( 3 ) The proposed m i s s i o n p l a n n i n g f o r t h e f i r s t l u n a r
l a n d i n g m i s s i o n would s u p p o r t t h r e e monthly l a u n c h o p p o r t u n i t i e s spaced
This p a t t e r n
a p p r o x i m a t e l y 48 h o u r s a p a r t w i t h i n a b o u t a n 8-day p e r i o d .
of l a u n c h o p p o r t u n i t i e s w i l l r e p e a t e v e r y month. The a c t i v i t i e s f o r
g e n e r a t i n g t h e t a r g e t i n g and o t h e r m i s s i o n r e l a t e d d a t a t o s u p p o r t a
t h r e e - m o n t h s p a n o f l a u n c h o p p o r t u n i t i e s ( t h r e e o p p o r t u n i t i e s p e r 8-day
p e r i o d f o r e a c h of t h e t h r e e months) w i l l b e g i n a b o u t 7 t o 7 1 1 2 months
b e f o r e l a u n c h , and c u l m i n a t e i n f i n a l program v e r i f i c a t i o n and t r a n s m i t t a l t o KSC a t a p p r o x i m a t e l y one month b e f o r e s c h e d u l e d l a u n c h . KSC
w i l l be p r o v i d e d " t y p i c a l " m i s s i o n d a t a f o r u s e u n t i l L-1 month. During
t h e p r e s e n t a t i o n t h e c e n t e r s were asked t o d e t e r m i n e i f t h e i d e n t i f i e d
7 112-month l e a d time f o r o p e r a t i o n a l d a t a could n o t b e reduced t o a
2-month l e a d time.
This is being i n v e s t i g a t e d .
C.
F l i g h t Mechanics P a n e l and Sub-panels A c t i v i t i e s
1.
and 20, 1966.
follows:
F l i g h t Mechanics P a n e l (FMP)
The E i g h t e e n t h FMP Meeting was h e l d a t MSC on October 19
Some of t h e items from t h e m e e t i n g a r e summarized a s
�( a ) A t a s k team of t h e FMP i s b e i n g e s t a b l i s h e d t o
f o r m u l a t e and implement a p l a n of a c t i o n f o r d e t e r m i n i n g t h e f e a s i b i l i t y
of manual b o o s t e r c o n t r o l and a l s o t o d e t e r m i n e i f LV/SC g u i d a n c e s w i t c h o v e r i n e a r t h o r b i t i s indeed w i t h i n t h e c a p a b i l i t y o f t h e v e h i c l e (from
a s p e c t s of g u i d a n c e , dynamics, and c o n t r o l , e t c . , d u r i n g S-IVB second
b u r n of AS-503 and s u b s ) .
(b) A s k e l e t o n p l a n f o r t r a n s f e r r i n g i n t e r f a c e w e i g h t
( i . e . , payload changes) n e a r l a u n c h time due t o L / V payload c a p a b i l i t y
changes a n d / o r v a r y i n g m i s s i o n r e q u i r e m e n t s due t o time o f p r o j e c t e d
launch d a t a has been prepared.
The d e t a i l s of t h e s e p r o c e d u r e s a r e
s u b j e c t t o r e f i n e m e n t and w i l l be f u l l y documented.
( c ) The problem of " q u i c k r e t a r g e t i n g " o f t h e L/V
and S/C f o r LOR m i s s i o n s caused b y changes (such a s l a n d i n g s i t e s ) a s
l a t e as one month b e f o r e l a u n c h h a s been i n v e s t i g a t e d . Computer programs, LV/SC i n t e r f a c e d a t a exchange r e q u i r e m e n t s , and o t h e r p r o c e d u r e s
a r e b e i n g planned t o accommodate t h i s c a p a b i l i t y .
The "nominal" t i m e
r e q u i r e m e n t s a r e c o n s i d e r a b l y l o n g e r , of c o u r s e , and t h e s e p r o c e d u r e s
a r e planned o n l y f o r t h e c o n t i n g e n c y c a s e of l a t e changes. Both t h e
If
nominal" and " q u i c k turn-around" s c h e d u l e s a r e b e i n g documented.
( d ) The FMP h a s o f f i c i a l l y s t a r t e d m i s s i o n p l a n n i n g
work f o r AS-209 (AAP) m i s s i o n .
The r e s u l t s of t h i s m e e t i n g a r e documented i n MSC memorandum PM2-M2-9-66, d a t e d October 20, 1966.
2.
1966.
F l i g h t L i m i t s Sub-panel
(FLSP)
The S i x t h FLSP Meeting was h e l d a t MSFC on November 9 ,
The m i n u t e s a r e documented i n MSFC memorandum R-AERO-P-459-66.
3.
Guidance and Performance Sub-panel (G&PSP)
The Twenty-Second G&P Sub-panel m e e t i n g was h e l d a t
MSFC on November 8 , 1966. Among t h e i t e m s d i s c u s s e d was t h e s t a t u s o f
t h e m i s s i o n p l a n n i n g a c t i v i t i e s f o r each of t h e ~ p o l l o / S a t u r nm i s s i o n s .
It was p o i n t e d o u t t h a t MSC i s c o n s i d e r i n g r e d u c i n g t h e d i f f e r e n c e i n
o r b i t a l a l t i t u d e between t h e AS-207 and AS-208 v e h i c l e s from t h e p r e s e n t
20 n.mi. t o a p p r o x i m a t e l y 1 0 t o 15 n.mi.
The m i s s i o n a n a l y s i s , b e i n g
conducted by MSC, w i l l b e completed by a b o u t December 1 5 , 1966. I f t h e
change i s made, t h e a l t i t u d e of t h e CSM w i l l p r o b a b l y b e changed r a t h e r
t h a n r e q u i r i n g a change o f t h e LM (AS-208) a l t i t u d e . For AS-209, t h e
m i s s i o n r e q u i r e m e n t s , p r e l i m i n a r y m i s s i o n p r o f i l e , and p r e l i m i n a r y
r e f e r e n c e t r a j e c t o r y have b e e n d e l a y e d a p p r o x i m a t e l y one month b e c a u s e
of t h e r e c e i p t of d i r e c t i o n t h a t AS-209 w i l l b e a n unmanned workshop.
MSC p r e s e n t e d d a t a on t h e planned a c t i o n of t h e SC i n t h e e v e n t of
e a r l y s t a g i n g of t h e S-IVB from t h e S-11 S t a g e . MSC s t a t e d t h a t , f o r
manned m i s s i o n , t h e i r primary c o n c e r n i s a t t a i n i n g a " s a f e " o r b i t from
�which a b o r t t o a d e s i r e d recovery a r e a can be i n i t i a t e d .
The "safe"
o r b i t was d e f i n e d a s a n o r b i t w i t h a p e r i g e e of n o t l e s s than 75 n.mi.
For AS-501, i f s t a g i n g is i n i t i a t e d a t a time which w i l l n o t a l l o w t h e
S-IVB t o a t t a i n i t s 100 n.mi. e a r t h o r b i t , t h e SM w i l l be s t a g e d from
t h e S-IVB a t t h e time of S-IVB c u t o f f , and flown t o a r e e n t r y e l l i p s e
which w i l l p r o v i d e some s i m u l a t i o n of t h e r e e n t r y t e s t .
CSM w i l l be
t a r g e t e d f o r a n e l l i p s e w i t h an apogee of a b o u t 6,000 n.mi.
This
e l l i p s e can be a t t a i n e d f o r a l l S - I 1 f a i l u r e times a f t e r 164-seconds
The t e s t would provide h e a t l o a d s a t r e e n t r y f o r about
of S - I 1 burn.
56 p e r c e n t of t h e nominal t r a n s l u n a r r e e n t r y c o n d i t i o n s . For S - I 1
f a i l u r e s b e f o r e 164 seconds of S - I 1 burn, t h e CSM t a r g e t i n g w i l l remain
t h e same, and f u r t h e r d e g r a d a t i o n of t h e h e a t s h i e l d t e s t w i l l be
a c c e p t e d . The minutes of t h e meeting a r e documented i n MSFC memorandum
R-AERO-P-472-66, dated November 1 2 , 1966.
Guidance Switchover and Manual Booster Control Task Team
On November 15, 1966, MSFC R e p r e s e n t a t i v e s a t t e n d e d t h e
f i r s t meeting of t h e Guidance Switchover and Manual Booster Control
Task Team Meeting a t MSC. The Apollo Systems S p e c i f i c a t i o n Requirements
c a l l s f o r S a t u r n V guidance switchover c a p a b i l i t y i n o r b i t . R-AERO w i l l
be involved i n comparing t h e S I C Trans-Lunar I n j e c t i o n (TLI) guidance
equations t o the G
IM e q u a t i o n s f o r performance and accuracy c a p a b i l i t i e s
should switchover be r e q u i r e d .
I n t h e a r e a of manual b o o s t e r c o n t r o l ,
MSC p r e s e n t e d a proposed scheme which b a s i c a l l y monitors a l t i t u d e ,
a l t i t u d e r a t e , and v e l o c i t y f o r use i n manually c o n t r o l l i n g the b o o s t e r
d u r i n g upper s t a g e s of f l i g h t should t h i s be r e q u i r e d .
Through a hand
c o n t r o l l e r , t h e launch v e h i c l e body r a t e w i l l be commanded. The SIC
i s programmed w i t h t h e nominal p r o f i l e (polynomial) which i s used a s a
Since t h e IGM can a c t u a l l y be f u n c t i o n i n g
guidance/control baseline.
p r o p e r l y and t h e p r o f i l e n o t comparing c l o s e t o a p r e - p r o g r a m e d a r t i f i c i a l p r o f i l e , MSFC expressed concern t h a t a s w i t c h i n g d i s c o n t i n u i t y would
e x i s t and l a r g e t r a n s i t s would r e s u l t . The scheme was modified t o comp a r e t h e p r e - p r o g r a m e d p r o f i l e t o t h e a c t u a l p r o f i l e and t o b i a s t h e
pre-programmed t o match t h e a c t u a l p r o f i l e b e f o r e s w i t c h i n g t o manual
control.
This w i l l a l l e v i a t e t h e p o t e n t i a l problem.
Dynamic s i m u l a t i o n s
w i l l be conducted by R-ASTR and R-AERO t o v e r i f y performance, s t a b i l i t y ,
e t c . , witlh t h e man-in-the-loop.
MSC p l a n s t o go ahead w i t h implementing
t h e scheme a s modified because of s c h e d u l e c o n s i d e r a t i o n s ; t h e v e r i f i c a t i o n of t h e scheme, a s w e l l a s t h e d e t e r m i n a t i o n of t h e o p e r a t i o n a l
p r o c e d u r e s , w i l l be conducted w h i l e t h e scheme i s being implemented.
E f f o r t s w i l l be c o n c e n t r a t e d on AS-503 and s u b s . No SC/LV hardware
i n t e r f a c e problems o r requirements f o r new c a b l e s , w i r e s , e t c . , were
identified.
�111.
ADVANCED STUDIES OFFICE
A.
O f f i c e o f t h e Chief
The FY-65 S a t u r n Improvement S t u d i e s h a v e b e e n completed and
f i n a l c o n t r a c t o r p r e s e n t a t i o n s were made d u r i n g t h e f i r s t week of
O c t o b e r . A summary o f t h e i n f o r m a t i o n was p r e s e n t e d by MSFC t o
H e a d q u a r t e r s on November 21, 1966. An a b b r e v i a t e d v e r s i o n of t h e
H e a d q u a r t e r s r e v i e w was p r e s e n t e d t o t h e L a b o r a t o r y s t a f f o n November 28,
1966.
The FY-65 funded s t u d i e s were aimed a t t h r e e a r e a s of u p r a t i n g :
t h e S a t u r n IB, S a t u r n V, and a c l a s s c a l 1 e d " i n t e n n e d i a t e s a t u r n ! ' The
l a s t c l a s s , i n t e r m e d i a t e S a t u r n , i n v e s t i g a t e d t h e f e a s i b i l i t y of using
S a t u r n V s t a g e s i n v a r i o u s ground l a u n c h modes.
The s t u d i e s i n v o l v e d s i x c o n t r a c t o r s and i n t e r f a c e d c l o s e l y w i t h
p a r a l l e l KSC l a u n c h f a c i l i t y s t u d i e s .
The c o n t r a c t o r s and d o l l a r s
i n v o l v e d were as f o l l o w s :
UTC (United Technology Corp.)
NAA ( N o r t h American A v i a t i o n )
TBC (The Boeing Company)
DAC (Douglas A i r c r a f t Company)
CCSD ( C h r y s l e r C o r p o r a t i o n Space D i v . )
(sub)
$1,644K
A-JG (Aero-Jet G e n e r a l )
Launch F a c i l i t i e s Study:
TMC (The M a r t i n Company)
C o n n e l l (A&E)
TOTAL
$1,894~
The i n - d e p t h a n a l y s e s a c h i e v e d f o r t h e v a r i o u s v e h i c l e c o n f i g u r a t i o n s
w e r e d i r e c t l y p r o p o r t i o n a l t o t h e f u n d s expended; t h e c o n t r a c t / d o l l a r
v a l u e i s g i v e n t o r e f l e c t man-hours expended.
The s t u d i e s were " t o t a l " s y s tems s t u d i e s d e f i n i n g t h e s t a g e
m o d i f i c a t i o n and d e s i g n , f a c i l i t y i m p a c t s ( m a n u f a c t u r i n g , t e s t and
launch), transportation, resource requirements, e t c .
�S i n c e d e t a i l e d d o c u m e n t a t i o n was a r e q u i r e m e n t , much u s e f u l
i n f o r m a t i o n i s a v a i l a b l e f o r t h e advanced m i s s i o n p l a n n e r .
B.
F l i g h t Mechanics and Performance A n a l y s i s Group
1. T h i s g r o u p p a r t i c i p a t e d i n t h e e v a l u a t i o n of p r o p o s a l s
f o r "Use o f L a r g e S o l i d Motors i n B o o s t e r A p p l i c a t i o n s . "
Of t h e f o u r
p r o p o s a l s s u b m i t t e d , D o u g l a s ' a n d ~ o e i n g ' swere a d j u d g e d t o b e p r a c t i c a l l y
e q u i v a l e n t i n terms o f t e c h n i c a l a p p r o a c h , and t h e r e f o r e , I. 0. i s i n
a bargaining position t o negotiate the contract.
2. A p r e l i m i n a r y t i m e l i n e a n a l y s i s f o r t h e SA4 Synchronous
M i s s i o n h a s b e e n g e n e r a t e d by R-AERO-DAM (Mrs. B a u e r ) .
R-AERO-FO
(Mr. H i l l ) i s f u r n i s h i n g t h e a n a l y s i s of t h e t r a c k i n g and communications
r e q u i r e m e n t s r e s u l t i n g from h i s i n v e s t i g a t i o n s .
These r e s u l t s have b e e n
s u b m i t t e d t o t h e p r i m a r y i n v e s t i g a t o r s , R-P&VE and R-ASTR i n p r e l i m i n a r y
form and w i l l b e u p d a t e d .
3 . A memorandum (R-AERO-X-118-66) summarizing t h e performance
c a p a b i l i t i e s o f s e l e c t e d c o n f i g u r a t i o n s o f t h e S a t u r n V and S a t u r n I B
f o r space s t a r i o n s u p p o r t has been d i s t r i b u t e d .
4. The m i s s i o n s u p p o r t c o n t r a c t o r (Raytheon) h a s s u c c e s s f u l l y
implemented t h e IGM i n t h e BOP deck. The p r o c e d u r e i s t o u s e t h e I G M
i n o b t a i n i n g t h e f i r s t nominal t r a j e c t o r y ( s h a p i n g o n l y ) on which t h e
s t e e p e s t ascent technique is applied t o optimize the vehicle s i z i n g .
Using t h e IGM i n t h i s manner ( r a t h e r t h a n g u e s s i n g i n i t i a l c o n d i t i o n s )
h a s r e s u l t e d i n a v e r y a p p r e c i a b l e s a v i n g s i n computer t i m e (up t o 1 1 2 ) .
5 . The f i r s t i t e r a t i o n on e v a l u a t i n g t h e s t u d y p r o p o s a l s f o r
S-IVB S p e n t S t a g e U t i l i z a t i o n h a s b e e n made.
P a r t i c i p a t i n g w i t h R-AERO-X
w e r e R-AERO-F (Mr. Fulmer) and R-AERO-D (Mr. Verderaime).
The f i n a l
e v a l u a t i o n i s t o b e completed a b o u t December 1, 1966,
C.
As t r o d y n a m i c s and Miss i o n
1.
Manned P l a n e t a r y Flyby M i s s i o n s Based on S a t u r n / A p o l l o
Sys tem
The f i r s t q u a r t e r l y r e v i e w o f t h i s s t u d y c o n t r a c t w i t h
N o r t h American A v i a t i o n was h e l d a t MSFC o n November 2, 1966. T h i s
f i r s t p h a s e o f t h e s t u d y was p r i m a r i l y concerned w i t h g e n e r a t i n g
p a r a m e t r i c d a t a t o c o v e r t h e s p e c t r u m o f s y s t e m s , modes, and programs
b e i n g c o n s i d e r e d . P r i m a r y e f f o r t was expended on d e f i n i n g rendezvous
p r o f i l e s f o r t h e two o r b i t l a u n c h v e h i c l e s (S-IVB and S - I I B ) b e i n g
s t u d i e d . The s c i e n t i f i c and e x p e r i m e n t s programs a r e a l s o w e l l under
way.
The s i x s c i e n t i f i c c o n s u l t a n t s , NAA, and t h e i r s u b c o n t r a c t o r ,
AVCO, h a v e had m e e t i n g s t o d e f i n e a n e x p e r i m e n t s program and t o b e g i n
�p r e l i m i n a r y p r o b e d e s i g n c o n c e p t s . A l s o s e v e r a l c a n d i d a t e s u b s y s tems
and s y s t e m s have b e e n s e l e c t e d f o r p o s s i b l e i n c l u s i o n i n t h e makeup of
complete v e h i c l e / s y s t e m s c o n f i g u r a t i o n s .
Presently, there is considerable discussion a s t o the
r e l a t i o n s h i p o f t h i s NAA c o n t r a c t e d s t u d y and t h e NASA i n - h o u s e
p l a n e t a r y JAG e f f o r t . A m e e t i n g was h e l d a t NASA h e a d q u a r t e r s t o
I t was
attempt t o s e t f o r t h guidelines t o define the relationship.
t e n t a t i v e l y d e c i d e d by D r . Dixon, NASA h e a d q u a r t e r s , t h a t a copy of
t h e JAG r e p o r t would b e p r o v i d e d t h e c o n t r a c t o r , t h r o u g h B. G. N o b l i t t ,
COR f o r t h e f l y b y s t u d y c o n t r a c t . B e f o r e s e n d i n g t h e r e p o r t t o t h e
c o n t r a c t o r , D r . Dixon w i l l d i s c u s s w i t h t o p management o f N o r t h American
A v i a t i o n c o n c e r n i n g t h e i n t e n t o f NASA t o p r o v i d e them a copy of t h e
report.
2.
G e n e r a l Theory of R e l a t i v i t y Experiment
E f f o r t i s c o n t i n u i n g i n s u p p o r t of RPL t o i d e n t i f y
a t t r a c t i v e h e l i o c e n t r i c o r b i t p r o f i l e s t h a t a r e compatible w i t h the
e x p e r i m e n t m i s s i o n r e q u i r e m e n t s and t h e S a t u r n V payload c a p a b i l i t y
t o meet t h e r e q u i r e d e n e r g y l e v e l s . A l s o o f i m p o r t a n c e i s t h e a t t r a c t i v e n e s s o f t h e o r b i t s f o r t r a c k i n g and o r b i t d e t e r m i n a t i o n p u r p o s e s .
R e p r e s e n t a t i v e he1i o c e n t r i c o r b i t s having e c c e n t r i c i t i e s
between 0 . 4 and 0.5 and semi-major a x e s between 0.7 and 0 . 8 A . U . ' s
have been s e l e c t e d t o b e e v a l u a t e d i n more d e t a i l . Communication
d i s t a n c e and a n g l e s a r e b e i n g d e t e r m i n e d f o r t h e s e p r o f i l e s .
From
t h e v i e w p o i n t o f t h e e x p e r i m e n t s , i t may b e d e s i r a b l e t o have t r a j e c t o r i e s t h a t a r e somewhat i n c l i n e d t o t h e e c l i p t i c p l a n e ; t h e r e f o r e ,
p r o f i l e s i n c l i n e d t o t h e e c l i p t i c p l a n e by a p p r o x i m a t e l y 20 degrees,
a s well a s t r a j e c t o r i e s t h a t a r e i n the e c l i p t i c plane a r e being
analyzed.
3.
P h o t o g r a p h i c E x p l o r a t i o n o f Mars w i t h S o l a r E l e c t r i c
Propulsion
T h i s e f f o r t i s c o n t i n u i n g i n s u p p o r t of RPL. A twod i m e n s i o n a l , h e l i o c e n t r i c l o w - t h r u s t computer program h a s b e e n
d e v e l o p e d and checked o u t . The program h a s b e e n used t o v e r i f y and
e x t e n d d a t a o b t a i n e d by M r . Wood, RPL. O r b i t - k e e p i n g r e q u i r e m e n t s
f o r c i r c u l a r o r b i t s a t Mars w i t h a l t i t u d e s between 200 and 5 0 , 0 0 0 km
have been generated
.
Data g e n e r a t e d by R-AERO-XA i n s u p p o r t of t h i s p r o j e c t
a r e b e i n g p r e p a r e d f o r M r . Wood, RPL. M r . Wood t e n t a t i v e l y p l a n s t o
p r e s e n t t h e r e s u l t s o f t h i s s t u d y t o D r . von Braun i n mid-December.
�4.
Mars S u r f a c e Sample R e t u r n Probe
-
MSSR
Both t h e in-house s t u d y and t h e c o n t r a c t o r ' s s t u d y a r e
s c h e d u l e d f o r c o m p l e t i o n by t h e f i r s t week of December.
D.
Systems A n a l y s i s Group
A memorandum i s t o be p u b l i s h e d t o b r i e f t h e a d d r e s s e e s on t h e
aerodynamic d a t a t o be a v a i l a b l e s h o r t l y on t h e improved S a t u r n IB and
V v e h i c l e s , and t h e b a s e h e a t i n g t e s t s planned f o r a n improved S a t u r n V
configuration.
These t e s t d a t a w i l l e n a b l e t h e c o n t r a c t o r s t o p e r f o r m
more r e l i a b l e c o n t r o l s t u d i e s , s t r e s s a n a l y s e s , e t c . , i n a n y f u t u r e
S a t u r n improvement s t u d i e s
.
IV.
AEROSPACE ENVIRONMENT DIVISION
A.
Space Environment Branch
P r o p o s a l s have b e e n r e c e i v e d and a r e b e i n g e v a l u a t e d on t h e
d e f i n i t i o n of a n e x p e r i m e n t t o s t u d y i n t e r a c t i o n s of g a s m o l e c u l e s
w i t h a s o l i d s u r f a c e i n t h e ambient s p a c e environment. The e v a l u a t i o n
and c o n t r a c t n e g o t i a t i o n s w i l l be completed soon. Two t e c h n i q u e s , b o t h
o f which a r e p r o m i s i n g , have b e e n proposed, and b o t h w i l l p r o b a b l y be
studied.
P r o p o s a l s r e c e i v e d on t h e d e f i n i t i o n o f a n o r b i t a l d e n s i t y ,
d r a g c o e f f i c i e n t , and gas-molecule s o l i d - s u r f a c e i n t e r a c t i o n e x p e r i m e n t
have been e v a l u a t e d . Three s e p a r a t e c o n c e p t s have been p r o p o s e d , and
p o s s i b l y a l l t h r e e w i l l be s t u d i e d .
Work was i n i t i a t e d on programming a new model of t h e e a r t h ' s
upper a t m o s p h e r e f o r u s e as a s t a n d a r d a t MSFC.
T h i s i s ~ a c c h i a ' s 1964
model which a p p e a r s t o be t h e b e s t a v a i l a b l e a t t h e p r e s e n t t i m e . A
computer program f o r t h i s model i s b e i n g developed.
Work i s c o n t i n u i n g on producing a more r e l i a b l e method f o r
p r e d i c t i n g f u t u r e s u n s p o t c y c l e s . A F o u r i e r s e r i e s a n a l y s i s i s produci n g some e x c e l l e n t r e s u l t s ; however, a d d i t i o n a l v e r i f i c a t i o n i s r e q u i r e d
b e f o r e t h e method can be used.
Work is c o n t i n u i n g on r e f i n i n g o u r model of t h e J o v i a n atmosp h e r e . A problem has a r i s e n i n t h e t e m p e r a t u r e computation p o r t i o n of
t h e program, however, which h a s d e l a y e d p u b l i c a t i o n .
The l a u n c h e s s c h e d u l e d f o r October i n o u r upper atmosphere
measurement program have been postponed due t o a problem i n t h e
s e n s i t i v i t y of t h e i n s t r u m e n t a t i o n w i t h r e s p e c t t o t h e a t m o s p h e r i c
�c o n s t i t u e n t s . G o l d - p l a t e d i n s t r u m e n t s launched i n August were n o t a b l e
t o measure a t o m i c oxygen. A c o n c e r t e d e f f o r t t o remedy t h i s d e f i c i e n c y
was begun i n September; however, no s o l u t i o n h a s y e t b e e n found.
An a r t i c l e e n t i t l e d , " I o n o s p h e r i c R a r e f a c t i o n F o l l o w i n g Rocket
T r a n s i t , " w r i t t e n by M e s s r s . F e l k e r and R o b e r t s a p p e a r e d i n October 1
i s s u e o f t h e J o u r n a l o f Geophysical R e s e a r c h . S e v e r a l equipment i t e m s
have b e e n p u r c h a s e d i n p r e p a r a t i o n f o r t h e L a b o r a t o r y ' s i o n o s p h e r i c
s t u d y program.
S i x t r a n s m i t t e r s have been ordered along w i t h a t o t a l
of t w e l v e c r y s t a l o s c i l l a t o r s which h a v e a s t a b i l i t y o f one p a r t i n 10".
Two t e n t a t i v e s i t e s have b e e n i n s p e c t e d by t h e l a b o r a t o r y p r o j e c t
managers.
P r e l i m i n a r y approval has been obtained f o r t h e use of t h e s e
1o c a t i o n s .
Chances f o r o b t a i n i n g t h e C-4 ionosonde a p p e a r t o b e r e l a t i v e l y
good. A v a n is b e i n g r e n o v a t e d s o t h a t t h e ionosonde may b e conveni e n t l y moved t o a n y s i t e o f o u r c h o o s i n g . H o p e f u l l y , t h e program w i l l
become o p e r a t i o n a l by F e b r u a r y .
B.
T e r r e s t r i a l Environment Branch
1.
Technical Reports
O f f i c e memorandum R-AERO-Y-124-66, "Frequency o f Thunders t o r m O c c u r r e n c e s a t H u n t s v i l l e , Alabama ," d a t e d O c t o b e r 3 , 1966.
TM X-53422, " E s t i m a t i o n of P a r a m e t e r s i n Compound W e i b u l l
D i s t r i b u t i o n s , " by L. W. F a l l s , March 30, 1966,
2.
Analytical Investigations
A s t u d y i s b e i n g completed on t h e f r e q u e n c y d i s t r i b u t i o n
of t h e l a r g e s t monthly and l a r g e s t y e a r l y mean r e l a t i v e s u n s p o t number.
These d a t a w e r e s e l e c t e d t o i l l u s t r a t e t h e u s e o f e x t r e m e v a l u e s t a t i s t i c s , d e v e l o p e d by D r . Gumbel, f o r o t h e r g e o p h y s i c a l d a t a . The r e s u l t s
o f t h e s t u d y w i l l be u s e d by t h e Space Environment Branch.
A d d i t i o n a l work h a s b e e n done on t h e r e l a t i v e d e v i a t i o n s
o f d e n s i t y w i t h r e s p e c t t o t h e P a t r i c k R e f e r e n c e Atmosphere, 1963.
A new memo w i l l b e p u b l i s h e d when t h e c o m p u t a t i o n s h a v e b e e n completed
g i v i n g v a l u e s of t h e r e l a t i v e d e v i a t i o n s of d e n s i t y f o r a l l months and
the annual period.
3.
Contracts
E l e v e n p r o p o s a l s r e c e i v e d on RFQ' s f o r "world-Wide Cloud
Coverage f o r M i s s i o n A n a l y s i s " were e v a l u a t e d , and n e g o t i a t i o n s a r e
b e i n g made w i t h a s e l e c t e d c o n t r a c t o r . Responses w e r e from a good
�c r o s s s e c t i o n of r e s e a r c h and a e r o s p a c e o r g a n i z a t i o n s . The a e r o s p a c e
o r g a n i z a t i o n s , i n p a r t i c u l a r , were s t r o n g i n t h e i r s u p p o r t of t h e proj e c t f o r t h e i r i n t e r n a l and o t h e r m i s s i o n a n a l y s i s a p p l i c a t i o n s . We
hope t o i n c o r p o r a t e i n p u t s from o t h e r NASA c e n t e r s (MSC, AMES, GSFC,
LRC) and H e a d q u a r t e r s (Bellcomm, OSSA, OART, OMSF) i n t h e s t u d y , and
t h e r e b y produce a more c o o r d i n a t e d and g e n e r a l l y u s e f u l f i n a l p r o d u c t .
R-AERO-D (Mr. eat on) i s working w i t h u s . , T h i s w i l l h e l p a s s u r e a
useable routine f o r mission analysis.
V.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
O p t i m i z a t i o n Theory Branch
1.
A n a l y t i c R e d u c t i o n o f Optimal T r a j e c t o r y Problem
The r e p r e s e n t a t i v e o p t i m a l t r a j e c t o r y problem h a s b e e n
s i m p l i f i e d , p e r m i t t i n g t h e number o f unknown i n i t i a l c o n d i t i o n s t o
b e r e d u c e d from f i v e t o t h r e e . The problem was w r i t t e n i n t r a n s f o r m e d
c o o r d i n a t e s and t h e c o o r d i n a t e s y s t e m p h y s i c a l l y i d e n t i f i e d . A comp u t e r program making u s e o f t h i s r e d u c t i o n method i s b e i n g p r e p a r e d .
A second t r a n s f o r m a t i o n which f u r t h e r r e d u c e s t h e c o m p l e x i t y of t h e
problem i s under s t u d y . D i f f i c u l t y h a s b e e n e n c o u n t e r e d i n d e t e r m i n i n g
a n analytical expression f o r a v e c t o r i a l integration constant.
If
t h i s c o n s t a n t can b e e x p r e s s e d , t h e problem of c h o o s i n g t h e c o r r e c t
i n i t i a l v a l u e s n e c e s s a r y t o compute a n o p t i m a l t r a j e c t o r y would b e
r e d u c e d t o t h e problem o f i s o l a t i o n of a s i n g l e i n i t i a l c o n d i t i o n .
2.
D e s i g n Concept Comparison S t u d y
A s t u d y t o compare s e v e r a l p r o m i s i n g c o n t r o l s y s t e m s and
t h e i r r e l a t e d s y n t h e s i s t e c h n i q u e s i s i n p r o g r e s s . The o b j e c t i v e i s
t o e v a l u a t e t h e e f f e c t i v e n e s s of t h e v a r i o u s c o n t r o l d e s i g n c o n c e p t s
i n m e e t i n g p r i m a r y and s e c o n d a r y c o n t r o l s y s t e m g o a l s .
The s t u d y h a s
b e e n o u t l i n e d and t h e computer program n e c e s s a r y f o r comparison r u n s
h a s b e e n programmed. Work h a s b e e n c u r t a i l e d somewhat b e c a u s e o f
o t h e r p r o j e c t s , b u t i t i s e x p e c t e d t h a t t h e s t u d y can p e r h a p s b e
c a r r i e d on as a s e c o n d a r y e f f o r t .
3.
Mars P h o t o O r b i t e r C o n t r o l
I n s u p p o r t o f R-RP-N, a p r e l i m i n a r y i n v e s t i g a t i o n was
made o f t h e f e a s i b i l i t y o f i o n t h r u s t d i f f e r e n t i a l c o n t r o l f o r a s o l a r
e l e c t r i c Mars o r b i t e r v e h i c l e p r e s e n t l y under s t u d y by t h a t l a b o r a t o r y .
It was concluded t h a t v a r y i n g t h e t h r u s t o f t h e i o n e n g i n e s i n d i v i d u a l l y
would s u p p l y s u f f i c i e n t c o n t r o l t o r q u e s f o r t h e e x p e c t e d m a j o r d i s t u r b a n c e
torques.
T h r u s t d i f f e r e n t i a l c o n t r o l f o r p i t c h and yaw a x i s c o n t r o l h a s
b e e n recommended d u r i n g p e r i o d s of t h r u s t i n g .
The s t u d y is documented
i n memo R-AERO-G-7-66.
�4.
AAS P r e s e n t a t i o n
An a b s t r a c t f o r a p a p e r e n t i t l e d "A Review o f Some E x i s t i n g L i t e r a t u r e Concerning D i s c o n t i n u o u s S t a t e V a r i a b l e s i n t h e C a l c u l u s
of V a r i a t i o n s " was a c c e p t e d by t h e American A s t r o n a u t i c a l S o c i e t y f o r
p r e s e n t a t i o n a t t h e December m e e t i n g i n H u n t s v i l l e .
5.
New E q u a t i o n s of Motion f o r S t a b i l i t y A n a l y s e s
I n t e r n a l Note R-AERO-IN-18-66,
e n t i t l e d " S t a b i l i t y of
Motion o f a Launch V e h i c l e C o n s i d e r i n g t h e R a t e of Change of t h e P a t h
Angle," h a s b e e n w r i t t e n and approved.
I n t h i s report, a modification
t o t h e p e r t u r b a t i o n e q u a t i o n s of m o t i o n used t o a n a l y z e s t a b i l i t y of
t h e l a u n c h v e h i c l e ' s m o t i o n a b o u t t h e nominal t r a j e c t o r y i s p r o p o s e d .
I t i s shown t h a t t h e m o d i f i e d (new) e q u a t i o n s p e r m i t more a c c u r a t e
p r e d i c t i o n of s t a b i l i t y and s h o r t - t e r m dynamic b e h a v i o r t h a n do t h e
c u r r e n t l y u s e d e q u a t i o n s . The r e p o r t recommends t h a t t h e new e q u a t i o n s
b e used f o r a l l f u t u r e s t a b i l i t y a n a l y s e s .
6.
Saturn
voyager
Shroud S t u d y
R i g i d body c o n t r o l r e s p o n s e s t u d i e s i n s u p p o r t o f t h e
r
D e s i g n S t u d y a r e a p p r o x i m a t e l y f o u r weeks
S a t u r n ~ / ~ o y a g eShroud
b e h i n d s c h e d u l e , due t o f a i l u r e t o r e c e i v e mass d a t a from PEEVE. Once
mass d a t a a r e r e c e i v e d , i t i s a n t i c i p a t e d t h a t t h e s t u d y w i l l b e comp l e t e d i n t h e four-week p e r i o d o r i g i n a l l y a l l o t t e d .
7.
Contractor
a.
N o r t h r o p S c h e d u l e Order /I26
(1)
Voyager S t u d i e s
Objectives:
To i n v e s t i g a t e l o a d r e l i e f s y s t e m s
f o r t h e S a t u r n V/Voyager, and t o p r o v i d e s e p a r a t i o n dynamics s t u d i e s
f o r t h e Voyager Shroud Design Study.
A s t u d y h a s b e e n made t o d e t e r m i n e t h e f e a s i b i l i t y
of implementing t h e proposed l o a d r e l i e f c o n t r o l law d e v e l o p e d f o r t h e
S a t u r n V/Voyager w i t h i n e r t i a l p l a t f o r m o u t p u t s i n s t e a d of a c c e l e r o m e t e r
o u t p u t s . Although incomplete, t h e s t u d y i n d i c a t e s t h a t i n e r t i a l p l a t form o u t p u t s c a n b e used t o d u p l i c a t e t h e p e r f o r m a n c e of t h e convent i o n a l l y implemented l o a d r e l i e f law. However, t h i s performance i s
a c h i e v e d a t t h e e x p e n s e of c o m p l i c a t e d g a i n s c h e d u l e s , l a r g e g a i n s ,
a n d i n d i v i d u a l l o o p i n s t a b i l i t y ( a l t h o u g h t h e o v e r a l l performance i s
stable).
�The s e p a r a t i o n dynamics s t u d y h a s o n l y r e c e n t l y
been i n i t i a t e d .
E f f o r t s t o d a t e have b e e n a s s o c i a t e d w i t h d e t e r m i n a t i o n
o f t h e p e r t i n e n t e q u a t i o n s of m o t i o n , p a r a m e t e r v a r i a t i o n s and p r o b a b i l i t y
d i s t r i b u t i o n s , and c h a r a c t e r i s t i c s o f s e p a r a t i o n d e v i c e s . Numerical d a t a
for the study a r e not yet available.
(2)
A n a l y t i c Design of V e h i c l e C o n t r o l Systems
Objective:
t e c h n i q u e s f o r 1i n e a r s y s tems.
To i n v e s t i g a t e a n a l y t i c a l d e s i g n
The a n a l y t i c d e s i g n t e c h n i q u e under s t u d y a p p e a r s
t o work w e l l f o r v a r i o u s s e n s o r l o c a t i o n s ; however, i t a p p e a r s t h a t t h e
f i l t e r s d e s i g n e d f o r one time p o i n t w i l l g e n e r a l l y n o t b e s u i t a b l e a t
o t h e r t i m e p o i n t s . L i n e a r o p t i m a l c o n t r o l may b e u s e f u l i n r e l i e v i n g
t h i s problem.
The i n h e r e n t i n s e n s i t i v i t y o f l i n e a r o p t i m a l s y s t e m s may
make i t p o s s i b l e t o choose f i l t e r c h a r a c t e r i s t i c s which w i l l p r o v i d e
good performance o v e r a wide r a n g e of o p e r a t i n g c o n d i t i o n s .
b.
N o r t h r o p S c h e d u l e Order #32 (New)
Objective:
t o r y o p t i m i z a t i o n problems.
To a p p l y f u n c t i o n a l a n a l y s i s t o t r a j e c -
The proposed f u n c t i o n a l a n a l y s i s methods employed show
promise o f s i m p l i f y i n g t h e s p l i t boundary v a l u e problem by a l l o w i n g
a u x i l i a r y v a r i a b l e s t o b e i n t r o d u c e d . These v a r i a b l e s , i n t e g r a t e d a
s i n g l e time from known i n i t i a l c o n d i t i o n s , y i e l d i n f o r m a t i o n on t h e
i n i t i a l v a l u e s t o b e used f o r t h e Lagrange m u l t i p l i e r s . The u t i l i t y
o f t h e t e c h n i q u e depends on convergence p r o p e r t i e s which must b e
investigated computationally.
c.
Honeywell (NAS8-11206)
(1)
S a t u r n V/Voyager Load R e l i e f
O b j e c t i v e : To d e v e l o p a n e f f e c t i v e l o a d r e l i e f
c o n t r o l s y s tem f o r t h e S a t u r n ~ I ~ o y a g e r
.
A load r e l i e f c o n t r o l system has been designed
f o r t h e S a t u r n VIVoyager which ( f o r t h e 95 p e r c e n t November s y n t h e t i c
wind p r o f i l e ) r e s u l t s i n a t o t a l b e n d i n g moment of o n l y 70 p e r c e n t o f t h e
a l l o w a b l e v a l u e a t t h e c r i t i c a l s t a t i o n . Parameter v a r i a t i o n s a r e n o t
considered i n t h i s value.
Terminal t r a j e c t o r y d i s p e r s i o n s a r e a b o u t
7 km, a l i t t l e o v e r t h r e e t i m e s as much a s t h o s e induced by a t t i t u d e
control.
�Current problems a r e i n t h e a r e a s of s l o s h
s t a b i l i t y and r i g i d body g a i n margin. E f f o r t s w i l l be made t o a r r i v e
a t s a t i s f a c t o r y s o l u t i o n s f o r t h e s e s i t u a t i o n s i n t h e coming month.
(2)
Development of T o l e r a n t C o n t r o l Systems
O b j e c t i v e : To develop c o n t r o l l e r s which maximize
t h e t o l e r a n c e t o v e h i c l e and environmental parameter v a r i a t i o n s .
A n a l y s i s w i t h r i g i d body dynamics has developed
a c a n d i d a t e system w i t h a d e q u a t e l y t o l e r a n t c h a r a c t e r i s t i c s over t h e
f i r s t s t a g e f l i g h t . However, t h e a d d i t i o n of t h e v e h i c l e bending
modes has produced t r a j e c t o r y r e g i o n s where d i f f e r e n t c o n t r o l charact e r i s t i c s a r e needed t o a c h i e v e t h e d e s i r e d t o l e r a n c e s .
The c a n d i d a t e
system i s being a d j u s t e d t o meet t h e new c o r r e l a t i o n s .
d.
North American A v i a t i o n
A f u r t h e r e x t e n s i o n of t h e o r b i t a l t r a n s f e r work
accomplished by t h e c o n t r a c t o r under NAS8-20238 has been r e q u e s t e d .
(1) t h r e e This work w i l l involve e x t e n s i o n s t o .
dimensional f i n i t e t h r u s t t r a n s f e r s between o r b i t s ; ( 2 ) a parameter
s t u d y t o i l l u s t r a t e d i f f i c u l t o r l i m i t i n g c a s e s of t h e o r b i t a l t r a n s f e r scheme of p a r t (1) ; (3) t h e e x t e n s i o n of q u a s i - l i n e a r i z a t i o n t e c h niques t o t h e c a s e of f i n i t e burn time, r e s t r i c t e d three-body maneuvers,
and t r a n s f e r s
A Denbow f o r m u l a t i o n i n v o l v i n g s t a g i n g w i l l be included
i n p a r t (3).
.
e.
C o r n e l l A e r o n a u t i c a l Lab (NAS8-18054)
O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g
l i n e a r optimal c o n t r o l t h e o r y t o t h e s y n t h e s i s of launch v e h i c l e cont r o l s y s tems
.
Work i s i n p r o g r e s s on a method of i n c o r p o r a t i n g a
s e n s i t i v i t y measure i n t h e performance index s o a s t o reduce s e n s i t i v i t y
of performance t o parameter v a r i a t i o n s . A major problem w i t h t h e curr e n t f o r m u l a t i o n i s t h a t , f o r a n n t h o r d e r system, each parameter being
considered adds n h y p o t h e t i c a l s t a t e s t o t h e s y s tem and consequently
r e q u i r e s n a d d i t i o n a l measurements.
This problem might be reduced by
u s i n g f i l t e r d e s i g n techniques t o approximate t h e "states:' b u t , even s o ,
t h e i n c r e a s e d o r d e r of t h e c o n t r o l l e d system would r e s u l t i n h i g h - o r d e r
filters.
�B.
Astrodynamics Branch
1.
I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House)
a . Work i s n e a r i n g completion on two double p r e c i s i o n ,
power s e r i e s i n t e g r a t i o n decks.
One of t h e decks i n t e g r a t e s n-bodies w i t h interdepende n t g r a v i t a t i o n a l f i e l d s and c o n t a i n s a p o t e n t i a l f u n c t i o n f o r t h e
c e n t r a l body ( u s u a l l y t h e e a r t h ) which i n c l u d e s t h e second, t h i r d , and
f o u r t h s p h e r i c a l harmonics. I n p u t t o and o u t p u t from t h i s deck can be
i n most any one of t h e commonly used C a r t e s i a n c o o r d i n a t e systems. An
i s o l a t i o n r o u t i n e capable of computing t h e i n i t i a l v e l o c i t y a s a f u n c t i o n
of t h e f l i g h t time and t a r g e t p l a n e t a r r i v a l parameters i s p r e s e n t l y being
added t o t h e deck; a n d , o u t p u t of a s s o c i a t e d c o n i c elements i s a l s o being
implemented.
The o t h e r deck i n t e g r a t e s t h r e e b o d i e s plus t h e probe
and i s s i m i l a r t o t h e one d e s c r i b e d above e x c e p t t h a t t h i s deck c o n t a i n s
thrust capability.
I n t h i s deck, t h e t h r u s t i n g a n g l e may be s p e c i f i e d
o r computed by t h e deck. I f computed by t h e deck, t h r u s t can be
d i r e c t e d p e r p e n d i c u l a r t o t h e probe-sun l i n e o r a l o n g t h e v e l o c . i t y
v e c t o r . The t h r u s t and mass flow r a t e a r e n o t c o n s t a n t , b u t d e c r e a s e
a s a f u n c t i o n of r ' l o 7 (where r i s t h e probe-sun d i s t a n c e ) . The Research
P r o j e c t s Laboratory h a s i n d i c a t e d t h a t t h i s should g i v e a good r e p r e s e n t a t i o n of t h e d e c r e a s e i n t h e power o u t p u t of s o l a r c e l l s .
Isp i s
cons i d e r e d a cons t a n t .
b. An i n i t i a l f a m i l i a r i z a t i o n s t u d y of t h e work done by
and f o r J P L i n t h e phase A and phase B s t u d i e s of Voyager has been comp l e t e d , and a comprehensive, in-depth survey of t h i s and r e l a t e d m a t e r i a l
i s now underway.
c , I n s u p p o r t of a f e a s i b i l i t y s t u d y of s o l a r e l e c t r i c
p r o p u l s i o n f o r i n t e r p l a n e t a r y v e h i c l e s being sponsored by t h e Research
P r o j e c t s Laboratory, a program designed t o i n v e s t i g a t e t h e e f f e c t s of
o b l a t e n e s s on a s a t e l l i t e i n a Martian o r b i t was formulated f o r use on
S t u d i e s using t h i s program have i n d i c a t e d that,
t h e IBM 1130 computer.
i f the c o r r e c t i n c l i n a t i o n i s used, a s a t e l l i t e w i l l remain f o r an
extended p e r i o d of time i n a sun shychronous o r b i t of Mars a t a l t i t u d e s
r a n g i n g from 1 , 0 0 0 t o 5,500 k i l o m e t e r s .
I n a d d i t i o n , t h e beginning and
ending d a t e s of t h e M a r t i a n seasons f o r t h e y e a r s from 1970 t o 1980
have been determined.
�d.
I n s u p p o r t of t h e Mars S u r f a c e Sample and Return Probe
(MSSR) s t u d i e s being d i r e c t e d by t h e Advanced S t u d i e s O f f i c e , a deck
was w r i t t e n f o r t h e IBM 1130 computer t o examine t h e v a r i o u s parameters
associated with hyperbolic o r b i t a l t r a n s f e r s i n the g r a v i t a t i o n a l f i e l d
of Wars. Also, a p a r a m e t r i c a n a l y s i s of t h e impulsive v e l o c i t y r e q u i r e ments f o r launching a probe from a f l y b y s p a c e c r a f t a t some time b e f o r e
p e r i a p s i s s o t h a t t h e probe a r r i v e s a t Mars b e f o r e t h e f l y b y s p a c e c r a f t
In addition, an analysis i s
a r r i v e s a t p e r i a p s i s i s being conducted.
being made of e n t r y a n g l e and v e l o c i t y c o n d i t i o n s of t h e probe a s i t
e n t e r s t h e Martian atmosphere plus a s t u d y of t h e communication d i s t a n c e s between t h e s p a c e c r a f t and t h e probe from time of launch from
t h e s p a c e c r a f t t o t h e p r o b e ' s impact w i t h Mars.
The d a t a n e c e s s a r y
f o r t h e s e a n a l y s e s have been o b t a i n e d .
2.
Support C o n t r a c t
a.
Cislunar Orbit Studies
The s t u d y t o determine t h e v e l o c i t y requirements
f o r m a i n t a i n i n g o r b i t s t a b i l i t y i n c i s l u n a r s p a c e over long time
i n t e r v a l s has been completed, and w i l l be documented soon.
b.
Interplanetary Transit Studies
Work is c o n t i n u i n g on t h e problem of adding powered
f l i g h t c a p a b i l i t y t o t h e Modified Marshall interplanetary Conic Tra ject o r y Program.
C.
Guidance Theory Branch
1.
Support C o n t r a c t S t u d i e s
a.
Low T h r u s t Guidance
R e s u l t s show t h a t a n a d a p t i v e d e l t a minimum guidance
scheme does not s a t i s f a c t o r i l y c o n t r o l t h e range a n g l e a t i n j e c t i o n i f
p e r t u r b a t i o n s occur d u r i n g t h e s p i r a l phase of a low t h r u s t t r a j e c t o r y .
A new technique was developed which uses t a n g e n t i a l t h r u s t u n t i l t h e
energy approaches w i t h i n LY~ of t h e d e s i r e d l e v e l . AE is chosen such
t h a t i t can be gained i n l e s s than one r e v o l u t i o n of t h e s p i r a l phase.
A 90-degree a n g l e of a t t a c k (no energy b u i l d u p ) i s used d u r i n g p a r t of
t h e l a s t r e v o l u t i o n i n o r d e r t o c o n t r o l t h e range a n g l e a t i n j e c t i o n .
A t t h e proper time t h e a n g l e of a t t a c k i s reduced back t o z e r o u n t i l
escape.
�b.
Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange M u l t i p l i e r s
Work h a s c o n t i n u e d on a s e r i e s s o l u t i o n f o r t h e i n i t i a l
L a g r a n g i a n m u l t i p l i e r s f o r optimum t r a n s f e r from a f i x e d p o i n t t o a n
ellipse.
The s i x t e r m i n a l c o n d i t i o n e q u a t i o n s h a v e b e e n expanded i n
T a y l o r s e r i e s of o r d e r f o u r , and programs have b e e n w r i t t e n f o r e a c h
s e r i e s t o n u m e r i c a l l y t e s t t h e i r a c c u r a c y u s i n g d a t a from a numerically.*'
integrated calculus of v a r i a t i o n s trajectory.
Debugging and f i n a l checko u t o f t h e s e t e s t programs have c o n t i n u e d .
c.
Voyager P r o j e c t S u p p o r t S t u d i e s
A new nominal S a t u r n V / ~ o y a g e r t r a j e c t o r y was computed
u s i n g new aerodynamic and w e i g h t d a t a . A s t u d y h a s b e e n i n i t i a t e d t o
d e t e r m i n e t h e performance of t h e I G M a p p l i e d t o t h e S a t u r n V/Voyager
m i s s i o n . An IGM d e c k i s now b e i n g p r e p a r e d f o r u s e i n t h i s s t u d y .
2.
In-House S t u d i e s
a . The c o d i n g n e c e s s a r y t o i n c l u d e c o r n e r c o n d i t i o n s i n t o
t h e program t o compute o p t i m a l o r b i t t r a n s f e r s w i t h o p t i m a l c o a s t i n g
t i m e s h a s been completed.
The program i s b e i n g checked o u t and t h e
n u m e r i c a l d i f f i c u l t i e s i n h e r e n t i n t h i s t y p e o f problem a r e b e i n g
investigated.
b. During t h i s r e p o r t i n g p e r i o d , a s t u d y of t h e b r a k i n g
p h a s e i n t o c a p t u r e o r b i t a b o u t Mars f o r t h e Mars P h o t o O r b i t e r M i s s i o n ,
r e q u e s t e d by R e s e a r c h P r o j e c t s L a b o r a t o r y , was i n i t i a t e d and f i n i s h e d .
S e v e r a l a p p r o a c h a l t i t u d e s were used a l o n g w i t h s e v e r a l d i f f e r e n t C 3
v a l u e s t o i n v e s t i g a t e t h e c a p t u r e maneuver a b o u t Mars.
c . A s u r v e y of g u i d a n c e c o n c e p t s whic'h could p o s s i b l y b e
used f o r t h e "Mars S u r f a c e Sample and R e t u r n P r o b e Mission" h a s b e e n
conducted.
R e s u l t s o f t h i s s t u d y w i l l b e f o r w a r d e d t o R-AERO-X i n
the near future.
3.
Contracts
a.
Boeing
-
Rendezvous Guidance
During t h i s r e p o r t i n g p e r i o d , i t was shown t h a t t h e
c o r r e c t i v e scheme f o r r e l a t i v e g u i d a n c e h a s t h e c a p a b i l i t y of hand1 i n g
t h r u s t v a r i a t i o n ofJ+3 percent. A switching f u n c t i o n h a s been developed
which p r e d i c t s e n g i n e i g n i t i o n t i m e f o r t h e f i n a l s t a g e .
The i d e a
employed i n t h e r e l a t i v e g u i d a n c e scheme was e x t e n d e d t o f o r m u l a t e t h e
switching function.
Programming i s complete on t h e i t e r a t i v e g u i d a n c e
scheme f o r a b u r n - c o a s t - b u r n t r a j e c t o r y and c h e c k o u t i s underway.
�b.
Lockheed
-
Rendezvous Guidance
A f i r s t burn p o l i c y ("time-to-go" and d i r e c t i o n ) is
being formulated a s a f u n c t i o n of t h e system s t a t e , i . e . , of t h e
s e p a r a t i o n a n g l e , i n t e r c e p t e r r a d i u s , v e l o c i t y and f l i g h t p a t h a n g l e .
The c o n t r o l law i s g i v e n by a s e t of f o u r t r a n s c e n d e n t a l a l g e b r a i c
e q u a t i o n s which a r e s o l v e d f o r time-to-go of t h e f i r s t burn and t h e
t h r u s t d i r e c t i o n . A s a f i r s t approximation, t h e assumption of c o n s t a n t
mass has been made. F u r t h e r m o d i f i c a t i o n w i l l i n c l u d e t h e case of a
v a r y i n g mass.
c.
General P r e c i s i o n
A computer program f o r a p p l y i n g quasi-optimum feedback guidance f o r t h e h e l i o c e n t r i c phase of t h e low t h r u s t problem has
been completed. A few numerical checks a r e b e i n g made t o determine t h e
e f f e c t i v e n e s s and a c c u r a c y of t h i s program b e f o r e c o n t i n u i n g w i t h t h e
p l a n e t - c e n t e r e d phase and t h e matching problem f o r t h e d i f f e r e n t phases.
d.
Vanderbil t U n i v e r s i t y
E f f o r t i s being continued on developing s u f f i c i e n c y
c o n d i t i o n s f o r m u l t i s t a g e c o n t r o l problems and on determining sequences
of sub-optimal s o l u t i o n tending toward a n optimal s o l u t i o n .
D.
S c i e n t i f i c Advisory Committee
1. A paper, " I n t e r p r e t a t i o n of Liapunov S t a b i l i t y Regions, I '
has been a c c e p t e d f o r p u b l i c a t i o n by t h e AIAA J o u r n a l .
2. Work is c o n t i n u i n g on e x i s t e n c e and uniqueness theorems
of o r d i n a r y d i f f e r e n t i a l e q u a t i o n s and t h e r e l a t i o n s between t h e s e
theorems and those r e l a t i n g t o p e r i o d i c s o l u t i o n b e h a v i o r .
A r e c e n t paper by Moyer c o n t a i n s a theorem which i n c l u d e s
a l l known uniqueness theorems. A n o t e i s b e i n g prepared showing t h a t
t h i s r e s u l t i s contained i n papers by Okamura p u b l i s h e d i n t h e 1 9 4 0 ' s .
3.
Hamil t o n i a n Sys tem S t a b i l i t y
The s t a b l e l i b r a t i o n p o i n t s of t h e r e s t r i c t e d three-body
problem a r e being i n v e s t i g a t e d by u s i n g Liapunov t h e o r y . R e s u l t s
o b t a i n e d i n d i c a t e t h a t q u a r t i c Liapunov f u n c t i o n s can be reduced t o
q u a d r a t i c f o r determining s u f f i c i e n t c o n d i t i o n s f o r s t a b i l i t y .
�4. The new r e s u l t s obtained f o r t h e l ' C o n t r o l l a b i l i t y of
S i n g l e - I n p u t Systems" s t u d y w i l l be published soon a s a NASA Technical
Note.
5.
C o n t r o l l a b i l i t y of General M u l t i - I n p u t L i n e a r Systems
Work i n t h i s a r e a has been c o n c e n t r a t e d on s o l v i n g t h e
f o l l o w i n g problems:
(a)
Given a g e n e r a l l i n e a r s y s tem, determine t h e
minimal number of independent i n p u t f u n c t i o n s
r e q u i r e d f o r t h e complete c o n t r o l l a b i l i t y of
t h e system.
(b)
Having determined t h e minimal number of i n p u t
f u n c t i o n s , determine t h e i n p u t coding-ma t r i x .
The f i r s t problem has been completely s o l v e d and a p r a c t i c a l method
o b t a i n e d which s p e c i f i e s t h e corresponding coding-matrix of problem (b).
These r e s u l t s a r e being prepared f o r p u b l i c a t i o n .
6.
Q u a l i t a t i v e Methods f o r Determininp t h e Behavior of
T r a j e c t o r i e s of Nonlinear D i f f e r e n t i a l Equations
over a F i n i t e Time I n t e r v a l
While t h i s s t u d y i s i n i t s e a r l y s t a g e s , s e v e r a l new
r e s u l t s have a l r e a d y been obtained which i n d i c a t e t h e approach t a k e n
should l e a d t o u s e f u l methods.
7.
Contracts
a.
Brown U n i v e r s i t y (NAS8-11264)
Objective:
dynamical systems.
Research i n t h e g e n e r a l a r e a of n o n l i n e a r
I n f a n t e and Slemrod have a p p l i e d t h e d i r e c t method of
Liapunov t o a c l a s s of problems of n o n l i n e a r p a r t i a l d i f f e r e n t i a l
e q u a t i o n s of the same n a t u r e a s t h e beam e q u a t i o n , and they have
o b t a i n e d s t a b i l i t y r e s u l t s t h a t g e n e r a l i z e t h o s e o b t a i n e d by Morchan.
H a l l and I n f a n t e a r e c o n t i n u i n g t h e i r work on t h e e x i s t e n c e of p e r i o d i c
s o l u t i o n s of weakly n o n l i n e a r s y s tems of p a r t i a l d i f f e r e n t i a l e q u a t i o n s
of t h e h y p e r b o l i c type.
M i l l e r has been working on some r e s u l t s i n t h e q u a n t i t a t i v e t h e o r y of i n t e g r a l e q u a t i o n s . This work c o n s i s t s p r e s e n t l y of
checking t h e d e t a i l s of t h e proof t h a t t h o s e e q u a t i o n s can be viewed a s
dynamical systems. He i s a l s o s e a r c h i n g f o r f u r t h e r examples t o which
t h i s theory a p p l i e s
.
�M i l l e r i s a l s o s t u d y i n g some problems i n p a r t i a l d i f f e r e n t i a l e q u a t i o n s . It appears t h a t one can g e t weak s o l u t i o n s of
n o n l i n e a r h y p e r b o l i c c o n s e r v a t i o n laws using a n analog of an o r d i n a r y
It i s hoped t h a t t h e s o l u t i o n s
d i f f e r e n t i a l e q u a t i o n s technique.
o b t a i n e d i n t h i s manner w i l l be t h e p h y s i c a l l y i n t e r e s t i n g ones.
Weiss i s c o n t i n u i n g h i s work on t h e t h e o r y of m a t r o i d s
and on c o n d i t i o n s f o r c o n t r o l l a b i l i t y of d e l a y - d i f f e r e n t i a l e q u a t i o n s .
The work of Minty on t h i s s u b j e c t i s being i n t e g r a t e d w i t h e a r l i e r work
of Idhitney and T a t t e , and t h e main theorems of Minty have been reproved
s t a r t i n g w i t h t h e more u s u a l axioms d e f i n i n g m a t r o i d .
The connections
between T a t t e ' s work and t h e problem of e x i s t e n c e and uniqueness of
s o l u t i o n s t o e l e c t r i c a l network e q u a t i o n s a r e b e i n g worked o u t .
F u r t h e r r e s u l t s on c o n t r o l l a b i l i t y c o n d i t i o n s f o r
d e l a y - d i f f e r e n t i a l e q u a t i o n s beyond those r e p o r t e d on i n e a r l i e r
p r o g r e s s r e p o r t s a r e under development.
Meyer has been working on t h e problem of c h a r a c t e r i z i n g
s t r u c t u r a l l y s t a b l e systems by means of a g l o b a l Liapunov f u n c t i o n .
I n g e n e r a l , a s t r u c t u r a l l y s t a b l e system i s a system of d i f f e r e n t i a l
e q u a t i o n s whose g l o b a l phase p o r t r a i t does n o t change under s m a l l pert u r b a t i o n s . Meyer has e s t a b l i s h e d some l o c a l lemmas t h a t w i l l be needed
f o r t h e g l o b a l c h a r a c t e r i z a t i o n . ,.
b.
General P r e c i s i o n (NAS8-20062)
O b j e c t i v e : I n v e s t i g a t e s t a b i l i t y p r o p e r t i e s of
p e r i o d i c and alrnos t p e r i o d i c o r b i t s .
A computer program which w i l l normalize a timedependent Hamiltonian i s p r e s e n t l y being prepared.
The development of
t h i s program i s d i v i d e d i n t o two phases: second o r d e r n o r m a l i z a t i o n ,
and h i g h e r o r d e r n o r m a l i z a t i o n s
The r o u t i n e f o r hig'her o r d e r normal i z a t i o n s i s n e a r l y complete. Emphasis w i l l t h e n t u r n t o t h e second o r d e r
normal i z a t i o n which w i l l i n c l u d e t h e symbolic r e p r e s e n t a t i o n of t h e
s o l u t i o n of a system of l i n e a r d i f f e r e n t i a l e q u a t i o n s w i t h p e r i o d i c
coefficients
.
.
c.
Grumnan A i r c r a f t Engineering Corp (NASB-20306)
Objective:
l i n e a r dynamical s y s terns.
Determine s t a b i l i t y domains f o r non-
During October and November, add i t i o n a l improvements
were made i n t h e computer program f o r e s t i m a t i n g t h e domain of a t t r a c t i o n ( s t a b i l i t y domain) of t h e e q u i l i b r i u m s o l u t i o n of n o n l i n e a r dynamical
�systems. The second q u a r t e r l y p r o g r e s s r e p o r t has been i s s u e d . Part i c u l a r items d i s c u s s e d i n t h e r e p o r t a r e a s follows:
(1) Some e x p e r i mental r e s u l t s o b t a i n e d by means of t h e procedures developed d u r i n g
t h e f i r s t q u a r t e r ; (2) r e f o r m u l a t i o n of t h e procedure t o avoid comput a t i o n a l d i f f i c u l t i e s encountered d u r i n g t h e experiments; ( 3 ) development of a p a r a m e t e r i z a t i o n of t h e s e t of p o s i t i v e d e f i n i t e n x n
m a t r i c e s ; and (4) a n a l y s i s of a s y s tem w i t h time-dependent closed-loop
guidance.
d.
Drexel I n s t i t u t e of Technology (NAS8-20347)
Objective:
Research i n methods of g e n e r a t i n g Liapunov
functions.
During t h e c u r r e n t r e p o r t i n g p e r i o d , s e v e r a l l i n e s of
i n v e s t i g a t i o n were followed.
(1) E v a l u a t i o n of t h e work done by D r . J e s s e Clay
d u r i n g t h e s u m e r of 1966 (see monthly r e p o r t s f o r J u l y and August).
It was decided t h a t t h i s l i n e of i n v e s t i g a t i o n is f a r t o o g e n e r a l t o
produce any p r a c t i c a l r e s u l t s a t t h i s s t a g e of our knowledge. Perhaps
i t would be f r u i t f u l t o r e t u r n t o t h i s work a f t e r g a i n i n g more d e t a i l e d
knowledge of some p a r t i c u l a r Liapunov f u n c t i o n s .
(2) An a t t e m p t was made t o f i n d some s o r t of connect i o n between some of t h e v a r i o u s methods of g e n e r a t i n g Liapunov funct i o n s . S p e c i f i c a l l y , examples were chosen (from among t h e worked
examples i n R. rake's r e p o r t ) i n which Liapunov f u n c t i o n s were found
by t h e v a r i a b l e g r a d i e n t t e c h n i q u e , and an a t t e m p t was made t o o b t a i n
Liapunov f u n c t i o n s by t h e use of one o r a n o t h e r of t h e i n t e g r a t i o n by
p a r t s techniques and by t h e use of I n f a n t e ' s i n t e g r a l method.
Fair
s u c c e s s was achieved w i t h autonomous systems, 5 = f ( z ) , when t h e o r d e r
of the s y s tem was two o r t h r e e and t h e f i ( s ) were polynomials i n t h e
xi's.
But no s u c c e s s a t a l l f o r h i g h e r o r d e r systems o r f o r more comp l i c a t e d forms of t h e f i ( z ) % .
The s u c c e s s of any g i v e n method a p p e a r e d ,
from our e f f o r t s , t o depend most h e a v i l y on t h e i n g e n u i t y of t h e
i n v e s t i g a t o r and v e r y l i t t l e on t h e form of t h e system of e q u a t i o n s a t
hand.
The v a r i o u s methods t r i e d seem t o be i s o l a t e d from each o t h e r
i n t h e s e n s e t h a t i t i s impossible t o t e l l a p r i o r i which method i s
l i k e l y t o b e s u c c e s s f u l f o r a g i v e n system of e q u a t i o n s .
e.
Lockheed M i s s i l e s and Space Company, H u n t s v i l l e
Research and Engineering Center (NAS8-20323)
Objective:
p e r i o d i c motions.
Perform r e s e a r c h i n t h e s t a b i l i t y of
�During October and November t h e Recurrence Theorem
comprising Chapter 30 of S i e g e l and t h e mapping theorem of Moser were
s t u d i e d . I n the former we proceed, a s u s u a l , from a system of d i f feren t i a l equations
i n which t h e f u n c t i o n s f k ( x ) need n o t be r e g u l a r b u t mus: be d i f f e r e n t i a b l e i n t h e r e a l domain, R , considered.
A p p l i c a t i o n s t o t h e r e s t r i c t e d t h r e e body problem and
t o t h e n-body problem a r e g i v e n i n S i e g e l .
Siege1 men-cions t h a t t h e
method i s f r a u g h t w i t h problems which appear d i f f i c u l t even compared
t o o t h e r methods of determining s t a b i l i t y .
However, s i n c e S i e g e l f s t e x t was p u b l i s h e d , two
n o t a b l e s t e p s have been made, one by Arnold and t h e o t h e r by Moser.
That of Moser h a s been b r i e f l y s t u d i e d and concerns t h e e x i s t e n c e of
i n v a r i a n t curves i n a n a r e a - p r e s e r v i n g mapping. We have s e e n t h z t trle
e l l i p t i c c a s e of t h e a r e a - p r e s e r v i n g mapping i s , i n t h e n ~ r m a iform,
a t w i s t mapping*and hence a l l c i r c l e s c e n t e r e d a t t h e o r i g i n a r e
i n v a r i a n t . Now Moser c o n s i d e r s a p e r t u r b e d mapping and g i v e s suf
f i c i e n t c o n d i t i o n s f o r t h i s p e r t u r b e d mapping t o have i n v a r i a n t curves
n e a r c o n c e n t r i c c i r c l e s . We know t h a t , i n a s u f f i c i e n t l y small n e l g k borhood a n e l l i p t i c type mapping can be bought a r b i t r a r i l y c i o s : ? t o a
t w i s t mapping by a convergent t r a n s f o r m a t i o n s o t'mt we can conside:
i t a p e r t u r b a t i o n of a t w i s t mapping. Moser then continues ic r e c l ~ c ~
t h e s t a b i l i t y problem t o one of f i n d i n g two numbers, Z, 3 , and shcijs
s t a b i l i t y f o r (3 # 0. This paper w i l l s t i l l be under s t u d y d u r i n g
December and w i l l be commented on more f u l l y i n a l a t e r p r o g r e s s r e p o r t .
-
f.
The U n i v e r s i t y of Texas (NAS8-18120)
Objective:
guidance s y s tems
.
Study of s ~ a b i l . i t yand sensitivity of
The s t u d y has been d i v i d e d e s s e n t i a l l y i n t o chred
parts:
( a ) A comprehensive s t u d y i s being made of t h e meaning of
s e n s i t i v i t y a s r e l a t e d t o c o n t r o l systems.
This s t u d y has r e c e n c l y
produced d e f i n i t i o n s of s e n s i t i v i t y , p r a c t i c a l i t y and f e a s i b i l i t y f ~ r
c o n t r o l systems f o r b o t h l a r g e and small v a r i a t i o n s i n s e l e c t e d parame t e r s . A complete formalism i s expected t o be e s t a b l i s h e d i n t h e ned,
future.
(b) The second a r e a of work has been i n t h e development of
c r i t e r i a of s t a b i l i t y d e t e r m i n a t i o n of coupled suboptimal nonl i n e a r
systems.
The aim i s t o o b t a i n methods of a n a l y s i s by means of which
i t can be determined how t h e coupling of simple sub-systems w i l l d f i c ~ c
�t h e s t a b i l i t y of t h e system t o w h i c h they belong.
( c ) The t h i r d a r e a
of work i s i n e s t a b l i s h i n g n e c e s s a r y a n a l y s i s and c o m p u t a t i o n a l p r o c e d u r e s f o r s t u d y i n g t h e s t a b i l i t y o f g u i d a n c e s y s t e m s and t h e o p t i m i z a t i o n problems a s s o c i a t e d w i t h A p o l l o - t y p e m i s s i o n s .
The a t t e m p t w i l l b e
made t o e s t a b l i s h methods whereby t r u l y optimum t r a j e c t o r i e s could b e
obtained f o r Apollo-type lunar t r a j e c t o r i e s .
VI.
AEROPHYSICS DIVISION
A.
F l u i d Mechanics R e s e a r c h O f f i c e
1.
O r b i t a l Gauge Response
I n O c t o b e r , M r . B a l l a n c e met w i t h Goddard Space F l i g h t
C e n t e r p e r s o n n e l t o d i s c u s s t h e i n - s i t e measurements of t h e u p p e r
a t m o s p h e r e by d e n s i t y and mass s p e c t r o m e t e r gauges of E x p l o r e r X V I I
and X X X I I . M r . B a l l a n c e p o i n t e d o u t t r e n d s i n t h e i r p u b l i s h e d d a t a
w h i c h h e c o n s i d e r e d t o be a n obvious i n d i c a t i o n of t h e s o u r c e o f e r r o r
i n t h e measurements, and d e m o n s t r a t e d some p r e l i m i n a r y r e s u l t s o f a
Monte C a r l o a n a l y s i s made of t h e Redhead gauge which c o r r e l a t e d v e r y w e l l
w i t h t h e f l i g h t d a t a . The Goddard p e r s o n n e l d i d n o t a c c e p t t h e a r g u ment i n i t s e n t i r e t y , b u t d i d a g r e e t h a t i t seemed r e a s o n a b l e .
They
r e q u e s t e d t h a t a p a r a m e t r i c s t u d y o f b o t h t h e Redhead d e n s i t y gauge
and t h e B a y a r d - A l p e r t d e n s i t y gauge b e made.
It a p p e a r e d t o be e a s i e r
and q u i c k e r t o m o d i f y t h e d e c k s and o b t a i n t h e d a t a h e r e a t M a r s h a l l
t h a n t o t r y t o t r a i n t h e Goddard p e r s o n n e l i n t h e l o g i c and o p e r a t i o n
of t h e program.
A c c o r d i n g l y , a program o f a p p r o x i m a t e l y 160 h o u r s of
CDC 3200 time was e s t a b l i s h e d .
Mr. Ballance monitors t h e d a t a a s they
a r e o b t a i n e d , t o v e r i f y p r o p e r o p e r a t i o n , and f o r w a r d s t h e r e s u l t s t o
Goddard f o r a n a l y s i s . About 85 h o u r s of t h e program i s c o m p l e t e . A
summary r e p o r t of t h e d a t a i s b e i n g p r e p a r e d f o r o u r r e c o r d s .
2.
Sounding Rocket Gauge Response
A program s i m i l a r t o t h a t b e i n g conducted f o r Goddard was
done l a s t s p r i n g and summer on t h e mass s p e c t r o m e t e r b e i n g used on t h e
MUMP ( M a r s h a l l Upper Atmosphere Measuring P r o b e ) . A r e p o r t i s b e i n g
p r e p a r e d showing t h e r e s u l t s .
It i s i n t e r e s t i n g t o o b s e r v e t h a t , s i n c e
i t was d i f f i c u l t t o program t h e e x a c t p h y s i c a l geometry of t h e p r o b e ,
a s imp1 i f i e d g e o m e t r y , which t h e U n i v e r s i t y of Michigan i s now a d o p t i n g
i n t o t h e d e s i g n o f t h e s e n s o r , was u s e d .
3.
O r b i t a l Aerodynamic C a l c u l a t i o n s R e s e a r c h
The commonly a c c e p t e d method f o r aerodynamic c a l c u l a t i o n s
f o r a n o r b i t i n g s y s tem i s t h a t t h e l e a d i n g e l e m e n t c a s t s i t s "shadow"
o n t o a n y t r a i l i n g e l e m e n t s and removes t h a t a r e a from c o n t r i b u t i o n t o
�the calculations.
I n a Monte C a r l o program a n a l y z i n g two c o a x i a l d i s c s ,
t h e s e a s s u m p t i o n s a r e b e i n g examined, a s w e l l as a n y m u l t i p l e c o l l i s i o n
e f f e c t s w i t h r e f l e c t i n g molecules.
Some v e r y i n t e r e s t i n g r e s u l t s ,
which show t h a t p r e s e n t a s s u m p t i o n s a r e s i g n i f i c a n t l y i n e r r o r , a r e
being obtained.
For p r e s e n t e n g i n e e r i n g c a l c u l a t i o n s f o r t h e S a t u r n o r b i t i n g s y s t e m no change i s p r e s e n t l y p l a n n e d ; however, t h e computer d e c k s
a r e b e i n g m o d i f i e d s o t h a t t h e "shadowing" f a c t o r s can b e machinec a l c u l a t e d r a t h e r t h a n h a n d - c a l c u l a t e d a s done i n t h e p a s t . T h i s i s
made p o s s i b l e by i n c o r p o r a t i n g t h e c o n c e p t s of r a d i a t i o n h e a t t r a n s f e r
v i e w f a c t o r c a l c u l a t i o n s i n t o t h e program.
B.
M e c h a n i c a l Design O f f i c e
A s t u d y model of t h e G r a v i t y S i m u l a t i o n Workbench i s b e i n g
b u i l t , f o r u s e i n e x p e r i m e n t a l l y d e t e r m i n i n g t h e optimum work s u r f a c e
and i n l e t c o n f i g u r a t i o n , s c r e e n s i z e s , e t c .
D e s i g n of a s i n g l e component m i c r o f o r c e b a l a n c e f o r u s e i n
t h e Low D e n s i t y Chamber h a s p r o g r e s s e d beyond t h e i n i t i a l c o n c e p t
stage.
Work h a s c o n t i n u e d i n s u p p o r t of t h e d e s i g n of t h e High
Reynolds Number F a c i l i t y w i t h p a r t i c u l a r emphasis p l a c e d on t h e
diaphragm c u t t e r a s s e m b l y .
The f o l l o w i n g is a p a r t i a l l i s t o f a d d i t i o n a l p r o j e c t s and
their current status:
Viscous C r o s s Flow F o r c e Model and B a l a n c e
Delivered.
Updated S a t u r n V F o r c e Model
-
14" W.T.
M o d i f i c a t i o n o f Nozzles f o r S.T.S.
-
-
-
14" W.T.
-
Delivered.
14" W.T.
P l e x i g l a s s Models f o r C r o s s Beam i n S.T.S.
Delivered.
F i n and Asymmetric Body and B a l a n c e s
t ion.
-
-
-
Delivered.
14" W.T.
14" W.T.
-
Sidewall-Mounted I n n e r s t a g e Ring Model and B a l a n c e
14" W.T. - F a b r i c a t i o n .
-
Fabrica-
-
Updated S a t u r n IB Tank Loads F o r c e Model and B a l a n c e 14" W. T. - D r a f t i n g completed ( f a b r i c a t i o n c a n c e l l e d ) .
�8' O.D. Vacuum Exhaust Plenum
b e c a u s e of l a c k of f u n d s ) .
-
D r a f t i n g (holding
P e r f o r a t e d F l o o r and C e i l i n g Assembly, T.T.S.
14" W. T.
Fabrication.
-
-
P r e s s u r e Models f o r Cross Beam i n S.T.S.
Fabrication
S a t u r n I B Thin S k i n Heat T r a n s f e r Model
Base H e a t i n g Model
C.
-
IBFF
-
-
-
14" W.T.
JPL
-
Des i g n .
Fabrication.
Aerodynamic Design Branch
1.
SaturnV
a . A p o l l o / S a t u r n V s t a t i c aerodynamic l o c a l l o a d d i s t r i b u t i o n s were d e f i n e d a t Mach numbers of 0, 0 . 5 , 4.0 and 7.0 f o r 6, 8 ,
1 0 , 1 2 , 1 4 and 1 6 d e g r e e s a n g l e of a t t a c k by e x t r a p o l a t i n g e x i s t i n g
S a t u r n V aerodynamic d e s i g n c r i t e r i a . These d a t a , which were d e f i n e d
by TBC i n C o o r d i n a t i o n S h e e t No. AT-H-027, e x t e n d t h e p r e s e n t d e s i g n
The Boeing document i s b e i n g p u b l i s h e d
c r i t e r i a i n NASA TM X-53517.
a s d e s i g n c r i t e r i a i n O f f i c e Memorandum R-AERO-AD-66-52.
b.
The Boeing Company h a s r e c e n t l y completed a n i n - f l i g h t
v e n t i n g a n a l y s i s of t h e major compartments on t h e S-IC s t a g e . I n t e r n a l
p r e s s u r e h i s t o r i e s have been g e n e r a t e d f o r t h e b a s e compartment, t h e
i n t e r t a n k compartment, and t h e S-IC/S-I1 i n t e r s t a g e compartments.
These d a t a a r e b e i n g reviewed by MSFC f o r a p p r o v a l as d e s i g n d a t a .
c. The c o n t r o l f a c t o r s and v a r i a t i o n a l a n a l y s i s f o r
A p o l l o S a t u r n 502 w i l l be a v a i l a b l e by J a n u a r y 1967. The d a t a a r e
b e i n g s u p p l i e d by t h e Boeing Company f o r d i s t r i b u t i o n by R-AERO-AD.
d. Aerodynamic h i n g e moments f o r A p o l l o / S a t u r n V S-IC
e n g i n e were d e f i n e d f o r each e n g i n e a c t u a t o r a t Mach numbers from 0 . 5
t o 3.5 f o r a n g l e s of a t t a c k from 0 t o 15 d e g r e e s , e n g i n e d e f l e c t i o n s
from 0 t o 4 d e g r e e s , and v e l o c i t y r o l l a n g l e s of 0 t o 45 d e g r e e s .
These d a t a a r e b a s e d on t h e h i n g e moment t e s t (AD-3-64) conducted i n
t h e Lewis R e s e a r c h c e n t e r ' s 1 0 x 1 0 - f o o t s u p e r s o n i c wind t u n n e l and
8 x 6 - f o o t t r a n s o n i c wind t u n n e l . These d a t a , which were d e f i n e d by
TBC i n C o o r d i n a t i o n S h e e t No. AT-H-016, a r e b e i n g e s t a b l i s h e d a s
d e s i g n c r i t e r i a i n a n R-AERO-AD o f f i c e memorandum t o be pub1 i s h e d i n
t h e n e a r f u t u r e . Hinge moments f o r e a c h v e h i c l e w i l l be d e f i n e d by
TBC based on t h i s document and t r a j e c t o r y and c o n t r o l s t u d i e s f o r t h e
particular vehicle.
�e . The aerodynamic c h a r a c t e r i s t i c s of t h e S a t u r n V a b o r t
c o n f i g u r a t i o n a r e b e i n g d e t e r m i n e d . V e h i c l e s t a b i l i t y and d r a g have
been d e f i n e d , and l o c a l normal f o r c e d i s t r i b u t i o n s a r e b e i n g b a l a n c e d
w i t h s t a b i l i t y d a t a . The d a t a from t h i s a n a l y s i s w i l l cover t h e same
f l i g h t c o n d i t i o n s a s t h o s e i n TM X-53517 f o r S a t u r n V.
The a b o r t a e r o dynamics w i l l s o o n b e p u b l i s h e d i n a n o f f i c e memorandum.
.
f
P r e l i m i n a r y aerodynamics f o r t h e S a t u r n ~ / ~ o y a g e r
(54' s h r o u d l e n g t h ) a r e b e i n g p r e p a r e d . I n a d d i t i o n t o t o t a l a e r o dynamics, d i s t r i b u t e d aerodynamics w i l l b e p r e s e n t e d f o r Mach numbers
o f 1 . 0 0 , 1.20, 1 . 4 3 , 1.70 and 2.00 f o r a n g l e s of a t t a c k up t o 15 d e g r e e s .
These d a t a w i l l soon be p u b l i s h e d i n a n o f f i c e memorandum.
A wind t u n n e l t e s t h a s b e e n conducted i n t h e MSFC
1 4 - i n c h T r i s o n i c Wind Tunnel t o d e t e r m i n e t h e s t a t i c s t a b i l i t y and
a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n V Voyager l a u n c h v e h i c l e w i t h
a 4 5 - f o o t Voyager payload e n v e l o p e . A 0.3366 p e r c e n t s c a l e model was
t e s t e d a t Mach numbers from 0.50 t o 5.00 and a t a n g l e s of a t t a c k up t o
1 6 d e g r e e s . The d a t a a r e b e i n g i n c o r p o r a t e d i n a n aerodynamic d e s i g n
memorandum.
g.
S a t u r n V/Voyager I n - F l i g h t Venting: P r e l i m i n a r y
i n t e r n a l p r e s s u r e time h i s t o r i e s a r e b e i n g d e f i n e d f o r t h e f i v e i n t e r i o r
compartments i n t h e r e g i o n of t h e Voyager Shroud. Because of s t e r i l i z a t i o n r e q u i r e m e n t s , t h e two Voyager compartments w i l l b e v e n t e d w i t h
v a l v e s i n t o a d j o i n i n g compartments, which w i l l , i n t u r n , be v e n t e d by
f l a t p l a t e c u t - o u t s i n t o t h e e x t e r n a l s t r e a m . An e x i s t i n g two-compartment v e n t i n g program h a s been m o d i f i e d t o p r e d i c t t h e i n t e r n a l p r e s s u r e
time h i s t o r i e s f o r t h i s t y p e of v e n t i n g scheme.
h.
Cone-Cylinder Frustum-Cylinder T r i s o n i c Study: The
f i n a l r e p o r t from Lockheed, " T r i s o n i c Loads Study,'' h a s been r e c e i v e d
and i s s a t i s f a c t o r y . This r e p o r t (LMSC/HREC8783468) c o n t a i n s t h e
r e s u l t s of a p a r a m e t r i c wind t u n n e l t e s t o f cone-cyl i n d e r - f l a r e - c y l i n d e r
models. The l o a d d i s t r i b u t i o n s o v e r t h e s e models were d e t e r m i n e d by
i n t e g r a t i n g p r e s s u r e s around t h e c i r c u m f e r e n c e of t h e body.
The l o c a l
normal f o r c e d i s t r i b u t i o n s were t h e n i n t e g r a t e d and compared w i t h
e x p e r i m e n t a l f o r c e d a t a . T h i s r e p o r t i s a n advance i n t h e s t a t e - o f t h e - a r t i n t h a t t h e aerodynamic d e s i g n e r can now d e f i n e l o a d d i s t r i b u t i o n s i n t h e t r a n s o n i c Mach regime (0.7 t o 2.0).
T h e o r e t i c a l methods,
s u c h as second o r d e r shock e x p a n s i o n s , l i n e a r i z e d t h e o r y , Van ~ y k e ' s
above Mach 1 . 5 and h y p e r s o n i c impact t h e o r y above Mach 5 . 0 can be used
t o d e f i n e l o a d d i s t r i b u t i o n s . A s u b s o n i c t h e o r y , which h a s a l s o b e e n
d e v e l o p e d , i s u s e f u l up t o Mach numbers of 8 . 0 .
However, r e l i a b l e
t h e o r e t i c a l methods i n t h e t r a n s o n i c Mach number regime d o n o t e x i s t .
The r e s u l t s of t h i s Lockheed s t u d y a r e i n t e n d e d t o f i l l t h e v o i d i n
t h e t r a n s o n i c Mach number regime.
�i. Q - B a l l E r r o r A n a l y s i s : A r e p o r t d e s c r i b i n g t h e use
and accuracy of EDS Q - B a l l was published d u r i n g November.
The t i t l e is
" Q - B a l l E v o l u t i o n , Emergency D e t e c t i o n System A p p l i c a t i o n , and E r r o r
Analysis a s Applied t o t h e A p o l l o / S a t u r n , " R-AERO-AD-66-40, dated
September 1 5 , 1966.
j.
S-IC/S-11
I n t e r s t a g e Aerodynamic I n v e s t i g a t i o n : Data
from t h e s u p e r s o n i c t e s t s conducted i n t h e MSFC 1 4 x 14" TWT i n June
1966 a r e b e i n g a n a l y s e d on a p a r t - t i m e b a s i s w h i l e p r e p a r a t i o n s a r e
being made f o r t h e s u b s o n i c and t r a n s o n i c t e s t s .
These t e s t s w i l l use
a technique i n which one-half of t h e model i s mounted on a s p l i t t e r
p l a t e , which i s , i n t u r n , mounted t o t h e t u n n e l s i d e w a l l .
The models
and b a l a n c e s being f a b r i c a t e d should be ready f o r t e s t s scheduled f o r
e a r l y January.
k.
The o r i f i c e flow c o e f f i c i e n t i n v e s t i g a t i o n , which
s u p p o r t s t h e S a t u r n V v e n t i n g program, was conducted i n t h e Ames Research
c e n t e r ' s 6 x 6-foot s u p e r s o n i c t u n n e l from October 17, 1966 t o November 1 8 ,
1966. Because of model hardware problems caused by poor f a b r i c a t i o n and
i n s t r u m e n t a t i o n , t h e t e s t o b j e c t i v e s were n o t reached. Although o n l y a
l i m i t e d amount of d a t a was o b t a i n e d , it should be s u f f i c i e n t t o s u p p o r t
t h e f i r s t S a t u r n V f l i g h t . P r e s e n t p l a n s a r e t o complete t h e t e s t
The model w i l l b e r e d e s i g n e d and r e b u i l t t o
program a t Ames i n A p r i l .
c o r r e c t e r r o r s and d e f i c i e n c i e s t o i n s u r e t h a t t h e t e s t time w i l l be
used e f f i c i e n t l y .
The c o n t r a c t w i t h Northrop Space L a b o r a t o r i e s w i l l be
extended t o a l l o w completion of t h e planned t e s t program, a l o n g w i t h
a d d i t i o n a l work which i n c l u d e s a s t u d y of o r i f i c e flow c o e f f i c i e n t s f o r
g a s e s o t h e r than a i r and a s h o r t program i n t h e MSFC 1 4 x 1 4 - i n c h TWT.
This program w i l l determine t h e f e a s i b i l i t y of running v e n t i n g s t u d i e s
i n t h e MSFC f a c i l i t y .
1. S a t u r n V Load D i s t r i b u t i o n Report: Lockheed has comp l e t e d a r e p o r t p r e s e n t i n g t h e r e s u l t s of s t a t i c p r e s s u r e measurements
o b t a i n e d on a 4 p e r c e n t s c a l e model of t h e S a t u r n V launch v e h i c l e i n
t h e AEDC 1 6 - f o o t t r a n s o n i c wind t u n n e l .
This r e p o r t c o n t a i n s l o c a l
p r e s s u r e d i s t r i b u t i o n s , l o c a l normal f o r c e c o e f f i c i e n t s , l o c a l normal
f o r c e c o e f f i c i e n t g r a d i e n t s ( f o r a = 0°), and boundary l a y e r p r o f i l e s
f o r Mach numbers from 0.6 t o 1.45 and a n g l e s of a t t a c k up t o 10 d e g r e e s .
The r e p o r t should be a v a i l a b l e by December 15, 1966.
2.
Uprated S a t u r n I B
Hypersonic s t a t i c s t a b i l i t y and a x i a l f o r c e t e s t s of t h e
AS-206 c o n f i g u r a t i o n have been completed i n t h e AEDC Tunnel E . Data
were o b t a i n e d a t Mach numbers of 5 , 6, 7 , and 8 through an a n g l e of
These d a t a a r e being analyzed and
a t t a c k range from - 3 t o +12 degrees.
a s t a t i c aerodynamic r e p o r t covering t h e f l i g h t Mach range of t h e AS-206
w i l l be published soon.
�Aerodynamic design d a t a f o r t h e S a t u r n IB/LEM a l o n e
v e h i c l e a r e being r e v i s e d , based on t h e r e s u l t s of s e v e r a l wind tunnel
The r e v i s e d s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s
tests
have been documented i n R - A E R O - A D - ~ ~ - ~ s~u, p e r s e d i n g R-AERO-AD-66-25.
Maximum/minimum and z e r o a n g l e - o f - a t t a c k e x t e r n a l p r e s s u r e d i s t r i b u t i o n s
f o r the upper s t a g e , documented i n CCSD TB-AP-66-62, a r e being approved
f o r use a s d e s i g n c r i t e r i a .
.
Wind t u n n e l t e s t s i n t h e MSFC 1 4 x 14-irich TWT t o d e t e r mine t a n k l o a d s , s t r a p - o n l o a d s , and s t a t i c s t a b i l i t y of s e v e r a l proposed u p r a t e d S a t u r n I B c o n f i g u r a t i o n s have been completed. T e s t
con£ i g u r a t i o n s included b o t h two and f o u r UTC-120 seven-segment s o l i d
r o c k e t motor s t r a p - o n u n i t s .
S t a t i c s t a b i l i t y and s t r a p - o n l o a d s were
much a s expected; however, tank l o a d s on t h e 70-inch diameter S-IB
b o o s t e r tanks were i n c r e a s e d by a f a c t o r of two i n f o r c e s and a f a c t o r
It was
of t h r e e i n moments from t h e o p e r a t i o n S-IB c o n f i g u r a t i o n .
found t h a t t h e s e l o a d s could be s i g n i f i c a n t l y reduced by u s i n g a d i f f e r e n t nose shape on t h e s t r a p - o n u n i t s .
Forthcoming r e p o r t s a r e
expected t o be ready f o r t h e phase I11 C h r y s l e r c o n t r a c t .
S t a t i c tank l o a d s f o r t h e 70-inch d i a m e t e r S a t u r n I B tanks
were determined f o r s i m u l a t e d ground winds by t e s t i n g a 0.55 p e r c e n t
s c a l e d model i n t h e Wyle low speed wind t u n n e l . The primary purpose
of t h e i n v e s t i g a t i o n was t o v a l i d a t e t h e f e a s i b i l i t y of using s m a l l
s c a l e d models f o r measuring tank l o a d s . The r e s u l t s of t h e s e t e s t s
compare q u i t e f a v o r a b l y w i t h d a t a o b t a i n e d from l a r g e s c a l e models.
Tank l o a d s were a l s o determined f o r one of t h e u p r a t e d S a t u r n I B conf i g u r a t i o n s which has f o u r UTC-120 s o l i d r o c k e t motor s t r a p - o n u n i t s .
3.
General
a.
O r b i t a l Aerodynamics: A p a r a m e t r i c s t u d y was conducted on t h e S a t u r n I/SA-5 o r b i t a l v e h i c l e t o i n v e s t i g a t e t h e s e n s i t i v i t y of body-to-ambient temperature r a t i o (from 0.2 t o 0.5) and
molecular speed r a t i o (from 7 t o 10) on o r b i t a l aerodynamic p r o p e r t i e s .
For p e r f e c t thermal accommodation, a 150 p e r c e n t i n c r e a s e i n t h e temp e r a t u r e r a t i o i n c r e a s e d t h e aerodynamic d r a g c o e f f i c i e n t a b o u t 2 p e r cent.
S i m i l a r l y , a 43 p e r c e n t i n c r e a s e i n t h e molecular speed r a t i o
decreased t h e drag c o e f f i c i e n t l e s s than 3 p e r c e n t . An a n a l y s i s has
been completed t o i n v e s t i g a t e t h e e f f e c t s of t h e c o n c a v i t y of a s p h e r i c a l
s u r f a c e on t h e aerodynamic p r o p e r t i e s . By comparing t h e r e s u l t s w i t h
i t s corresponding convex s u r f a c e , t h e change i n t h e aerodynamics due t o
c o n c a v i t y was about 1 p e r c e n t (assuming a g a i n p e r f e c t thermal accommoda t i o n )
.
�b. O r b i t a l Aerodynamics: Lockheed has c a l c u l a t e d t h e
o r b i t a l aerodynamics f o r t h e SA-504 o r b i t a l c o n f i g u r a t i o n i n a 188.4 km
c i r c u l a r e a r t h o r b i t . A p r e l i m i n a r y d a t a r e p o r t should soon be a v a i l able.
Lockheed i s p r e s e n t l y c a l c u l a t i n g o r b i t a l aerodynamics
f o r t h e LM/ATM c l u s t e r c o n f i g u r a t i o n . Some d a t a should be a v a i l a b l e
i n rough form by December 9 , 1966.
D.
Experimental Aerophysics Branch
1.
14 x 14-Inch T r i s o n i c Wind Tunnel
a . An i n v e s t i g a t i o n i s being made f o r t h e s t u d y and
r e f i n e m e n t of h i g h a n g l e - o f - a t t a c k t e s t i n g u s i n g t h e r e f l e c t i o n plane
technique f o r Apollo s p a c e c r a f t and a r i g h t c i r c u l a r c y l i n d e r c o n f i g u r a tion.
This t e s t used a new s idewall-mounted b a l a n c e and a n g l e - o f - a t t a c k
mechanism. A f u l l 360-degree range of a l p h a i s provided by t h e
s y s tem.
T o t a l runs:
68.
b. An i n v e s t i g a t i o n t o determine t h e i n f l u e n c e of wake
d i r e c t i n g and n o n d i r e c t i n g s o u r c e s on t h e S a t u r n I B and V Apollo command and s e r v i c e modules i s being made by Lockheed f o r R-AERO-AU.
A body such a s a cone, mounted upstream of the model,
i s forced t o o s c i l l a t e a t v a r i o u s amplitudes and f r e q u e n c i e s up t o 200 cps.
The t e s t model i s submerged i n t h e wake of t h e o s c i l l a t i n g body, and t h e
unsteady f o r c e s a r e r e c o r d e d . C o r r e l a t i o n w i l l y i e l d a "convective
v e l o c i t y " of t h e wake. These d a t a w i l l become p a r t of t h e "quasi-steady"
method of determining s t a t i c s t a b i l i t y d e r i v a t i v e s . The i n s t r u m e n t a t i o n
and r e c o r d i n g systems f o r t h i s t e s t were designed and f u r n i s h e d by
R-AERO-AE.
Much d i f f i c u l t y and l o s t t e s t time were experienced
d u r i n g t h e t e s t because of model hardware f a i l u r e and t h e i n a b i l i t y
t o f u n c t i o n p r o p e r l y under t e s t c o n d i t i o n s . The hardware i s now b e i n g
r e e v a l u a t e d and modified f o r t h e n e x t t e s t p e r i o d , which i s scheduled
f o r mid-January 1967. T o t a l runs t o d a t e :
110. The d a t a o b t a i n e d
were analyzed by R-AERO-AE and Lockheed p e r s o n n e l , u s i n g our analog
c o r r e l a t o r and a t a p e loop machine borrowed from R-COMP-R.
c. The v i s c o u s cross-flow e f f e c t s on v a r i o u s b o d i e s of
r e v o l u t i o n a t h i g h a n g l e s of a t t a c k a r e being s t u d i e d . The vapor
s c r e e n method of flow v i s u a l i z a t i o n , which i s t o be t r i e d l a t e r i n
t h i s t e s t , has n o t been p r e v i o u s l y used a t MSFC; some p i l o t s t u d i e s
were conducted i n t h e 7- x 7-inch wind t u n n e l . A s m a l l l a s e r was
used a s a l i g h t s o u r c e w i t h encouraging r e s u l t s .
�d.
An i n v e s t i g a t i o n t o determine t h e r e p e a t a b i l i t y of d a t a
a t overlapping a n g l e s of a t t a c k using s t i n g s which m a i n t a i n t h e same
model c e n t e r of r o t a t i o n i s being made. T o t a l runs:
10.
e. The s t a t i c l o n g i t u d i n a l s t a b i l i t y and a x i a l f o r c e
c h a r a c t e r i s t i c s of s e v e r a l S a t u r n V Voyager c o n f i g u r a t i o n s a r e being
49.
determined.
T o t a l runs:
2.
7- x 7-Inch B i s o n i c Wind Tunnel
The i n v e s t i g a t i o n by R-AERO-T i n t o t h e use of l a s e r s i n
measuring gas v e l o c i t i e s w a s terminated d u r i n g October. The t e r m i n a t i o n
of t h e i n v e s t i g a t i o n was due i n p a r t t o t h e c o r r o s i v e a c t i o n of t h e
t r a c e r m a t e r i a l on t h e t u n n e l components. R-AERO-AT w i l l c o n t i n u e t h e i r
i n v e s t i g a t i o n i n Bldg. 4311 u s i n g small 3-dimens i o n a l n o z z l e s .
3.
Thermal-Acous t i c J e t F a c i l i t y
The Cold Flow Duct was busy d u r i n g October concluding t h e
f i n a l f a c i l i t y checks b e f o r e t h e IITRI p e r s o n n e l a r r i v e d . The f i r s t
p r o d u c t i v e t e s t i n g was done i n November i n c o n j u n c t i o n w i t h IITRI
p e r s o n n e l ; t h e cross-beam c o r r e l a t i o n technique was used a s a flow
analysis tool.
The e a r l y t e s t r e s u l t s were v e r y s a t i s f a c t o r y . Addit i o n a l flow a n a l y s e s of t h e j e t s t r e a m a r e now being made by means of
h i g h speed movies.
An 8000-frame-per-second movie camera was i n s t a l l e d i n t h e
s c h l i e r e n s y s tem; a b o u t 25 runs were made t o s e e i f t h e r e i s a n uns t e a d i ness i n t h e shock s t r u c t u r e . F u r t h e r t e s t s a r e scheduled i n which p r e s s u r e surveys a r e t o be made of s i n g l e and c l u s t e r n o z z l e a r r a y s . A
l i m i t e d sound-pressure l e v e l survey was t a k e n around t h e n o z z l e e x i t .
(See memo d a t e d November 1, 1966 from John Heaman t o Ken Johnston,
R-AERO-AM. )
The helium h e a t e r h a s been assembled and i s being checked
out.
The c o n t r a c t o r , Fuel Engineering Company, has had a d d i t i o n a l p r e s s u r e c o n t r o l l e r problems which a r e now s o l v e d . This has delayed t h e
d e l i v e r y s c h e d u l e a n a d d i t i o n a l t h r e e weeks. D e l i v e r y i s s t i l l u n c e r t a i n .
4.
Hot and Cold Flow T e s t F a c i l i t i e s
A cover was made f o r t h e pebble bed h e a t e r t o provide a
1i g h t - s h i e l d e d a r e a f o r shadowgraph s t u d i e s i n t h e i n v e s t i g a t i o n of
Mach wave r a d i a t i o n a s a n o i s e s o u r c e i n a s u p e r s o n i c r o c k e t e x h a u s t .
This cover allowed completion of t h e t e s t . A d d i t i o n a l t e s t i n g i s
planned f o r e a r l y n e x t y e a r .
�5.
Data Reduction and Process in%
Boeing personnel were t r a i n e d i n t h e u s e of some of our
analog a c o u s t i c and v i b r a t i o n a n a l y s i s equipment t o a n a l y z e ground wind
data.
The program t o reduce t h e Cold Flow Duct c a l i b r a t i o n d a t a
The program reduces
was completed, and more than 50 runs were reduced.
measured p r e s s u r e s and temperatures t o e n g i n e e r i n g u n i t s , and c a l c u l a t e s
l o c a l Mach number, v e l o c i t y , d e n s i t y , Reynolds number, and v i s c o s i t y
from t h e measurements.
Data have been r e c e i v e d i n magnetic t a p e form from t h e
R-AERO-AD t e s t of t h e v i s c o u s c r o s s flow models a t LTV. A program was
developed t o t r a n s c r i b e t h e d a t a o n t o c a r d s , and t h e c a r d s were used
f o r f u r t h e r r e d u c t i o n w i t h our programs and f o r p l o t t i n g .
S t a t i c p r e s s u r e d a t a from t h e S a t u r n V 4 p e r c e n t a c o u s t i c
t e s t a t AEDC, which have been r e c e i v e d on magnetic t a p e , was converted
t o cards f o r p l o t t i n g .
The conversion program may be used f o r any AEDCg e n e r a t e d d a t a . A l l conversion uses t h e CDC 3200 computer i n Bldg. 4200.
~ x c e l l e n ta s s i s tance was g i v e n by R-COMP.
Three d i f f e r e n t p r e s e n t a t i o n s have been g i v e n by R-COMP on
t h e i r f h i r d - g e n e r a t i o n computer system. S e v e r a l problems which have
a l r e a d y been discovered a r e being r e s o l v e d by M r . Jandebeur.
Two wide-band magnetic t a p e systems a r e being used t o
make d u p l i c a t e d a t a t a p e s of t h e f i r s t phases of t h e S a t u r n V 4 p e r c e n t
R-AERO-AE i s reducing 11 runs o r 1200 sound-pressure
acoustic test.
l e v e l s from t h e s e dubbed t a p e s .
R e s u l t s of t h e reduced d a t a w i l l be
a v a i l a b l e t o -AU i n e a r l y December.
6.
Low D e n s i t y Chamber
C a l i b r a t i o n of t h e Mach 4 low d e n s i t y n o z z l e has c o n t i n u e d ,
and s u c c e s s i v e c a l i b r a t i o n runs have been made t o e s t a b l i s h r e p e a t a b i l i t y
of the Mach number a t t h e n o z z l e e x i t plane.
These r u n s have been comp l e t e d , and t h e d a t a a r e being reduced.
C a l i b r a t i o n runs w i t h t h e impact
p r e s s u r e probe downstream and upstream of t h e n o z z l e e x i t a r e being made
t o e s t a b l i s h t h e Mach number g r a d i e n t . Experiments a r e being designed
f o r measuring drag f o r c e s on s p h e r e s , hemispheres, c y l i n d e r s and wedges
i n t h e low d e n s i t y flow. Drag f o r c e s w i l l f i r s t b e measured by v a r i o u s
simple techniques such a s displacement measurement and t o r s i o n b a l a n c e
technique. A pendulum-type b a l a n c e has been designed and i s i n t h e
shop f o r f a b r i c a t i o n .
�The f i r s t s e r i e s of experiments w i t h t h e molecular beam i s
completed. Molecular beam i n t e n s i t i e s have been s u c c e s s f u l l y measured
w i t h a VEECO RG-75 h o t cathode i o n i z a t i o n gauge, thus d e f i n i n g a w e l l c o l l i m a t e d beam f o r t h e c a p t u r e c o e f f i c i e n t experiments. The maximum
i n t e n s i t y recorded was 8.8 x loL3 molecules p e r second f o r a carbon
d i o x i d e s t a g n a t i o n p r e s s u r e of 3850 t o r r . T e s t s u s i n g t h e Sloan Quartz
Microbalance a t LN, temperature t o d e t e c t condensing CO, have been comp l e t e d , and t h e d a t a a r e being analyzed.
Work has been delayed on t h e t i t a n i u m pumping experiment
i n f a v o r of t h e molecular beam experiment.
7.
IBFF
-
The North American A v i a t i o n Dual Plane S e p a r a t i o n T e s t
(AT-62) conducted f o r AERO-AT was completed. A l l d a t a were t r a n s m i t t e d
t o North American viat ti on' s Space and I n f ormation Sys tems Divis i o n f o r
a n a l ys is.
Hot flow f o r c e d a t a g e n e r a l l y a g r e e d w i t h t h e cold flow
f o r c e d a t a o b t a i n e d p r e v i o u s l y a t Langley. However, a t s m a l l i n t e r s t a g e
s e p a r a t i o n d i s t a n c e s , t h e f o r c e d a t a were h i g h e r t h a n expected, according t o N.A.A.
Some p r e s s u r e and h e a t t r a n s f e r d a t a were o b t a i n e d . A l l
p r e s s u r e d a t a g e n e r a l l y agreed w i t h t h e o r e t i c a l p r e d i c t i o n s .
Heat
t r a n s f e r d a t a on t h e h e a t s h i e l d were much h i g h e r t h a n expected f o r a l l
s e p a r a t i o n di s tances
.
A h i g h Reynolds number model f a c i l i t y was f a b r i c a t e d and
tested a t an e a r l i e r date.
The f o l l o w i n g g e n e r a l d a t a t r e n d s were
established:
(1)
Flow e s t a b 1 ishment time a t s u b s o n i c , t r a n s o n i c
and s u p e r s o n i c speeds.
(2)
S t a r t time and s t a r t load comparisons w i t h
t h e primary diaphragm l o c a t e d upstream and
downstream of t h e t e s t s e c t i o n .
A 0.5 s c a l e t e s t s e c t i o n of t h e h i g h Reynolds number model
f a c i l i t y has been f a b r i c a t e d and i s b e i n g t e s t e d t o o b t a i n d a t a t r e n d s
on a s c a l e d f a c i l i t y .
�8.
Heat T r a n s f e r I n s trumenta t i o n
The h e a t t r a n s f e r work on t h e 1000°F gauges h a s been
t e r m i n a t e d f o r t h e p r e s e n t . Upon a r r i v a l and t e s t i n g of t h e f i r s t
u n i t s , e v a l u a t i o n s w i l l resume.
E v a l u a t i o n s of t h e performance of newer t y p e s h e a t t r a n s f e r gauges a r e c o n t i n u i n g i n t h e IBFF.
9.
M i s c e l laneous
a . A low-speed t a n k l o a d s t e s t of t h e S a t u r n IB and
p o s s i b l e u p r a t e d s t r a p - o n c o n f i g u r a t i o n s was conducted by R-AERO-AD
a t Wyle L a b o r a t o r i e s u s i n g t h e i r low s p e e d wind t u n n e l . A d i g i t a l
d a t a a c q u i s i t i o n s y s tem, c a r d punch, and a s s o c i a t e d s i g n a l c o n d i t i o n i n g
equipment were t a k e n t o Wyle and used f o r t h e t e s t .
The d a t e f o r t h e second phase of t h e S a t u r n V 4 p e r b.
c e n t a c o u s t i c model t e s t a t AEDC h a s s l i p p e d t o J a n u a r y 9 , 1967.
Checkout and p r e l i m i n a r y c a l i b r a t i o n s o f t h e model and i n s t r u m e n t a t i o n
w i l l be done a t MSFC b e f o r e shipment t o AEDC., The equipment w i l l be
shipped b e f o r e t h e Christmas holidays.
c. Forced o s c i l l a t i o n b a l a n c e No. 208 has b e e n i n c o r p o r a t e d i n t o a t e s t j i g t o d e t e r m i n e t h e e f f e c t s of l i f t and d r a g l o a d s
upon t h e a c c u r a c y o f s t r a i n gauge a n g u l a r d i s p l a c e m e n t t r a n s d u c e r s .
P r e l i m i n a r y t e s t s have i n d i c a t e d t h a t t h e i n a c c u r a c y of t h e d i s p l a c e ment t r a n s d u c e r i s a b o u t two p e r c e n t o r l e s s .
10.
G r a v i t y S i m u l a t i o n Workbench
\
P r e l i m i n a r y work h a s begun i n t h e d e f i n i t i o n of t h e comp o n e n t s of t h e workbench. Hardware i s b e i n g d e s i g n e d f o r a p r e l i m i n a r y
i n v e s t i g a t i o n of t h e g r a v i t y s i m u l a t i o n workbench c o n c e p t . T h i s t e s t
w i l l u s e a p r e s e n t l y a v a i l a b l e c e n t r i f u g a l blower t o i n c l u d e f l o w
t h r o u g h t h e f u l l s c a l e workbench model. The t e s t , t o be conducted a t
a t m o s p h e r i c p r e s s u r e , w i l l a l s o use a t u r b i n e - t y p e f l o w m e t e r t o measu r e t o t a l mass f l o w t h r o u g h t h e bench work s u r f a c e . The t e s t s c h e d u l e
i s i n d e f i n i t e b e c a u s e of t h e b o t t l e n e c k s a n t i c i p a t e d i n d e l i v e r y of
t h e hardware from ME L a b o r a t o r y .
11.
S a t u r n V High Angle-of-Attack
Loads I n v e s t i g a t i o n
High Reynolds Number
With encouragement from t h e NASA R e s e a r c h A d v i s o r y Comm i t t e e on Space V e h i c l e Aerodynamics, t h e Aerophys i c s D i v i s i o n h a s
submitted a t e s t requirement f o r obtaining Saturn V load d i s t r i b u t i o n
a t h i g h a n g l e of a t t a c k and v e r y h i g h Reynolds number ( a b o u t 500 x 10"'
�based on model l e n g t h ) t o R&DO f o r funding. This requirement has a l s o
been included i n t h e Lab's S a t u r n V " s o f t s p o t " l i s t . Action i s s t i l l
pending on t h i s item, and a subsequent p r e s e n t a t i o n t o t h e MSFC Direct o r ' s o f f i c e w i l l be made i n t h e n e a r f u t u r e .
C e r t a i n hardware and
l e g a l d e t a i l s a r e being worked o u t w i t h F a c i l i t i e s and Design O f f i c e
and t h e Chief Counsel, r e s p e c t i v e l y .
E.
Thermo Environment Branch
1.
Saturn I B
a.
Aerothermodynamics
The SA-204 launch v e h i c l e thermal environment was
p u b l i s h e d d u r i n g October. The aerodynamic h e a t i n g p o r t i o n of t h e SA-204
launch v e h i c l e environment was found t o be approximately 2 p e r c e n t l e s s
s e v e r e than t h e SA-201 environment.
Corresponding b a s e thermal environments were found t o be comparable i n s e v e r i t y t o t h o s e environments
experienced by SA-202.
As a r e s u l t of t h e s e f i n d i n g s , no thermal problems
a r e a n t i c i p a t e d d u r i n g t h e SA-204 f l i g h t .
The SA-206 maximum aerodynamic h e a t i n g environmental
r e p o r t i s being p u b l i s h e d . R e s u l t s contained i n t h i s r e p o r t were based
on t h e maximum aerodynamic h e a t i n g t r a j e c t o r y f o r SA-206 published
October 1 2 , 1965. This t r a j e c t o r y r e s u l t e d i n a n environment t h a t was
a b o u t 8 p e r c e n t and 1 8 p e r c e n t more s e v e r e t h a n t h e corresponding environments f o r SA-201 and SA-202, r e s p e c t i v e l y .
However, a new SA-206 r e f e r ence t r a j e c t o r y i s now being computed by MSFC. E s t i m a t e s by MSFC i n d i c a t e
t h a t t h e new t r a j e c t o r y i s more s e v e r e than t h e previous maximum h e a t i n g
t r a j e c t o r y . P r e p a r a t i o n s a r e now being made t o determine t h e new more
s e v e r e maximum SA-206 aerothermodynamic h e a t i n g environment. Analyses
w i l l begin a s soon a s t h e new maximum h e a t i n g t r a j e c t o r y i s a v a i l a b l e .
b.
Base Heating
Analyses t o determine maximum b a s e and e x h a u s t plume
h e a t i n g environments f o r t h e SA- 206 v e h i c l e have been completed. R e s u l t ing maximum environments were published d u r i n g October. Also included
i n t h i s document a r e d i s c u s s i o n s concerning b o t h t h e c o n v e c t i v e and plume
r a d i a t i o n models developed a t CCSD. I n t e r s t a g e h e a t i n g , a s produced by
r e t r o and u l l a g e motor exhaust plume impingement, i s a l s o c o n s i d e r e d .
Base and aerodynamic h e a t i n g d a t a o b t a i n e d from model
t e s t s and a n a l y t i c a l p r e d i c t i o n s a r e being c o r r e l a t e d w i t h S a t u r n I B
flight test results.
This c o r r e l a t i o n was done f o r aerodynamic h e a t i n g
environments , H- 1 engine exhaus t r a d i a n t h e a t i n g r a t e s , and S-IB s t a g e
base region convective h e a t t r a n s f e r c o e f f i c i e n t s .
I n addition, correl a t i o n of r e t r o - r o c k e t plume impingement h e a t i n g d a t a h a s been i n i t i a t e d .
�A r e p o r t documenting t h e r e s u l t s of t h e s e e f f o r t s w i l l be r e l e a s e d i n
December f o r t h e SA-203 v e h i c l e . A s i m i l a r r e p o r t f o r t h e SA-201 and
SA-202 v e h i c l e s i s s c h e d u l e d f o r p u b l i c a t i o n d u r i n g J a n u a r y 1967.
I n s u p p o r t of v e h i c l e d a t a c o r r e l a t i o n , work i s cont i n u i n g on r e f i n i n g t h e t u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g comp u t e r program, which was developed t o p r e d i c t l o c a l thermochemical
p r o p e r t i e s i n t h e j e t wake f l o w f o r a c o n s t a n t p r e s s u r e e q u i l i b r i u m
c h e m i s t r y plume.
The p r e s e n t r e f i n e m e n t s i n v o l v e ( a ) i n c l u s i o n o f a n
eddy v i s c o s i t y f o r t h e f a r - j e t - m i x i n g c a s e , ( b ) d i r e c t c o u p l i n g of
NASA/LEWIS thermochemical s u b r o u t i n e t o p r o v i d e t h e r e q u i r e d e q u i l i b r i u m
c h e m i s t r y d a t a , and ( c ) w r i t i n g a s u b r o u t i n e t o a n a l y t i c a l l y p r e d i c t
spot concentrations.
I t e m s ( a ) and ( b ) a r e a b o u t 50 p e r c e n t c o m p l e t e ,
b u t item ( c ) has only been o u t l i n e d i n theory. P a r a m e t r i c runs w i l l
b e conducted u s i n g t h e program, and t h e r e s u l t s w i l l b e compared w i t h
s i m i l a r i n t e g r a l s o l u t i o n s p r e s e n t e d i n t h e l i t e r a t u r e . T h i s work
s h o u l d b e completed by mid-December.
E x i s t i n g computer programs and t e c h n i q u e s used t o
d e t e r m i n e r a d i a t i o n form f a c t o r s a r e b e i n g r e v i e w e d . These programs
a r e a v i t a l p a r t o f d e t e r m i n i n g thermal e n v i r o n m e n t s t o a r e a s o f t h e
S a t u r n IB v e h i c l e a f f e c t e d by e x h a u s t plume r a d i a t i o n .
c.
Thermodynamic F l i g h t E v a l u a t i o n
-
S-IB S t a g e
P r e l i m i n a r y p r e p a r a t i o n s f o r t h e e v a l u a t i o n of SA- 204
t h e r m a l d a t a a r e b e i n g made. Meanwhile, a n a l y s i s o f d a t a from t h e
SA-203 s p e c t r o m e t e r i s c o n t i n u i n g . Two r e c e n t changes w e r e i n t r o d u c e d
i n t h e s p e c t r o m e t e r d a t a r e d u c t i o n program b e c a u s e of a n a p p a r e n t s h i f t
i n a m p l i f i c a t i o n of t h e o u t p u t s i g n a l t h a t occurred a t approximately
75 s e c o n d s of f l i g h t . The program c a l c u l a t e s t h e i n t e g r a t e d a v e r a g e d
i n t e n s i t y o f e a c h c h a n n e l f o r e a c h of t h e t h r e e s p a t i a l s c a n s and f o r
t h e c a l i b r a t i o n c y c l e . An a t t e m p t i s b e i n g made t o c o r r e l a t e t h e
change i n t h e i n t e n s i t y l e v e l s of t h e s p a t i a l s c a n s w i t h t h e change i n
t h e l e v e l s of t h e c a l i b r a t i o n c y c l e a s a f u n c t i o n of t i m e . T h i s c o r r e l a t i o n s h o u l d y i e l d a time-dependent compensation f a c t o r t h a t would
ad j u s t t h e i n t e n s i t y l e v e l s of t h e d a t a i n l i n e w i t h changes i n t h e
l e v e l o f t h e c a l i b r a t i o n c y c l e . A r e p o r t on t h e s p e c t r o m e t e r d a t a
s h o u l d b e completed soon.
d.
S-IB High Angle o f A t t a c k
The i n a b i l i t y of t h e JPL H y p e r s o n i c Wind Tunnel t o
The
e s t a b l i s h t u r b u l e n t f l o w a t Mach number 6 i s c r e a t i n g problems.
l a m i n a r h e a t i n g r a t e i s low, and t h e r e s u l t i n g s k i n t e m p e r a t u r e r i s e
a p p e a r s t o be t o o s m a l l t o a l l o w a n a c c u r a t e t e m p e r a t u r e - t i m e s l o p e
measurement.
The p o s s i b i l i t y of r u n n i n g a s h o r t t e s t i n t u n n e l A of
AEDC a t t h e h i g h e r Mach numbers i s b e i n g s t u d i e d . The JPL f a c i l i t y
w i l l s t i l l b e used f o r t h e lower Mach numbers.
�An a n a l y t i c a l a p p r o a c h t o t h e h e a t i n g problems of
b o d i e s o f r e v o l u t i o n a t h i g h a n g l e o f a t t a c k i s underway.
2.
Saturn V
a.
S a t u r n V/Voyager Thermal Environment
An a n a l y s i s was s t a r t e d t o p r e d i c t t h e t h e r m a l e n v i r o n ment of t h e S a t u r n VIVoyager. Data f o r t h e f i r s t 250 s e c o n d s o f f l i g h t ,
which a r e b e i n g i n p u t t o t h e SHORE/CATCH computer program, c o n s i s t o f
c o n f i g u r a t i o n d a t a , m a t e r i a l p r o p e r t i e s , h e a t s i n k d e s c r i p t i o n , and f l o w
f i e l d ( p r e s s u r e ) d a t a . R e s u l t s o f a p r e l i m i n a r y r u n a r e b e i n g checked
f o r p o s s i b l e i n p u t e r r o r s . When t h e i n p u t d a t a a r e found t o b e c o r r e c t ,
t h e e n t i r e 250 s e c o n d s w i l l b e r u n .
Results of t h i s run w i l l provide
h e a t t r a n s f e r c o e f f i c i e n t s , recovery temperatures, wall temperatures,
and h e a t r a t e s f o r t h e f i r s t 250 s e c o n d s o f t h e S a t u r n V l ~ o y a g e rf l i g h t .
b.
Design Assurance
-
S-IC
Two a n a l y s e s have b e e n completed and a r e now b e i n g
i n c o r p o r a t e d i n t o t h e d e s i g n a s s u r a n c e document:
(1)
Energy t r a n s f e r from s o l i d m o t o r p a r t i c l e s
t o s u r f a c e s using experimental t e s t d a t a .
(2)
An a n a l y t i c a l d e t e r m i n a t i o n o f t h e f l o w
f i e l d r e s u l t i n g from a r o c k e t motor
e x h a u s t i n g i n t o a n oncoming s tream.
P u b l i c a t i o n s "Thermal Environment o f t h e Confined
D e t o n a t i n g Fuse and t h e R e t r o Rockets" and "Revised C o n v e c t i v e Heat
T r a n s f e r C o e f f i c i e n t f o r I U R e t r o ~ e f l e c t o r "w i l l b e i n c l u d e d i n t h e
d e s i g n a s s u r a n c e document.
c.
O p e r a t i o n a l Thermal Environment
-
SA-501
The document " S a t u r n V Launch V e h i c l e F i n a l Thermal
Environment SA-501 , I f which c o n t a i n s e s t i m a t e s o f t h e e n v i r o n m e n t s f o r
s p e c i f i c f l i g h t c a l o r i m e t e r s , g a s p r o b e s , t h e r m o c o u p l e s , and p r e s s u r e
t a p s on t h e S a t u r n SA-501 f l i g h t v e h i c l e , h a s b e e n completed.
3.
Miscellaneous
a.
Base P r e s s u r e and Environment
The p o r t i o n s of t h i s s t u d y now under i n v e s t i g a t i o n
i n v o l v e t h e t u r b u l e n t boundary l a y e r g r o w t h on n o z z l e w a l l s w i t h mass
i n j e c t i o n and t h e r e a c t i n g s h e a r l a y e r a t t h e plume boundary.
�The GASL f i n i t e - r a t e s h e a r l a y e r program i s being
used t o i n v e s t i g a t e t h e e f f e c t of e x i t plane j e t temperature on t h e
a f t e r b u r n i n g flame s tand-of f d i s tance.
A hand c a l c u l a t i o n procedure is being e s t a b l i s h e d t o
p r e d i c t h e a t i n g r a t e s downstream of Hz v e n t s on S a t u r n c l a s s v e h i c l e s .
It i s expected t h a t t h e r e s u l t s from computer program i n v e s t i g a t i o n s
of t h i s problem can be condensed t o a few simple formulas t o be used
w i t h one o r two p a r a m e t r i c c h a r t s .
R e s u l t s of t h e t e s t f i r i n g of C o r n e l l ' s 1 / 2 0 s c a l e
model F-1 engine a r e s t i l l pending.
b.
A b l a t i v e M a t e r i a l s Analysis
Work i s c o n t i n u i n g on t h e decomposition-in-depth comp u t e r program. A problem has been found i n t h e c o n t i n u i t y of t h e flow
between time s t e p s . A d d i t i o n a l e q u a t i o n s a r e being added t o t h e s e t
which i s solved s i m u l t a n e o u s l y i n a n e f f o r t t o c o r r e c t t h i s . Also,
work has s t a r t e d on t h e h e a t i n g a n a l y s i s f o r t h e Mars S o i l Sample
R e t r i e v a l Study.
c.
S t a g e S e p a r a t i o n Thermodynamics
The computer program t o p r e d i c t impingement p r e s s u r e s
a l o n g a s o l i d boundary i n t h e s t r o n g shock r e g i o n of a r o c k e t exhaust
impingement flow f i e l d has been completed and t h e r e s u l t s checked
a g a i n s t b o t h experimental d a t a and v a l u e s o b t a i n e d i n t h e p a s t by
hand c a l c u l a t i o n s . For comparison, a s e c t i o n was added t o t h e program
which computes t h e t h e o r e t i c a l Newtonian p r e s s u r e s a t t h e same p o i n t s
a l o n g t h e boundarywhere t h e s t r o n g shock c a l c u l a t i o n s a r e made.
A new a r e a of i n t e r e s t i n impingement h e a t i n g has been
e x p l o r e d . When a r o c k e t exhaust plume impinges on a s o l i d boundary a t
v e r y h i g h a l t i t u d e s , i t seems c e r t a i n t h a t p o r t i o n s of t h a t boundary
w i l l e x p e r i e n c e f r e e molecular h e a t i n g . A t p r e s e n t , t h e r e a r e s e v e r a l
programs a v a i l a b l e t o c a l c u l a t e t h i s h e a t i n g i f t h e medium i s "cold"
a i r , which, of c o u r s e , i s a poor assumption i n a r o c k e t e x h a u s t . Thus,
a new c a l c u l a t i o n scheme was devised t o handle f r e e molecular h e a t i n g
i n high temperature e x c i t e d g a s e s . This new scheme has been i n c o r p o r a t e d
method of characi n t o a computer program which depends on t h e LMSC/HREC
t e r i s t i c s (MOC) d e s c r i p t i o n of t h e plume flow f i e l d f o r i n p u t . S i n c e
no experimental d a t a on f r e e molecular h e a t i n g r a t e s i n h i g h temperat u r e g a s e s a r e a v a i l a b l e , i t was decided t o i n p u t t h e c a s e of a f l a t
p l a t e a t a n a n g l e of a t t a c k i n "cold" a i r and check t h e r e s u l t s of t h e
program a g a i n s t t h e o u t p u t of a conventional f r e e molecular h e a t i n g
program. The agreement was e x c e l l e n t . This agreement i s n e c e s s a r y
b u t n o t s u f f i c i e n t proof of t h e v a l i d i t y of t h e c a l c u l a t i o n scheme.
It w i l l be s t u d i e d i n more d e t a i l .
�d.
Nozzlc and J c t Wakc Sttidy
Measured and c a l c u l a t e d p i t o t p r e s s u r e s i n t h e plume
of a c o l d f l o w 1 / 5 6 s c a l e model F-1 e n g i n e h a v e b e e n compared. The
a n a l y t i c a l c a l c u l a t i o n s were made u s i n g t h e method o f c h a r a c t e r i s t i c s
R e s u l t s , which i n d i c a t e f a i r agreement, w i l l be published i n t h e near
future.
5-2 e n g i n e f l o w f i e l d s w i t h e x t e n s i o n s k i r t s h a v e been
studied.
S k i r t h a l f - a n g l e s were v a r i e d from 4 . 9 d e g r e e s i n 2 - d e g r e e
i n c r e m e n t s . I n e a c h c a s e , t h e c a l c u l a t i o n s w e r e c o n t i n u e d downstream
t o a n a r e a r a t i o of 200.
A r e p o r t h a s b e e n p r e p a r e d documenting t h e work p e r formed t o d a t e on a new method f o r computing s u p e r s o n i c f l o w f i e l d s .
T h i s method computes t h e f l o w f i e l d a l o n g s t r e a m l i n e s and n o r m a l s .
The u l t i m a t e g o a l o f t h i s t y p e o f a p p r o a c h i s t o h a n d l e m u l t i p l e s h o c k s
i n the flow f i e l d .
e.
E q u i l i b r i u m Real Gas/Normal Shock Program f o r S t a g n a t i o n P o i n t Heating
Mass i n j e c t i o n e f f e c t s h a v e b e e n added t o t h e b o u n d a r y
l a y e r s o l u t i o n , and t h e r e s u l t i n g computer program i s b e i n g checked o u t .
A l s o , e f f o r t was d e v o t e d t o p r e d i c t i n g c o n v e c t i v e h e a t r a t e s f o r e n t r y
of a v e h i c l e i n t o t h e M a r t i a n atmosphere. E n t r y t r a j e c t o r i e s have been
e s t a b l i s h e d , and b o u n d a r y c o n d i t i o n s d e t e r m i n e d f o r i n p u t t o t h e convective heating routines.
Shock l a y e r r a d i a t i o n p r e d i c t i o n t e c h n i q u e s
a r e b e i n g r e v i e w e d , and t h e m o s t a p p l i c a b l e w i l l b e used i n t h i s s t u d y .
f
.
Thermal R a d i a t i o n Memorandum
A p r o p o s e d NASA TM X e n t i t l e d "Theory o f Thermal R a d i a t i o n from L i q u i d and S o l i d P r o p e l l a n t Rocket E x h a u s t s ," h a s b e e n w r i t t e n .
I n t h i s 200-page memorandum, n e a r l y 600 r e f e r e n c e s a r e d i s c u s s e d , and
n e a r l y 500 e q u a t i o n s a r e p r e s e n t e d which d e s c r i b e t h e d e t a i l s of
g a s e o u s r a d i a t i o n , r a d i a t i o n from c a r b o n p a r t i c l e s , and r a d i a t i o n
from A1 ?03 p a r t i c l e s .
The e q u a t i o n o f r a d i a t i o n t r a n s f e r i s d e r i v e d
i n d e t a i l , and s o l u t i o n s a r e g i v e n w h i c h i n c l u d e t h e e f f e c t s o f
s c a t t e r i n g (Mie and R a y l e i g h ) , a s w e l l a s e m i s s i o n and a b s o r p t i o n . The
a n a l y s e s o f s p e c t r a l l i n e b r o a d e n i n g and band models a r e p r e s e n t e d f o r
g a s e o u s r a d i a t i o n and f o r m a t i o n and s i z e s o f c a r b o n . Al,O3 p a r t i c l e s
a r e d i s c u s s e d f o r p a r t i c l e r a d i a t i o n . Numerous methods of p r e d i c t i n g
g a s and p a r t i c l e e m i s s i v i t i e s and r a d i a t i v e h e a t i n g a r e c r i t i c a l l y
r e v i e w e d and a n a l y z e d , and t h e m o s t a c c u r a t e methods c u r r e n t l y a v a i l a b l e
a r e d i s c u s s e d . Although t h e a p p l i c a t i o n of t h e g e n e r a l theory is
d i r e c t e d toward r a d i a t i o n from t h e e x h a u s t s o f t h e S a t u r n H - 1 , F-1, 5 - 2 ,
and RL-10 l i q u i d p r o p e l l a n t m o t o r s ( f o r s t a g e - s e p a r a t i o n h e a t i n g ) , t h e
�b a s i c t h e o r y a p p l i e s t o r a d i a t i o n from t h e exhaust of any l i q u i d propell a n t engine o r s o l i d p r o p e l l a n t motor.
g.
O r b i t a l Heating Analysis of t h e S-IVB Workshop
The o r b i t a l h e a t i n g a n a l y s i s of the S-IVB workshop
has been completed and a memo w r i t t e n p r e s e n t i n g t h e r e s u l t s .
Total
r a d i a t i v e h e a t r a t e d i s t r i b u t i o n s about t h e workshop a r e p r e s e n t e d f o r
175- and 259-nautical-mile o r b i t s f o r s e v e r a l p o s s i b l e o r i e n t a t i o n s
and launch d a t e s , June 2 2 and December 22.
F.
Unsteady Aerodynamics Branch
1.
I n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Environments
a . The 4 p e r c e n t S a t u r n V f l u c t u a t i n g p r e s s u r e model i s
being prepared a t Marshall f o r use i n t h e AEDC 1 6 - f o o t s u p e r s o n i c wind
t u n n e l on January 3 , 1967. The p r e s s u r e c o e f f i c i e n t s and boundary l a y e r
v e l o c i t y p r o f i l e s from the t r a n s o n i c phase of t h e t e s t a r e being p l o t t e d .
The n e c e s s a r y p r e p a r a t i o n s a t t h e Computation Laboratory a r e being made
t o a n a l y z e t h e dynamic p r e s s u r e d a t a o b t a i n e d d u r i n g t h e t r a n s o n i c phase.
b.
P r e l i m i n a r y "quick-look" e v a l u a t i o n of t h e f l u c t u a t i n g
p r e s s u r e d a t a o b t a i n e d on t h e 4 p e r c e n t model a t AEDC a r e being conConcurrent w i t h
ducted. A t t h i s time, t h e r e s u l t s a r e encouraging.
t h e d a t a e v a l u a t i o n , experiments a r e being conducted t o d e l i n e a t e d a t a
a c q u i s i t i o n system c h a r a c t e r i s t i c s .
c. A "quick-look" method f o r a s s e s s i n g t h e response of t h e
S a t u r n V s t r u c t u r e t o f l u c t u a t i n g p r e s s u r e f o r c e s has been completed.
It i s planned t o use t h e d a t a from t h e 4 p e r c e n t model t e s t a t AEDC i n
t h e s e s t r u c t u r a l response e s t i m a t i o n s , which w i l l be made by R-P&VE-S.
2.
Launch S i t e A c o u s t i c Environment
a.
The j e t impingement program i n s u p p o r t of o f f s h o r e ,
launch f a c i l i t y f e a s i b i l i t y , w i t h r e s p e c t t o a c o u s t i c energy p r o d u c t i o n ,
i s continuing.
The v e h i c l e e l e v a t i o n changes w i t h r e s p e c t t o t h e water
l e v e l i n f luence, t h e a c o u s t i c environmental c o n d i t i o n s and i s being
monitored i n t h e a r e a s c r i t i c a l t o f a c i l i t y , v e h i c l e , and f a r f i e l d .
b. The AS-202 a c o u s t i c d a t a e v a l u a t i o n has been delayed
because of problems of i n t e r p r e t i n g t h e t e l e m e t r y system s i g n a l s . More
s t u d y i s r e q u i r e d i n t h i s a r e a , depending on ~ s t r i o n i c s ' r e e v a l u a t i o n
of t h e problems. The e r r o r s a r e p o s s i b l y dependent on s i g n a l amplitude
and c e r t a i n s y s tem n o n l i n e a r i t i e s
.
�c. The a c o u s t i c r e s e a r c h model programs a t t h e T e s t
L a b o r a t o r y a r e b e i n g a c c e l e r a t e d b e c a u s e o f t h e newly a c q u i r e d m u l t i p l e x s y s t e m f o r a c o u s t i c d a t a . This s y s t e m w i l l p r o v i d e s e v e r a l phase
c o r r e l a t a b l e c h a n n e l s w i t h i n a month o r s o a f t e r t h e i n s t a l l a t i o n i s
completed i n March 1967. A phase c o r r e l a t i o n t e c h n i q u e f o r d e t e r m i n i n g
sound s o u r c e d i s t r i b u t i o n s t r e n g t h s , a s t u d y f o r e v a l u a t i n g e n g i n e b e l l
e x p a n s i o n e f f e c t s on a c o u s t i c power g e n e r a t i o n , and a n e x p e r i m e n t a l
d e t e r m i n a t i o n of t h e e f f e c t s of nozzle e x i t p r e s s u r e v a r i a t i o n a r e
among t h e p r o j e c t s o f c u r r e n t i n t e r e s t .
d . The f i n a l r e p o r t under C o n t r a c t No. NAS8-11441 e n t i t l e d
" I n v e s t i g a t i o n t o D e f i n e t h e P r o p a g a t i o n C h a r a c t e r i s t i c s of a F i n i t e
A c o u s t i c P r e s s u r e Wave ," h a s b e e n completed.
(The p r i n c i p a l i n v e s t i g a t o r i n t h i s e f f o r t was M r . A. C. P e t e r s . )
T h i s r e p o r t i s concerned
w i t h t h e c o n t r i b u t i o n o f t h e e n t r o p y - p r o d u c i n g r e g i o n s t o t h e mechanism
o f n o i s e g e n e r a t i o n i n a s u p e r s o n i c e x h a u s t flow. T h i s a n a l y s i s shows
t h a t , even though t h e e n t r o p y v a r i a t i o n f o r weak s h o c k s i s o f a t h i r d
o r d e r m a g n i t u d e , t'he e f f e c t s o f e n t r o p y p r o d u c t i o n c a n n o t b e d i s r e g a r d e d
when c o n s i d e r i n g t h e a c o u s t i c p r e s s u r e s i n c e , i n t h e g o v e r n i n g d i f f e r e n t i a l e q u a t i o n , e n t r o p y e f f e c t s a r e of a f i r s t o r d e r m a g n i t u d e
because of a n a d d i t i o n a l f a c t o r appearing i n t h e a n a l y s i s . This r e s u l t
p o i n t s f o r t h e f i r s t time t o t h e s h o c k s t r u c t u r e o f a s u p e r s o n i c e x h a u s t
as t h e main n o i s e - g e n e r a t i n g mechanisms. When v e r i f i e d , t h i s w i l l
r e s u l t i n a major c o n t r i b u t i o n t o t h e understanding of t h e n o i s e
g e n e r a t e d by s u p e r s o n i c e x h a u s t s .
e . The e n c l o s u r e f o r t h e j e t f l o w shadowgraph s t u d y h a s
b e e n c o m p l e t e d , and a d d i t i o n a l shadowgraph e x p e r i m e n t s have b e e n cond u c t e d . The r e s u l t s o f t h e s e e x p e r i m e n t s a r e b e i n g documented.
f . Task Order No. 8 f o r Baganoff ~ s s o c i a t e s ' d a t a r e d u c t i o n on t h e MSFc/~mes s e p a r a t e d f l o w e x p e r i m e n t h a s b e e n i s s u e d t o
p r o v i d e f o r n a r r o w band time c o r r e l a t i o n s on d a t a from t h r e e s t e p configurations.
Completion o f t h i s t a s k o r d e r i s e x p e c t e d i n s i x weeks.
3.
Aeroelas t i c i t y
a.
Panel F l u t t e r
The d a t a from t h e wavy-wall p a n e l f l u t t e r t e s t s cond u c t e d i n t h e ARC 2 x 2 - f o o t t r a n s o n i c wind t u n n e l h a v e b e e n r e c e i v e d
by MSFC, and f u r t h e r d a t a r e d u c t i o n w i l l b e c a r r i e d o u t i n t h e n e a r
future.
The f l u t t e r p h a s e o f t h e p a n e l f l u t t e r t e s t s f o r t h e
L i m i t a t i o n s o f t h e AEDC
S a t u r n IVB forward s k i r t h a s b e e n completed.
1 6 - f o o t t r a n s o n i c wind t u n n e l made i t i m p o s s i b l e t o a c h i e v e i n f l i g h t
�c o n d i t i o n s i n a l l c a s e s , and a c o m p r e s s i v e l o a d l i m i t , e s t a b l i s h e d by
R-P&VE, made i t i m p o s s i b l e t o o b t a i n f l u t t e r d a t a f o r t h e f u l l y b u c k l e d
condition.
However, p a n e l f l u t t e r was e n c o u n t e r e d , a s e x p e c t e d , below
f l i g h t c o n d i t i o n s . A memorandum is b e i n g p r e p a r e d (R-AERO-AU-66-105),
and r e d u c t i o n o f t h e f l u t t e r d a t a w i l l c o n t i n u e .
b.
P i t c h Damping
A new dynamic b a l a n c e s y s t e m is b e i n g d e s i g n e d f o r
u s e i n t h e MSFC 1 4 - i n c h t r i s o n i c wind t u n n e l . The new d e s i g n is meant
t o r e d u c e t h e c o u p l i n g between t h e t w i s t i n g d e f l e c t i o n caused by t h e
p i t c h i n g m o t i o n o f a n o s c i l l a t i n g model and the b e n d i n g d e f l e c t i o n
caused by a x i a l f o r c e s a p p l i e d t o t h e model which o c c u r r e d on a p r e v i o u s
p i t c h damping t e s t .
There i s ample r e a s o n t o b e l i e v e t h a t t h i s c o u p l i n g
would a l s o o c c u r on t h e proposed pitch-damping t e s t .
It may t h e r e f o r e
b e n e c e s s a r y t o d e s i g n new models c o m p a t i b l e w i t h t h e new b a l a n c e s y s t e m .
A r u n s c h e d u l e , a s c h e d u l e f o r t h e d e s i g n and c o n s t r u c t i o n of new
models ( i f n e c e s s a r y ) , and a d a t a r e d u c t i o n p r o c e d u r e w i l l s o o n b e
forthcoming
.
c.
Quas i - S t e a d y O s c i l l a t i n g Wake S t u d y
The equipment f o r t h i s t e s t was i n i t i a l l y i n s t a l l e d on
O c t o b e r 7 , 1966. The week of October 10-14 was p r i m a r i l y used i n t e s t i n g t h e wake s o u r c e equipment and mod i f y i n g v a r i o u s components t o
s a t i s f y t u n n e l r e q u i r e m e n t s . ( F r i d a y a f t e r n o o n and Monday morning
(Oct. 1 4 and 1 7 ) were used i n work f o r NASA's open h o u s e week e n d . )
A d d i t i o n a l r u n s were made t o s t u d y what e f f e c t s t h e s t r u t may have
on f l o w c o n d i t i o n s , t u n n e l b l o c k a g e , and Mach number v a r i a t i o n s , s i n c e
t h i s s t r u t must b e p l a c e d i n t h e t e s t s e c t i o n c l o s e t o t h e t e s t models.
R e s u l t i n g d a t a compared f a v o r a b l y w i t h d a t a o b t a i n e d from models p r e v i o u s l y t e s ted
.
Tunnel t i m e was l o s t q u i t e f r e q u e n t l y b e c a u s e o f
problems w i t h t h e t u n n e l c o m p r e s s o r s , t h e h i g h p r e s s u r e v a l v e , and t h e
temperature control valve.
The t e s t , which was d i s c o n t i n u e d b e c a u s e o f
o t h e r t u n n e l commitments, w i l l b e resumed a t a l a t e r d a t e .
4.
S a t u r n V Ground Winds
R e d u c t i o n o f t h e l a t e s t S a t u r n V wind t u n n e l t e s t d a t a is
continuing.
F u l l - s c a l e b a s e b e n d i n g moments f o r 2 . 0 , 3 . 1 , and 4 . 5
p e r c e n t o f c r i t i c a l damping have b e e n p r e d i c t e d and f u r n i s h e d t o
R-P&VE-S.
R-P&VE-S h a s a l s o b e e n f u r n i s h e d p r e d i c t e d f u l l - s c a l e bendi n g moments a t t h e upper v e h i c l e s t a t i o n s f o r 3.1 p e r c e n t of c r i t i c a l
damp ing
.
�VII.
DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Multi-Pro j e c t s
1.
Guidance
a.
D i r e c t A s c e n t Rendezvous
A s t u d y t o d e t e r m i n e a r e l i a b l e d i r e c t a s c e n t rendezvous
scheme a l l o w i n g t h e f l e x i b i l i t y of a l a u n c h window t h a t i s r e s t r i c t e d
o n l y by v e h i c l e performance, Van A l l e n r a d i a t i o n b e l t , and s y s t e m s l i f e T h i s t e c h n i q u e p e r m i t s rendezvous
t i m e is b e i n g p u b l i s h e d a s a NASA TM X.
w i t h a n y v e h i c l e of a known ephemeris p r o v i d e d t h e e n e r g y r e q u i r e m e n t i s
w i t h i n t h e performance c a p a b i l i t y o f t h e p u r s u i t v e h i c l e .
This approach
t o rendezvous t a k e s a d v a n t a g e of t h e unique f e a t u r e s o f t h e S a t u r n I B
and S a t u r n V g u i d a n c e s y s t e n ( i t e r a t i v e g u i d a n c e scheme) t o compensate
f o r any i n f l i g h t performance v a r i a t i o n s t h a t would r e s u l t i n a t i m i n g
e r r o r a t rendezvous by making a c u t o f f e n e r g y c o r r e c t i o n t o i n s u z e
rendezvous s o l u t i o n . A scheme a c c u r a c y o f two n a t u i c a l m i l e s a t
rendezvous a c r o s s a 30-minute l a u n c h window i s i n d i c a t e d b y s t u d y
r e s u l t s a t t h i s time.
(-DG)
b.
G e n e r a l i z e d H y p e r s u r f a c e f o r t h e S a t u r n I B and
Saturn V Missions
The problem of s t a n d a r d i z i n g t h e i n p u t c o n s t a n t s and
g u i d a n c e e q u a t i o n s t o h a n d l e t h e l u n a r o r b i t a l rendezvous m i s s i o n , as
w e l l a s a n y e a r t h - o r i e n t e d m i s s i o n w i t h t h e same l a u n c h v e h i c l e d i g i t a l
computer program, h a s been r e s o l v e d .
This f l e x i b i l i t y allows t h e miss ion
t o undergo changes w i t h o u t h a v i n g a s o f t w a r e problem p r o v i d e d t h e l a u n c h
v e h i c l e d i g i t a l computer c a n h a n d l e t h e s c a l i n g f o r t h e m i s s i o n change.
These changes w i l l b e made t o t h e AS-504 g u i d a n c e e q u a t i o n s . They a r e
a l s o t o be made i n t h e AS-209 and s u b s e q u e n t f l i g h t s . Documentation of
a " G e n e r a l i z e d H y p e r s u r f a c e f o r t h e S a t u r n I B and S a t u r n V Missions" has
b e e n r e c e i v e d from N o r t h r o p ; b u t b e f o r e d i s t r i b u t i o n w i l l b e made, o t h e r
methods and comparisons f o r s i m p l i c i t y w i l l b e s u r v e y e d t o d e t e r m i n e
which i s more e a s i l y implemented i n t o t h e S a t u r n V s y s t e m .
(~~INorthrop)
c.
P a r a m e t r i c T r u n c a t i o n of I n t e l l i g e n c e Used i n IGM
S t e e r i n g Angle Computation
The s i g n i f i c a n t d i g i t s of t h e n a v i g a t i o n a l i n f o r m a t i o n
used i n t h e IGM s t e e r i n g e q u a t i o n s , as w e l l a s t h e f u n c t i o n s used
i n t e r n a l l y by IGM, were p a r a m e t r i c a l l y t r u n c a t e d u n t i l t h e s y s t e m
became i n d e t e r m i n a t e , o r performance and a c c u r a c y were s i g n i f i c a n t l y
penalized.
The m i s s i o n s s i m u l a t e d a r e as f o l l o w s :
�(3)
S a t u r n V t o a c i r c u l a r o r b i t a t 100 NM,
(4)
S a t u r n V t o a c i r c u l a r o r b i t a t 300 NM,
(5)
S a t u r n V t o a c i r c u l a r o r b i t a t 400 NM,
(6)
S a t u r n V t o a c i r c u l a r o r b i t a t 500 NM,
(7)
LOR parking o r b i t t o t r a n s l u n a r i n j e c t i o n ,
(8)
S a t u r n V t o a n 80 NM p e r i g e e through c o a s t
t o synchronous o r b i t a l t i t u d e ,
(9)
S a t u r n V Venus probe.
The d a t a have been c o l l e c t e d f o r a r e p o r t , which w i l l g i v e some i n s i g h t
i n t o t h e number of s i g n i f i c a n t d i g i t s r e q u i r e d f o r IGM t o perform i n
a s a t i s f a c t o r y manner and which w i l l i n d i c a t e how much t h e m i s s i o n can
be changed w i t h o u t needing t o r e s c a l e t h e f i x e d p o i n t launch v e h i c l e
(DG/Northrop)
d i g i t a l computer.
d.
Thrust F i l t e r i n g f o r IGM
A s t u d y has been undertaken t o determine i f a t h r u s t
f i l t e r would perform b e t t e r t h a n t h e p r e s e n t l y implemented M / F (mass
over t h r u s t ) f i l t e r . S i n c e t h r u s t i s supposedly a c o n s t a n t v a l u e i n
t h e upper s t a g e s of S a t u r n I B and S a t u r n V v e h i c l e s , e x c e p t f o r t h e
t r a n s i t p e r i o d d u r i n g p r o p e l l a n t mixture s h i f t , i t seems r e a s o n a b l e t o
assume t h a t a c o n s t a n t v a l u e would be more e a s i l y f i l t e r e d t h a n a s l o p e
s u c h a s M/F. The raw v a l u e of t h r u s t (F) i s computed by assuming t h a t
flow r a t e (fi) i s c o n s t a n t . The measured F/M is t h e n m u l t i p l i e d by t h e
c a l c u l a t e d mass t o g i v e a raw F v a l u e t o be f i l t e r e d by a d i g i t a l f i l t e r .
The F f i l t e r has been analyzed on t h e reduced AS-201 d a t a and a comparison made t o t h e M / F f i l t e r . The F f i l t e r w i l l a l s o be a p p l i e d t o t h e
AS-501 second S-IVB burn period and compared t o t h e M / F f i l t e r . Docu(DG/~orthrop)
m e n t a t i o n i s expected by mid-December.
2.
Dynamics and Control
A method has been developed f o r f i n d i n g t h e n a t u r a l f r e The
quencies and mode shapes of a v e h i c l e w i t h suspended masses.
v e h i c l e i s i d e a l i z e d a s a system of one beam and up t o t e n suspended
masses. A v i b r a t i o n a n a l y s i s i s f i r s t made of t h e beam, o m i t t i n g t h e
masses, by a modified S t o d o l a method. The e q u a t i o n s f o r t h e connected
�system a r e t h e n d e r i v e d u s i n g Lagrange's e q u a t i o n . These e q u a t i o n s
have been programmed f o r the I B M 7090 by t h e Computation Laboratory.
This program i s b e i n g used t o s t u d y t h e e f f e c t of t h e f l e x i b i l i t y of
(DDS)
t h e LEM on t h e bending c h a r a c t e r i s t i c s of a v e h i c l e .
B.
Saturn V
1.
Mission P r o f i l e
Nonlinear Accelerometer Feedback f o r S a t u r n V w i t h
F l e x i b l e Dynamics
a.
A previous s t u d y (Ref: TM-54130-7 2 , LMSCIHRECA71 2744,
Nonlinear Accelerometer Feedback f o r Load R e l i e f , " December 1965) has
i n d i c a t e d t h a t t h e bending moment may b e reduced a p p r e c i a b l y d u r i n g t h e
b o o s t f l i g h t of t h e S a t u r n V v e h i c l e by means of a l i m i t e d a c c e l e r o m e t e r
feedback and a p p r o p r i a t e g a i n s c h e d u l e s . This previous s t u d y d i d not
i n c l u d e t h e f l e x i b l e body e f f e c t s introduced by bending and s l o s h modes.
During t h e p r e s e n t s t u d y , t h e same load r e d u c t i o n approach was extended
t o i n c l u d e bending modes, f u e l s l o s h i n g , s t a b i l i z i n g f i l t e r s , and engine
a c t u a t o r dynamics i n a n analog s i m u l a t i o n of t h e S a t u r n V.
II
The s t u d y r e s u l t s documented i n TM-54130-111, LMSC/
HREC A783386, "Nonlinear Accelerometer Load R e l i e f F l e x i b l e Body Study,"
October 1966, i n d i c a t e t h a t , w i t h minor system m o d i f i c a t i o n s , bending
moment r e d u c t i o n s of t h e same o r d e r of magnitude a s t h o s e i n t h e r i g i d
body system may b e obtained. Under a t t i t u d e and a t t i t u d e r a t e c o n t r o l ,
t h e f l e x i b l e body system y i e l d s a bending moment of 31.0 x l o 7 i n - l b
f o r t h e 70 second wind, w h i l e t h e load r e l i e f g a i n s w i t h n o n l i n e a r
a c c e l e r o m e t e r feedback produce a moment of 13.0 x l o 7 i n - l b , a reduct i o n of 58 p e r c e n t .
These bending moment v a l u e s a r e taken from timev a r y i n g t r a j e c t o r y s i m u l a t i o n s . Although t h e maximum v a l u e s occurred
f o r t h e 70 second wind peak, s i m i l a r r e d u c t i o n s were i n d i c a t e d f o r
o t h e r time p o i n t s .
However, s e v e r a l a d d i t i o n a l f a c t o r s should be cons i d e r e d b e f o r e a d e f i n i t e s t a t e m e n t can be made on t h e f e a s i b i l i t y of
using t h e system i n a n a c t u a l launch v e h i c l e . For example, t h e bending
moments were recorded a t only one s t a t i o n where t h e bending moment coeff i c i e n t s peak, b u t n o t n e c e s s a r i l y where t h e v e h i c l e s t r u c t u r a l l i m i t
i s most c r i t i c a l . The bending moment c o n t r i b u t i o n from t h e f l e x i b l e
modes was n o t c o n s i d e r e d , a f a c t o r which could be s i g n i f i c a n t a t s t a t i o n s
n e a r t h e v e h i c l e nose. F i n a l l y , a more thorough i n v e s t i g a t i o n of t h e
p o s s i b l e winds t h a t could be encountered i s n e c e s s a r y , s i n c e a l a r g e
shear reversal
which i s conceivable
could produce l a r g e r moments
(DcA/
f o r t h e load r e l i e f system than f o r a n a t t i t u d e c o n t r o l system.
Lockheed)
-
-
�2.
Guidance
S a t u r n V Manual Guidance Backup
The Boeing Company hybrid computer has been s e l e c t e d
t o determine t h e f e a s i b i l i t y of manual guidance take-over d u r i n g t h e
S - I 1 and S-IVB s t a g e s of t h e S a t u r n V v e h i c l e f l i g h t i n t o e a r t h parking
o r b i t and a n a l y z e t h e M I T s y s tem f o r takeover d u r i n g t h e e a r t h parking
o r b i t and t r a n s l u n a r i n j e c t i o n power f l i g h t . A l l of t h e o r i g i n a l e f f o r t
w i l l be placed on t h e AS-503 mission.
A ground r u l e was e s t a b l i s h e d w i t h MSC t h a t manual
guidance takeover would be ac6.&nplished i n such a f a s h i o n t h a t no s t e e r ing command d i s c o n t i n u i t i e s would e x i s t , and t h e r e f o r e , no t r a n s i t
problemwould e x i s t .
(DG)
3.
Dynamics and Control
a.
S t a b i l i t y A n a l y s i s , SA-501
A s t a b i l i t y a n a l y s i s has been completed on SA-501
:
r e f l e c t i n g t h e changes caused by t h e use of o p e r a t i o n a l t r a j e c t o r y w i t h
new t o l e r a n c e s , updated aerodynamics d a t a and t o l e r a n c e s , updated s l o s h
damping, and updated bending and s l o s h model t o l e r a n c e s .
The r e s u l t s
of t h e a n a l y s i s a r e a s follows:
(1) The S-IC p i t c h c o n t r o l system aerodynamic margin
was reduced from 4.9 db t o 3.7 db d u r i n g maximum dynamic p r e s s u r e .
This d i f f e r e n c e i s caused by a change i n aerodynamic d a t a . This v a l u e
degrades t o 2.4 db under 30 c o n d i t i o n s .
( 2 ) The p e r i o d i n which v e h i c l e f a i l u r e occurs a s a
r e s u l t of a n S-IC engine o u t has i n c r e a s e d by approximately 10 seconds,
This c o n d i t i o n i s a s s o c i a t e d w i t h f a i l u r e s of i/1 and i/4 engines d u r i n g
t h e 60- t o 90-second f l i g h t p e r i o d . This change i s a l s o due t o t h e
updated aerodynamic d a t a .
(3) The S-IC p i t c h c o n t r o l system g a i n margin was
reduced from 4.8 db t o 5.2 db under r e f e r e n c e c o n d i t i o n s and t h e s l o s h
peak g a i n margin has changed from -3.6 db t o -1.25 db under 30 c o n d i t i o n s .
(DDD/
These changes a r e due t o new s l o s h damping v a l u e s and t o l e r a n c e s .
Boe i n g )
�b.
Saturn V
-
Umbilical Tower Analysis
A program i s being developed t o c a l c u l a t e t h e damped
modes of a c o m p l e x ~ s t r u c t u r a lsystem w i t h lumped damping. The f i r s t
a p p l i c a t i o n w i l l be a n a l y s i s of the S a t u r n V-Launcher combination.
This s t r u c t u r e has a damping mechanism between t h e v e h i c l e and u m b i l i c a l
tower t o provide damping and t h u s reduce t h e amplitude of wind-induced
o s c i l l a t i o n s . The program has been checked o u t f o r a simple t e s t
problem. Generation of t h e u m b i l i c a l tower mass and s t i f f n e s s d a t a i s ,
expected t o t a k e a b o u t t h r e e months.
(DDS/~ockheed)
c.
Dynamic Analysis of t h e S e r p e n t u a t o r
The dynamic a n a l y s e s of t h e f i v e - l i n k S e r p e n t u a t o r has
been completed. These S e r p e n t u a t o r l i n k s a r e t h r e e f e e t long and f o u r
inches i n d i a m e t e r . A s t r o n a u t p o s i t i o n c o n t r o l i s maintained by e l e c t r o mechanical motors sequenced a t each h i n g e . Dynamic l o a d s caused by
s t e p p i n g one motor and c u t t i n g o f f t h e motor a t preceding hinge (sequenci n g ) have been computed. This dynamic c o n d i t i o n c r e a t e s h i g h t r a n s i e n t
loads and d e s i g n s t h e motor-gear t r a i n c h a r a c t e r i s t i c s . Astro-Space,
I n c . , i s completing assembly of t h i h f i v e - l i n k S e r p e n t u a t o r , which w i l l
be a v a i l a b l e f o r dynamic t e s t i n g n e x t month.
(DD)
d.
AS-504 S l o s h i n g
An a t t e m p t was made t o a n a l y t i c a l l y determine t h e
damping r a t i o which might b e expected when t h e f r e e f l u i d s u r f a c e l i e s
w i t h i n t h e upper bulkhead of the S-IC f u e l tank.
This method cons i d e r e d t h e d e c r e a s i n g r a d i u s w i t h i n t h e bulkhead t o be analogous t o
t h e i n t r o d u c t i o n of r i n g b a f f l e s of i n c r e a s i n g width.
This approach
l e f t much t o be d e s i r e d .
A survey of t h e l i t e r a t u r e has shown t h a t t h e damping
r a t i o s f o r t h i s tank geometry can b e s t be o b t a i n e d by experimental
methods.
Data have been compiled f o r a h e m i s p h e r i c a l l y domed t a n k w i t h
and w i t h o u t a r i n g b a f f l e . Although t h e S-IC f u e l tank has a n e l l i p s o i d a l
dome, t h e d a t a should g i v e good comparison between t h e two t a n k s .
Results
w i l l be published n e x t month.
(DDD)
4.
P r o j e c t Information A p p l i c a b l e t o Many Vehicles
a.
S a t u r n V Current Performance
S a t u r n V c u r r e n t performance based on November 1966
c u r r e n t weight and v e h i c l e performance d a t a was computed and t r a n s m i t t e d
t o I n d u s t r i a l O p e r a t i o n s . S i g n i f i c a n t payload d e c r e a s e s were o b t a i n e d
due p r i m a r i l y t o l a r g e i n c r e a s e s i n p r o p e l l a n t r e s i d u a l s .
(~AP/Boeing)
�b.
been concluded.
(DAP/BO
ing
~)
5.
LOR Performance Reserves
The f l i g h t performance r e s e r v e and f u e l b i a s s t u d y has
F i n a l documentation w i l l be r e l e a s e d i n December.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
A e r o e l a s t i c Analysis of S a t u r n V
An a e r o e l a s t i c a n a l y s i s i s being performed on t h e
S a t u r n V t o determine t h e e f f e c t of v e h i c l e e l a s t i c i t y on f l i g h t l o a d s .
I n t h e p a s t , f l e x i b i l i t y has been l i m i t e d t o i n c l u s i o n of t h e v e h i c l e ' s
bending modes.
This accounts f o r bending mode coupling of t h e c o n t r o l
s e n s o r s . The a e r o e l a s t i c a n a l y s i s e v a l u a t e s t h e aerodynamic l o a d i n g
which i s induced by t h e d e f l e c t e d v e h i c l e shape. E a r l y i n d i c a t i o n s
a r e t h a t t h i s l o a d growth o r s t a t i c a e r o e l a s t i c i t y i s a p p r e c i a b l e
(10 p e r c e n t of t o t a l aerodynamic load f o r h i g h l o a d i n g c o n d i t i o n , and
a c o n s i d e r a b l y h i g h e r percentage i n terms of l o c a l bending moment).
b.
503 Dynamic Analysis
The f i n a l r e s u l t s of t h e dynamic a n a l y s i s of 503 using
t h e new n o n l i n e a r aerodynamics have been delayed f o r two weeks. This
r e p o r t should be r e c e i v e d by t h e middle of December. P r e s e n t r e s u l t s
show no engine-out c a p a b i l i t y f o r z e r o wind between approximately 60
and 80 seconds f l i g h t time.
(DDD)
C.
SaturnIB
1.
Guidance
a.
S-IVB Stage Guidance t o Fuel D e p l e t i o n f o r t h e
S a t u r n I B Vehicle
The e f f e c t s of going t o f u e l d e p l e t i o n f o r t h e AS-209
m i s s i o n have been s t u d i e d ; r e s u l t s show t h i s t o be u n f e a s i b l e e i t h e r
from s o f t w a r e impact o r from accuracy r e q u i r e m e n t s . The following
methods were i n v e s t i g a t e d :
(1) The t r a j e c t o r y can be shaped t o a t t a i n o r b i t w i t h
f u e l d e p l e t i o n based on t h e p r e d i c t e d performance of t h e v e h i c l e . This
r e q u i r e s a r e g e n e r a t i o n of t h e f i r s t s t a g e t i l t polynomial and i s a
s o f tware impact. This method cannot t a k e i n t o a c c o u n t t h e i n f l i g h t performance of t h e S-IB s t a g e and t h e S-IVB s t a g e .
�(2) A performance i n d i c a t o r a t S-IB s t a g e c u t o f f t o
a s s e s s t h e performance of t h e S-IB s t a g e and then t o change t e r m i n a l
c o n d i t i o n s t o account f o r S-IB s t a g e performance d e v i a t i o n s can be used;
however, t h i s r e q u i r e s s u b s t a n t i a l a d d i t i o n a l programming i n t h e onboard
computer and i s a major s o f t w a r e impact. The performance of d e v i a t i o n s i n
t h e S-IVB s t a g e i s n o t taken i n t o account.
S i n c e AS-209 (unmanned workshop) i s a rendezvous miss i o n , t h e a c c u r a c y requirements a r e v e r y s t r i n g e n t .
I f , f o r t h e nominal
m i s s i o n of 80 n. m i . by 175 n. m i . , t h e v e h i c l e burns t o f u e l d e p l e t i o n
i n c l u d i n g 1 , 5 0 0 l b 30 f l i g h t performance r e s e r v e , t h e apogee of the o r b i t
I f t h e v e h i c l e should have 30 h i g h peri s i n c r e a s e d t o 354.4 n. m i .
formance i n each s t a g e and burns t o f u e l d e p l e t i o n , t h e apogee i s r a i s e d
These wide d i s p e r s i o n s i n o r b i t a r e unacceptable f o r a
t o 492 n. m i .
rendezvous miss ion.
The conclusion was t h a t burning t o f u e l d e p l e t i o n r a t h e r
t h a n a v e l o c i t y c u t o f f i s u n f e a s i b l e f o r AS-209.
(~G/Northrop)
b.
S a t u r n I B AS-208 D i s p e r s i o n Analysis
The f i n a l s e t of p a r t i a l d e r i v a t i v e s f o r performance
and n a v i g a t i o n e r r o r s have been d e l i v e r e d t o MSC, a s r e q u i r e d , through
t h e Guidance and Performance Subpanel, based on t h e AS-208 r e f e r e n c e
trajectory.
(DG)
2.
Dynamics and Control
SA-203 Low G r a v i t y S l o s h R e s u l t s : A r e p o r t e n t i t l e d "An
Experimental I n v e s t i g a t i o n of Large Booster P r o p e l l a n t Dynamics i n
Orbit'' has been prepared and i s being reviewed. This r e p o r t w i l l p r e s e n t t h e low g r a v i t y s l o s h i n g d a t a o b t a i n e d from t h e AS-203 f l i g h t .
These d a t a showed t h a t t h e s l o s h b a f f l e and d e f l e c t o r prevented l a r g e
amplitude p r o p e l l a n t motion a f t e r i n j e c t i o n and t h a t t h e p r o p e l l a n t
s l o s h i n g d u r i n g o r b i t was n o t e x c e s s i v e .
(DD)
3.
P r o j e c t Information A p p l i c a b l e t o Many Vehicles
November Current Performance: Current performance was
c a l c u l a t e d and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . Payload c a p a b i l i t i e s
of v e h i c l e s AS-206 through AS-208 r e f l e c t a 55, 39, and 42 pound reduct i o n , r e s p e c t i v e l y , when compared t o l a s t month's performance.
These
(~AP/Chrysler)
payload d e c r e a s e s were due t o d r y weight i n c r e a s e s .
�4.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
AS-204 Second Fl. i g h t S t a g e S t a b i l i t y Analysis
The r e s u l t s of t h e second f l i g h t s t a g e s t a b i l i t y
a n a l y s i s v e r i f i e d t h a t a l l modes a r e s t a b l e f o r the time p o i n t s chosen
e x c e p t t h e LH2 s l o s h mode d u r i n g e a r l y p o r t i o n s of second-stage f l i g h t .
This mode was u n s t a b l e a t 20 seconds of second-stage f l i g h t and s t a b l e
a t 120 seconds of f l i g h t ; no f l i g h t times between t h e s e two were
i n v e s t i g a t e d . Because of t h e s m a l l s l o s h mass and t h e r e l a t i v e l y long
time r e q u i r e d t o double t h e amplitude of t h e i n s t a b i l i t y , a c o r r e c t i o n
(~Cl~ockheed)
was not considered necessary.
b.
AS-206 Nose Cone S e p a r a t i o n f o r Abort
This s t u d y has determined t h a t a s p r i n g s e p a r a t i o n
system s i z e d t o g i v e a s e p a r a t i o n v e l o c i t y of seven f e e t per second
f o r a normal s e p a r a t i o n ( n e g l i g i b l e dynamic p r e s s u r e ) w i l l a l l o w t h e
nose, cone t o be r e l e a s e d f o r a n a b o r t s i t u a t i o n t o permit launch of t h e
LEM a s e a r l y a s 186 seconds a f t e r l i f t - o f f (approximately 40 seconds of
second s t a g e f l i g h t and corresponding t o a dynamic p r e s s u r e of roughly
one pound per s q u a r e f o o t ) w i t h l i t t l e p r o b a b i l i t y of r e c o n t a c t w i t h
t h e S-IVB/LEM combination. No motion of t h e LEM s e p a r a t i o n from t h e
S-IVB has been considered f o r t h i s s t u d y . F u l l t h r u s t decay b e f o r e
i n i t i a t i o n of a b o r t was assumed. A memorandum d e s c r i b i n g t h e s t u d y i s
being i s s u e d .
(DC)
c.
AS-206 Control Responses
An a n a l y s i s t o determine t h e maximum expected response
envelopes a p p l i c a b l e f o r t h e AS-206 and AS-208 v e h i c l e s u s i n g d r i f t
minimum a n g l e - o f - a t t a c k c o n t r o l during f i r s t s t a g e f l i g h t has been
completed. The r e s u l t s of t h i s s t u d y have been documented i n Memo No.
R-AERO-DCC-18-66.
Vehicle responses were a l s o determined a t s e l e c t e d
f l i g h t times i n t h e maximum dynamic p r e s s u r e r e g i o n u s i n g t h e c o n t r o l
system s p e c i f i e d f o r t h e AS-206 v e h i c l e by R-ASTR-F.
For some f l i g h t
t i m e s , gimbal a n g l e requirements u s i n g a c c e l e r o m e t e r feedback exceeded
t h o s e f o r a n g l e of a t t a c k c o n t r o l .
However, t h e i n c r e a s e (6.3 t o 6.9
d e g r e e s a t maximum p) i s n o t enough t o p r e s e n t a c o n t r o l l a b i l i t y problem
f o r a nonmalfunctioned v e h i c l e even when s u b j e c t e d t o t h e 95 p e r c e n t i l e
d e s i g n winds.
Because of t h e i n c r e a s e d computer time r e q u i r e d , i t i s
n o t considered t o be c o s t e f f e c t i v e t o determine t h e response envelopes
d u r i n g complete f i r s t s t a g e f l i g h t using t h e s p e c i f i e d c o n t r o l system
u n t i l t h e v e h i c l e d a t a become more r e f i n e d .
�A s t u d y t o update c o n t r o l responses f o r u s e i n a n a l y s i s
of l o a d s i s t e m p o r a r i l y h a l t e d u n t i l r e c e i p t of r e v i s e d aerodynamic
d i s t r i b u t i o n s f ram R-AERO-AD.
(DC)
Based on t h e Launch Vehicle Reference T r a j e c t o r y documented i n C h r y s l e r Report TN-AP-66-85, and upon r e c e i p t of updated
three-sigma t o l e r a n c e s r e c e i v e d from MSFC, t h e launch v e h i c l e performance
a n a l y s i s and guidance e r r o r a n a l y s i s a r e c o n t i n u i n g . A l l r e q u i r e d S-IB
s t a g e engine-out d a t a have been r e c e i v e d , and t h e p r e l i m i n a r y a b o r t and
a 1 t e r n a t e miss i o n s t u d i e s have begun.
(DA)
D.
S a t u r n Apollo A p p l i c a t i o n Program
1.
Able
a . A s t u d y has been completed t o determine t h e minimum
t o t a l v e l o c i t y increment r e q u i r e d t o t r a n s f e r from a 100 NM c i r c u l a r
o r b i t w i t h a n i n c l i n a t i o n of 28.5 degrees t o a 6,000 NM c i r c u l a r equat o r i a l o r b i t . An impulsive Hohmann t r a n s f e r technique was used w i t h t h e
t o t a l plane change d i s t r i b u t e d between t h e p e r i g e e and apogee burn.
The
minimum t o t a l v e l o c i t y increment was found t o occur w i t h a f i r s t p l a n e
change of 4.34 d e g r e e s , w i t h t h e remaining 24.15 degrees made wFth t h e
apogee burn.
The t o t a l v e l o c i t y increment was found t o be 3,852 meters
p e r second. The s t u d y was made a s a n i n p u t i n t o a S a t u r n V performance
c a p a b i l i t y e s t i m a t e f o r P r o j e c t Able.
(DAO)
b.
The f i n a l c o n t r a c t o r p r e s e n t a t i o n s on P r o j e c t Able were
It was noted t h a t Goodyear Aerospace Corporation was unable
attended.
t o f i n d s t a b l e o r b i t s f o r t h e c a s e of a one-sided r e f l e c t o r .
This d i s crepancy has been r e s o l v e d i n a s p l i n t e r meeting w i t h t h e c o n t r a c t o r .
It was concluded t h a t , w i t h a s l i g h t l y more r e a l i s t i c s i m u l a t i o n , s t a b l e
(DAO)
o r b i t s could be found f o r t h i s c a s e .
c.
Pressure Perturbations
A paper on s o l a r p r e s s u r e p e r t u r b a t i o n s w r i t t e n by
M r . S c o t t P e r r i n e was accepted f o r p r e s e n t a t i o n a t t h e American A s t r o n a u t i c a l S o c i e t y S o u t h e a s t Regional S e c t i o n Symposium, December 5 - 7 ,
h e l d i n H u n t s v i l l e , Alabama.
S t a b l e o r b i t parameters were g e n e r a t e d
f o r m i r r o r s of .03 and .06 pounds p e r s q u a r e f o o t weight t o r a t i o f o r
o r b i t a l p e r i o d s of 6, 12, and 24 hours.
The r e s u l t s were included i n
a p r e s e n t a t i o n by M r . C a r t e r , R-ASO, t o t h e Department of Defense.
(DAO)
�2.
ATM
a.
AIM-Solar E c l i p s e O b s e r v a t i o n
An e l l i p t i c a l o r b i t h a s b e e n d e t e r m i n e d f o r t h e ATM
which y i e l d s a maximum time of a b o u t 4 . 5 h o u r s d u r i n g w h i c h t h e ATM i s
i n t h e umbra of t h e moon.
P l a n e changes and v e l o c i t y changes t h a t
w i l l be r e q u i r e d t o i n s e r t t h e ATM i n t o t h i s o r b i t u n d e r t h e p r e s e n t l y
(DAO)
known v e h i c l e c o n s t r a i n t s a r e b e i n g c o n s i d e r e d .
ATM 3-D S i m u l a t i o n
b.
A s t u d y of t h e e f f e c t s of e n v i r o n m e n t f o r c e s and
t o r q u e s on t h e A'IIM was begun. A 3-D computer s i m u l a t i o n i n c l u d i n g
g r a v i t y g r a d i e n t t o r q u e s and a e r o d y n a m i c f o r c e s i s p l a n n e d . A p r e l i m i n a r y b l o c k d i a g r a m o f t h e E u l e r i a n e q u a t i o n s o f m o t i o n and t h e
Work i s b e i n g
r e q u i r e d o r t h o g o n a l t r a n s f o r m a t i o n s h a s b e e n completed
done on a 1 t e r n a t e methods of t r a n s f o r m i n g and s imp1 i f y i n g a l l e q u a t i o n s
for ease i n simulation.
(DCA)
.
The d i g i t a l program t o c a l c u l a t e t h e a n g u l a r a t t i t u d e
This
of a n o r b i t i n g s p a c e s t a t i o n s u c h a s t h e ATM h a s b e e n c o m p l e t e d .
program assumes a r i g i d v e h i c l e s u b j e c t e d t o g r a v i t a t i o n a l and a e r o dynamic t o r q u e s e n c o u n t e r e d i n a c i r c u l a r o r b i t . The a t t i t u d e i s g i v e n
by t h e d i r e c t i o n c o s i n e s o f t h e p r i n c i p a l a x i s of t h e v e h i c l e r e l a t i v e
t o s p a c e - f i x e d c o o r d i n a t e s y s t e m . The a n g u l a r v e l o c i t y from w h i c h t h e
d i r e c t i o n c o s i n e s a r e c a l c u l a t e d i s o b t a i n e d f r o m ~ u l e r ' se q u a t i o n s
w h i c h d e s c r i b e t h e r o t a t i o n a l dynamics.
One sample problem f o r which
t h e s o l u t i o n i s known was a n a l y z e d u s i n g t h e d i g i t a l program, and a
r e s u l t i n g a m p l i t u d e was found t o b e i n a g r e e m e n t t o w i t h i n 3 p e r c e n t
f o r a small o s c i l l a t i o n about an equilibrium point.
The p e r i o d of
3 1 , 5 0 0 . s e c o n d s was a b o u t 1 . 5 p e r c e n t i n e r r o r .
(DC)
c.
Work S t a t e m e n t f o r ATM T i m e l i n e A n a l y s i s and R e s o u r c e
Requirements
Lockheed h a s b e e n d i r e c t e d t o work w i t h R-AERO-D i n
e s t a b l i s h i n g m i s s i o n t i m e l i n e and r e s o u r c e r e q u i r e m e n t s f o r i n c o r p o r a t i o n i n t h e ATM D e s i g n R e f e r e n c e M i s s i o n Document.
To e n s u r e a g r e e m e n t
on m i s s i o n d e f i n i t i o n , we w i l l r e v i e w and r e v i s e t h e e x i s t i n g Lockheed
ATM ephemera, a c t i v i t y , and r e s o u r c e d e f i n i t i o n s . A f t e r t h i s r e v i e w ,
a work s t a t e m e n t w i l l b e e s t a b l i s h e d .
(DAM)
d
.
Combined ~ o r k s h o p / A T M
A b r i e f s t u d y was made t o d e t e r m i n e t h e s e p a r a t i o n
d i s t a n c e h i s t o r y between t h e S-IVB o r b i t a l workshop and ATM due t o d i f The workshop and ATM
f e r e n t i a l d r a g d e c e l e r a t i o n s and o r b i t a l p l a n e s .
�were i n s e r t e d i n t o e l l i p t i c a l o r b i t s w i t h v e r y s m a l l e c c e n t r i c i t i e s .
Along t h e m a j o r a x i s , t h e o r b i t s were s e p a r a t e d by 30 m e t e r s . The
o r b i t s had a s l i g h t l y d i f f e r e n t i n c l i n a t i o n s u c h t h a t t h e maximum
l a t e r a l (normal t o t h e o r b i t p l a n e ) s e p a r a t i o n was 30 m e t e r s . Because
of t h e d i f f e r e n c e i n d r a g between t h e ATM and workshop, t h e s e b o d i e s
become p e r t u r b e d from t h e i r o r i g i n a l o r b i t s .
The l o n g i t u d i n a l , l a t e r a l ,
and a l t i t u d e s e p a r a t i o n d i s t a n c e s and r e q u i r e d t e t h e r l e n g t h ( s l a n t
r a n g e ) were computed f o r two h o u r s .
It was e x p e c t e d t h a t s t a t i o n k e e p i n g would be performed once p e r o r b i t w h i l e t h e b o d i e s were i n t h e
e a r t h ' s shadow. F u r t h e r s t u d y h a s b e e n i n i t i a t e d t o d e t e r m i n e t h e
f e a s i b i l i t y of u s i n g t h e t e t h e r between t h e ATM and S-IVB workshop a s
a station-keeping device.
The r e q u i r e m e n t s a r e t o r e s t r i c t t h e s e p a r a t i o n of t h e ATM by u s i n g a r e e l i n g d e v i c e on t h e t e t h e r between t h e two
b o d i e s when t h e y a r e on t h e n i g h t - s i d e o f t h e e a r t h and l e t t i n g them
d r i f t d u r i n g o b s e r v a t i o n of t h e s u n . The f i r s t a p p r o a c h t a k e n was t o
compute t h e t e t h e r f o r c e s r e q u i r e d t o i n c r e a s e t h e e n e r g y of t h e ATM
o r b i t a s s u m i n g t h e S-LVB workshop t o b e o f i n f i n i t e m a s s .
It was found
t h a t e n e r g y o f t h e ATM c o u l d be i n c r e a s e d b y t h e S-IVB a p p l y i n g a n
i m p u l s e t h r o u g h t h e c a b l e . T h i s i m p u l s e can b e a p p l i e d a n y t i m e d u r i n g
a 19-minute p e r i o d on t h e d a r k s i d e o f t h e o r b i t when t h e S-IVB l e a d s
t h e ATM.
The AV r e q u i r e d i s between 0 . 3 and 2 . 2 m e t e r s p e r s e c o n d .
The r e s u l t i n g e l l i p s e h a s i n c r e a s e d e n e r g y and momentum, b u t t h e m a j o r
a x i s i s r o t a t e d . An i n v e s t i g a t i o n t o f i n d t h e p r o p e r p o s i t i o n on t h e
r e s u l t i n g e l l i p s e t o r o t a t e t h e major a x i s back i n t o t h e e a r t h - s u n l i n e
i s underway.
(DA)
The c o n c e p t o f s t a t i o n - k e e p i n g by u s e o f a s o f t t e t h e r
between t h e Workshop and ATM is b e i n g i n v e s t i g a t e d .
The problem i s
b e i n g a p p r o a c h e d by s e e k i n g a s e t of i n i t i a l c o n d i t i o n s s u c h t h a t a t u g
on t h e t e t h e r w i l l i n t r o d u c e p e r t u r b a t i o n s t o t h e o r b i t j u s t o p p o s i t e t o
t h o s e o f a t m o s p h e r i c d r a g . The e f f e c t o f b o t h t h e m a g n i t u d e and d i r e c t i o n of t h e t u g on t h e p e r i o d and e c c e n t r i c i t y o f t h e r e s u l t i n g o r b i t
i s b e i n g p a r a m e t e r i z e d o v e r t h e i n i t i a l o r i e n t a t i o n s o f t h e two o r b i t s
a n d t h e p o s i t i o n s a t which t h e t u g s o c c u r . A computer r o u t i n e w r i t t e n
f o r t h i s p r o b l e m h a s been f o r m u l a t e d , coded, and checked o u t .
The
f i r s t r e s u l t s a r e being analyzed.
(DAO)
3.
Synchronous O r b i t
a . A p r e l i m i n a r y working p a p e r t y p e m i s s i o n a n a l y s i s and
g r o s s t i m e l i n e have b e e n g i v e n t o t h e r e p r e s e n t a t i v e s o f t h e p r i n c i p a l
i n v e s t i g a t o r s f o r r e v i e w and comment. The a n a l y s i s and t i m e l i n e cont i n u e t o b e r e f i n e d a s more i n f o r m a t i o n i s a s s e m b l e d and new e x p e r i m e n t s
a r e cons i d e r e d
A t p r e s e n t , o n l y t h e p r i m a r y e x p e r i m e n t s ( t h o s e which
r e q u i r e o r p r e f e r a synchronous o r b i t ) a r e being c o n s i d e r e d . P l a n s a r e
t o s e l e c t a c o m p a t i b l e s e t of p r i m a r y e x p e r i m e n t s , t h e n t h r o u g h f u r t h e r
m i s s i o n a n a l y s i s , c h o o s e a s e t o f s e c o n d a r y e x p e r i m e n t s t o f i l l any
t i m e and r e s o u r c e s u r p l u s . A l t h o u g h t h e a n a l y s i s i s now b e i n g done by
hand f o r q u i c k - l o o k i t e r a t i o n , ~ o c k h e e d ' s t i m e l i n e program now b e i n g s e t
(DAM)
up w i l l be used f o r t h e f i n a l i t e r a t i o n s .
.
�b.
The u l t r a v i o l e t e x p e r i m e n t h a s b e e n dropped from t h e
l i s t of c a n d i d a t e e x p e r i m e n t s and r e p l a c e d w i t h a number o f OSSA-proposed
candidates.
Data a r e s t i l l l a c k i n g on t h e s e e x p e r i m e n t s . Another g r o s s
t i m e l i n e w i l l b e g e n e r a t e d a s t h i s i n f o r m a t i o n becomes a v a i l a b l e .
(DAM)
4.
Thermo
a.
P r o j e c t Thermo
An e f f o r t i s b e i n g expended on a p r o j e c t proposed by
P&VE L a b o r a t o r y c a l l e d "Thermo," which i n v o l v e s t h e performance of
f l u i d mechanics and h e a t t r a n s f e r e x p e r i m e n t s under c o n t r o l l e d low g
c o n d i t i o n s i n o r b i t . The p r o j e c t i s b e i n g c o n s i d e r e d a s a p a r t o f t h e
combined S-IVB workshop/ATM c o n c e p t of D r . M u e l l e r . Thermo would cons i s t o f a CSM, LM, RACK, and Thermo e x p e r i m e n t package b e i n g b r o u g h t up
on some v e h i c l e l a t e r t h a n 212.
The v e h i c l e w i t h t h e Thermo e x p e r i m e n t s
would i n i t i a l l y dock w i t h t h e S-IVB workshop i n a 260 NM c i r c u l a r o r b i t .
The Thermo e x p e r i m e n t r e q u i r e s m a i n t a i n i n g a c c e l e r a t i o n l e v e l s of lo-",
lo-.', and 10'" g ' s , which a r e r e q u i r e d f o r p e r f o r m i n g t h e e x p e r i m e n t s .
The method c o n s i d e r e d i n t h i s s t u d y t o a c c o m p l i s h t h e s e a c c e l e r a t i o n
l e v e l s i s f o r t h e ~ ~ / R A c ~ / ~ h et romcoa s e o f f from t h e S-IVB workshop
and t h r u s t normal t o t h e o r b i t a l p l a n e . T h i s method r e s u l t s i n a
r e s t o r a t i o n of t h e o r i g i n a l o r b i t a f t e r a s p e c i f i e d time. A f t e r l e a v i n g
t h e workshop i n a f r e e mode and t h r u s t i n g a t a p r e s c r i b e d g l e v e l f o r
a p p r o x i m a t e l y two h o u r s , r e t u r n t o t h e workshop i s made by p e r f o r m i n g
a v e r y small p l a n e change c o r r e c t i o n . A f t e r a s p e c i f i e d t i m e f o r
s e t t l i n g o u t t r a n s i e n t s i n t h e e x p e r i m e n t f l u i d s , t h e p r o c e d u r e would
b e r e p e a t e d u n d e r a new g l e v e l . The AV c o r r e c t i o n i s made when t h e
two b o d i e s a r e a t t h e i r n e a r e s t a p p r o a c h - a p p r o x i m a t e l y 160 m e t e r s f o r
t h e l o m 3 g l e v e l c a s e , which o c c u r s a p p r o x i m a t e l y two h o u r s a f t e r l e a v i n g
the workshop. Maximum s e p a r a t i o n i n t h e two-hour p e r i o d i s approxima t e l y
g l e v e l , 1 . 5 km f o r t h e lo-" g l e v e l and .15 km f o r
15 km f o r t h e
t h e 10'" g l e v e l a c c e l e r a t i o n . Maximum s e p a r a t i o n may b e a f a c t o r s i n c e
Thermo i s b e i n g c o n s i d e r e d a s a manned LM. Atmospheric d r a g o f a p p r o x i m a t e l y l o - " g ' s m a g n i t u d e i s c o n s i d e r e d t o be a c t i n g on b o t h b o d i e s i n
o r b i t . T h i s method o f p r o d u c i n g t h e r e q u i r e d a c c e l e r a t i o n l e v e l s f o r
t h e e x p e r i m e n t s , a l o n g w i t h s p i n up and i n - p l a n e t h r u s t i n g modes, i s
b e i n g e v a l u a t e d by t h e P r o j e c t Thermo P a n e l . The a d v a n t a g e s o f t h e
normal t h r u s t method i n c l u d e p o s i t i o n r e p e a t a b i l i t y i n o r b i t w i t h
s m a l l e r AV c o r r e c t i o n s t o rendezvous and a l e s s complex g u i d a n c e and
c o n t r o l . A d i s a d v a n t a g e i s t h e added w e i g h t o f t h r e e s e p a r a t e t h r u s t
l e v e l motors.
(DAO)
A s i n g l e l a u n c h v e h i c l e f e a s i b i l i t y s t u d y was made on
a CSM/MSFC f u l l r a c k c o n f i g u r a t i o n . L o n g i t u d i n a l t h r u s t made f o r a
14-day m i s s i o n was c o n s i d e r e d ; t h e w e i g h t o f t h i s con£ i g u r a t i o n exceeded
t h e s i n g l e l a u n c h c a p a b i l i t y o f a n u p r a t e d S a t u r n I v e h i c l e by a l m o s t
-
�2 , 0 0 0 pounds.
System t r a d e o f f s ( i . e . , f u e l c e l l s v s b a t t e r i e s and
r o t a t i o n a l v s l o n g i t u d i n a l a c c e l e r a t i o n s y s t e m s ) and m i s s i o n d u r a t i o n
r e d u c t i o n s ~ w o u l db e r e q u i r e d t o make t h e s i n g l e l a u n c h Thermo m i s s i o n
feasible.
(DAO)
b.
O r b i t a l S l o s h T e s t Requirements
A memorandum d e t a i l i n g t h e low g s l o s h t e s t r e q u i r e m e n t s of t h e Aero-Astrodynamics L a b o r a t o r y h a s b e e n p u b l i s h e d .
These
r e q u i r e m e n t s would a p p l y t o t h e p r o p o s e d P r o j e c t Thermo o r a n y o t h e r
o r b i t a l f a c i l i t y i n w h i c h t h e o p p o r t u n i t y f o r low g t e s t i n g m i g h t e x i s t .
To o b t a i n t h e n e c e s s a r y i n f o r m a t i o n , a minimum o f t h r e e t e s t s was
s p e c i f i e d . A p p r o x i m a t e l y e i g h t e e n h o u r s o f low g t e s t t i m e would b e
required.
A memorandum i s b e i n g p r e p a r e d w h i c h documents t h e
r e s u l t s t o d a t e o f a low g l o n g i t u d i n a l a c c e l e r a t i o n s t u d y .
A s p l i n t e r m e e t i n g between P&VE, Advanced S y s t e m s , and
Aero-Astrodynamics p e r s o n n e l was h e l d t o d e t e r m i n e t h e r e s p o n s i b i l i t i e s
and r e q u i r e m e n t s o f t h e Aero-Astrodynamics L a b o r a t o r y i n P r o j e c t Thermo.
Mission p r o f i l e s a r e t o be s t u d i e d f o r the following: a dual launch
i n t e g r a t e d w i t h the c l u s t e r ; a s i n g l e launch i n t e g r a t e d w i t h t h e c l u s t e r ;
a d u a l 1-aunch i n d e p e n d e n t of t h e c l u s t e r ; and a s i n g l e l a u n c h i n d e p e n d e n t
of the c l u s t e r .
The p r i m a r y c a r r i e r v e h i c l e con£ i g u r a t i o n s t i l l r e m a i n s
t h e CSM/LEM (A/S) and MSFC h a l f r a c k , v i a d u a l l a u n c h , s i n c e i t e x c e e d s
t h e s i n g l e l a u n c h c a p a b i l i t y o f t h e S a t u r n IB b y more t h a n 7 , 0 0 0 pounds.
The a b o v e memorandum w i l l b e p u b l i s h e d t o p r o v i d e
t r a j e c t o r i e s i n c o r p o r a t i n g l o n g d u r a t i o n low g a c c e l e r a t i o n e x p e r i m e n t
t i m e l i n e a s o u t l i n e d i n a Douglas A i r c r a f t C o r p o r a t i o n (DAC) p r o g r e s s
r e p o r t on P r o j e c t Thermo. Even t h o u g h DAC h a s p r o v i d e d a n e x p e r i m e n t
timeline with d e t a i l e d s h o r t duration a c c e l e r a t i o n pulsing, i t was
decided t o d e a l o n l y w i t h broad a c c e l e r a t i o n h i s t o r i e s a t t h i s time.
T h i s d e c i s i o n was made b e c a u s e t h e p r e s e n t e x p e r i m e n t t i m e i s e x p e c t e d
t o be d r a s t i c a l l y a l t e r e d i n e a r l y December.
(DD)
5.
Odyssey
S u p p o r t i s b e i n g g i v e n t o t h e P r o j e c t Odyssey P a n e l d u r i n g
t h e f e a s i b i l i t y and c o n c e p t u a l d e s i g n p h a s e . By a s u r v e y of t h e p r e v e h i c l e s , it appears t h a t the
s e n t l y p r o p o s e d combined ~ o r k s h o p / ~ T M
Odyssey I package c a n b e i n t e g r a t e d i n t o t h e 212 m i s s i o n i f t h e t o t a l
S i n c e t h e 212 m i s s i o n
package w e i g h t c a n r e m a i n below 5 , 0 0 0 pounds.
would be unmanned and w i l l g o t o a 240 NM c i r c u l a r o r b i t (20 NM below
t h e workshop t o a l l o w r e n d e z v o u s ) , t h e p r o c e d u r e would b e t o j e t t i s o n
t h e n o s e cone and s e p a r a t e t h e Odyssey p a c k a g e f r o m t h e t o p of SLA.
�I t would t h e n be o u t o f t h e way when t h e CSM,brought up on 2 1 1 r e n d e z v o u s ,
docks and e x t r a c t s t h e LM/RAcK/ATM. S i n c e t h e d e s i r e d Odyssey o r b i t i s
a n e l l i p s e o f 180 km by 1220 km, t h e package would c o n t a i n a s o l i d p r o p e l l a n t motor.
The package would b e a t t i t u d e - s t a b i l i z e d , and t h e motor
would be ground-commanded t o t r a n s f e r t h e Odyssey package t o t h e d e s i r e d
o r b i t . An i m p u l s i v e s t u d y t o d e f i n e t h e t r a n s f e r p a t h a n g l e , v e l o c i t y
i n c r e m e n t , and t h e r e s u l t i n g motor s i z i n g i s under way. A p e r t u r b a t i o n
s t u d y o f p a t h a n g l e a c c u r a c y and motor impulse t o l e r a n c e s may be
b e n e f i c i a l t o h e l p i n t h e s e l e c t i o n of o f f - t h e - s h e l f g u i d a n c e e l e m e n t s
and s o l i d p r o p e l l a n t motor. A t r a d e o f f of o r b i t a l p a r a m e t e r s may b e
r e q u i r e d t o f i t o f f - t h e - s h e l f motors.
(DAO)
As a r e s u l t of t h e November 17 m e e t i n g of t h e P r o j e c t
Odyssey p a n e l w i t h D r . C . L u n d q u i s t of t h e S m i t h s o n i a n A s t r o p h y s i c a l
Observatory ( p r i n c i p a l i n v e s t i g a t o r f o r the atmospheric s t r u c t u r e
e x p e r i m e n t ) , t h e planned o r b i t was changed.
The p e r i g e e a l t i t u d e was
lowered from 180 km t o 160 km and t h e apogee was r a i s e d from 1 , 2 2 0 km
t o 1 , 7 5 0 km. The r e a s o n f o r t h i s change i s t o g i v e a t m o s p h e r i c d e n s i t y
d a t a o v e r a g r e a t e r r a n g e of a l t i t u d e s . As a r e s u l t , t h e P r o j e c t Odyssey
e x p e r i m e n t package t o t a l v e l o c i t y i n c r e m e n t (AV) i n c r e a s e d from 521 m/s
t o 6 9 9 m/s.
The major p o r t i o n of t h i s l a r g e A , i s t h e r e q u i r e d f l i g h t
p a t h a n g l e change o f 4.78 d e g r e e s r e s u l t i n g a t t h e i n t e r s e c t i o n of h i g h
e n e r g y e l l i p s e w i t h t h e 240 NM c i r c u l a r o r b i t p r e s e n t l y planned f o r t h e
211 v e h i c l e t h a t w i l l b e c a r r y i n g P r o j e c t Odyssey a s a piggyback payload.
As t h e m i s s i o n s and payloads of v e h i c l e s 212 and s u b s e q u e n t a r e made
f i r m , i t m i g h t be p o s s i b l e t o c a r r y P r o j e c t Odyssey i n a v e h i c l e w i t h a
lower p e r i g e e o r c i r c u l a r o r b i t . T h i s would r e d u c e somewhat t h e t o t a l
v e l o c i t y i n c r e m e n t (AV) r e q u i r e d .
(DAO)
'E.
Other P r o j e c t s
Development of Math Models f o r R-AERO-D Use: The U s e r ' s Document f o r m a t h e m a t i c a l models and e n g i n e e r i n g t e c h n i q u e s used i n t h e
modules f o r R-AERO-D, p r e p a r e d under c o n t r a c t by Lockheed, h a s been comp l e t e d and checked, by R-AERO-DM, f o r a c c u r a c y and c o m p l e t e n e s s . The
s c o p e o f work r e q u i r e s t h a t math models be developed f o r r i g i d and
f l e x i b l e body a n a l y s i s .
I t h a s become e v i d e n t d u r i n g development t h a t t h e u s e r document f o r m a t makes i t manageable f o r t h e programmer t o a s s i g n and keep
t r a c k of t h e v a r i o u s l a b e l common s t o r a g e a r e a s needed by any s u b r o u t i n e
(DMILockheed)
i n t h e MARVESS s ys tem.
F.
General
Mission P r o f i l e
M a r t i n Timeline A n a l y s i s Program: One of t h e decks of t h e
s e t of MArtin T i m e l i n e A n a l y s i s Programs, t h e S c h e d u l i n g A n a l y s i s Model,
�i s r u n n i n g and h a s b e e n checked o u t w i t h a sample s e t of i n p u t . The
O r b i t P o s i t i o n A n a l y s i s Model, t h e Grouping A n a l y s i s Model, and t h e
AAP Data Bank r e m a i n t o b e checked o u t . Martin-Denver
is sending a
r e p r s s e n t a t i v e t o d i s c u s s t h e s y s tem problems e n c o u n t e r e d and t o a s s i s t
i n implementing t h e r e m a i n i n g d e c k s .
(~AM/~artin)
2.
Dynamics and C o n t r o l
a. D e s i g n C r i t e r i a f o r C o n t r o l o f Space V e h i c l e s : A d r a f t
of t h e monograph "Rendezvous and ~ o c k i n g "by D a n i e l C h i a r a p p a h a s b e e n
r e v i e w e d , and a l i s t o f s u g g e s t e d r e v i s i o n s and c o r r e c t i o n s was p r e p a r e d and r e t u r n e d t o t h e c o n t r a c t o r . Only minor r e v i s i o n s were s u g g e s t e d f o r t h i s i n £o r m a t i v e monograph.
Of t h e s i x t e e n monographs b e i n g p r e p a r e d under C o n t r a c t
NAS8-11494, s e v e n have b e e n r e c e i v e d i n a form s a t i s f y i n g c o n t r a c t u a l
o b l i g a t i o n s . These have b e e n documented a s a c o n t r a c t o r p u b l i c a t i o n ,
and a r e a v a i l a b l e t o C e n t e r p e r s o n n e l :
(1)
S h o r t P e r i o d Dynamics
GDC-DDE-65-055
O c t . 1965
(2)
T r a j e c t o r y Equations
GDC-DIIE-65-058
Nov. 1965
(3)
L i n e a r Systems
GDC-DDE-66-019
A p r i l 1966
(4)
Nonl i n e a r Sys tems
GDC-DDE-65-056
S e p t . 1965
(5)
Stochastic Effects
GDC-DDE-66-006
Feb. 1966
(6)
O p t i m i z a t i o n Methods
GDC-DDE-66-026
J u l y 1966
(7)
Man i n t h e Loop
GDC-DDE-66-023
May 1966
NASA comments and s u g g e s t e d r e v i s i o n s have b e e n s e n t t o t h e c o n t r a c t o r
f o r two a d d i t i o n a l monographs.
Two o f t h e monographs a r e b e i n g r e v i e w e d
by NASA, and f i v e a r e s t i l l i n v a r i o u s s t a g e s o f p r e p a r a t i o n by t h e cont r a c t o r . A l l o f t h e s i x t e e n monographs w i l l b e e d i t e d f u r t h e r f o r
i n c l u s i o n w i t h o t h e r monographs i n t o one o f a s e r i e s of volumes e n t i t l e d
" S t a b i l i t y , Guidance, and C o n t r o l Design C r i t e r i a " by E l e c t r o n i c s
Research Center.
( ~ C A / ~ e n e r a~ly n a m i c s / ~ o n v a i r )
The monograph,"Component ~ y n a m i c ,sI 1 by J . G. Rolland
C o l l e t t e was r e c e i v e d November 23, 1966. The p u r p o s e s of t h i s mono(1) t o p r e s e n t t h e f o r m u l a t i o n of m a t h e m a t i c a l
graph a r e twofold:
models f o r s e n s o r s ( g y r o s c o p e s , a c c e l e r o m e t e r s , e t c . ) and a c t u a t i n g
e l e m e n t s which a r e a p p l i c a b l e t h r o u g h o u t t h e f r e q u e n c y r a n g e of
i n t e r e s t and (2) t o a c c o u n t f o r phenomena t h a t can i n f l u e n c e t h e
r e s u l t s o f a n a l y s e s . Copies of t h i s monograph w i l l b e d i s t r i b u t e d t o
a p p r o p r i a t e p e r s o n n e l f o r t h e i r comments and s u g g e s t e d r e v i s i o n s .
(DcA/ ~ e n e r a l~ y n a m i c/s~ o n v iar )
�b.
Assessment of S l o s h Coupling w i t h Space Vehicles
A f i n a l r e p o r t documenting t h i s s t u d y was r e c e i v e d
t h i s month. A v e r y r i g o r o u s d e r i v a t i o n of t h e v e h i c l e e q u a t i o n s of
motion was performed, i n c l u d i n g l i q u i d p r o p e l l a n t , by using a summation
of p e r t u r b a t i o n from a known r e f e r e n c e motion i n which v e h i c l e body
axes remain c o i n c i d e n t w i t h the r e f e r e n c e a x i s . The e f f e c t s of the
l i q u i d i n t h e p e r t u r b a t i o n e q u a t i o n s were i s o l a t e d and i d e n t i f i e d . On
r e p l a c i n g t h e l i q u i d motion by a simple mechanical system, t h e p l a n a r
p e r t u r b a t i o n e q u a t i o n s of motion f o r t h e v e h i c l e were a g a i n d e r i v e d .
Comparison of t h e two s e t s of e q u a t i o n s showed t h a t t h e p r e s e n t model
d u p l i c a t e d t h e r e s u l t s o b t a i n e d from t h e o r i g i n a l hydrodynamical simulat i o n . The o n l y d i s c r e p a n c i e s i n t h e MSFC p r e s e n t f o r m u l a t i o n i s a term
i n t h e cons tancy-of - p r e s s u r e e q u a t i o n p r o p o r t i o n a l t o t h e a n g u l a r d i s placement o f the body axes w i t h r e s p e c t t o t h e r e f e r e n c e a x i s . This
e r r o r a r o s e when t h e e q u a t i o n s of motion were n o t p e r t u r b e d , b u t were
(~~S/Convair)
a r b i t r a r i l y l i n e a r i z e d w i t h r e s p e c t t o body r a t e s .
c.
Drift-Minimum and Load Minimum C o n t r o l
An analog computer s i m u l a t i o n was i n i t i a t e d t o s t u d y
t r a n s i e n t s and s t e a d y - s t a t e v a l u e s of r e s u l t a n t v e h i c l e v a r i a b l e s when
e i t h e r drift-minimum o r load-minimum c o n t r o l laws a r e used.
The equat i o n s of motion, w r i t t e n i n body-fixed c o o r d i n a t e s , have been programmed.
Graphs of t h e v a r i a b l e s of i n t e r e s t ( a t t i t u d e e r r o r , a n g l e of a t t a c k ,
e t c . ) were o b t a i n e d f o r b o t h c o n t r o l laws, a s w e l l a s f o r normal gyro
c o n t r o l , t o compare t h e r e s u l t s .
The t h e o r e t i c a l s t e a d y - s t a t e v a l u e
of each v a r i a b l e was c a l c u l a t e d and checked w i t h t h e r e s u l t o b t a i n e d
(DC)
from the computer.
d.
A Method f o r t h e Determination of Empirical Formulas
f o r Launch Vehicle Angle of A t t a c k and Engine
Deflection
The i n t e r n a l n o t e , "A Method f o r t h e Determination of
Empirical Formulas f o r Launch Vehicle Angle of A t t a c k and Engine
D e f l e c t i o n , " October 6 , 1966, IN-AERO-16-55, has been d i s t r i b u t e d .
The computational procedure developed i n t h i s n o t e i s based on
c l a s s i c a l l a r g e sample l e a s t s q u a r e s methods.
The f e a s i b i l i t y of
extending t h i s method t o t h e d e t e r m i n a t i o n of e m p i r i c a l formulas f o r
t h e maximum bending moment w i t h t h e system being f o r c e d by an ensemble
of winds i s being i n v e s t i g a t e d .
(DM)
e.
Paper f o r AIAA 5 t h Aerospace Science Meeting
A paper e n t i t l e d , "The I n f l u e n t i a l Aspects of Atmosp h e r i c D i s t u r b a n c e s on Space Vehicle Design Using S t a t i s t i c a l Approaches
f o r A n a l y s i s , " has been prepared f o r p r e s e n t a t i o n a t t h e AIAA 5 t h
�Aerospace Sciences Meeting i n New York, January 23-26, 1967. This paper
i s t o be p r e s e n t e d i n t h e Atmospheric F l i g h t Mechanics s e s s i o n , Wednesday,
(DD)
January 25.
f.
Paper f o r P u b l i c a t i o n i n J o u r n a l of S p a c e c r a f t and
Rockets
A paper e n t i t l e d , "A Technique f o r Analyzing C o n t r o l
Gains Us ing Frequency Response Methods ," has been a c c e p t e d f o r p u b l i c a t i o n by J o u r n a l of S p a c e c r a f t and Rockets.
(DD)
g.
C o n t r a c t w i t h General Dynamics
The c o n t r a c t w i t h General Dynamics on s l o s h i n g a n a l y s i s
has been completed. F i n a l r e p o r t s have been o b t a i n e d :
(1) " B a f f l i n g of F l u i d S l o s h i n g i n C y l i n d r i c a l Tanks ."
This r e p o r t p r e s e n t s a complete t h e o r e t i c a l d i s c u s s i o n of t h e e f f e c t s of
a n a n n u l a r r i n g b a f f l e on t h e behavior of l i q u i d w i t h i n a r i g h t c i r c u l a r
c y l i n d e r . The problem i s solved by assuming two p o t e n t i a l f u n c t i o n s ,
one v a l i d i n t h e r e g i o n above t h e b a f f l e , t h e o t h e r v a l i d i n t h e r e g i o n
below t h e b a f f l e . Matching t h e two f u n c t i o n s i n t h e p l a n e of t h e b a f f l e
l e a d s t o a d u a l s e r i e s . Having t h e s o l u t i o n of t h e s e s e r i e s , we can
c a l c u l a t e t h e displacement of t h e f r e e s u r f a c e a s w e l l a s t h e l i q u i d s
p r e s s u r e , f o r c e s and moments.
( 2 ) "Analysis of F l u i d Sloshing.''
This r e p o r t extends
previous work by d e s c r i b i n g t h e behavior of p r o p e l l a n t due t o o r b i t i n g
motion w i t h s i x d e g r e e s of freedom when t h e c e n t e r of r o t a t i o n i s o f f
t h e a x i s of the v e h i c l e .
Some work i s included on t h e e f f e c t of b a f f l e s
and tank e l a s t i c i t y . A d i g i t a l r o u t i n e f o r computing the s l o s h param( I I D / ~ e n e r a lDynamics)
e t e r s i s included.
h.
C o n t r a c t w i t h Southwest Research I n s t i t u t e
The f i n a l r e p o r t "Experimental and T h e o r e t i c a l S t u d i e s
of Liquid S l o s h i n g a t Simulated Low G r a v i t i e s " has been r e c e i v e d . This
work i s unique i n t h a t i t p r e s e n t s t h e f o r c e s and moments a c t i n g on t h e
p r o p e l l a n t tank f o r Bond numbers between 10 and 200. The r e s u l t s a r e compared w i t h t h e o r e t i c a l p r e d i c t i o n s of t h e mechanical model, and good c o r r e l a t i o n between t h e o r y and experiment i s shown.
A f i n a l r e p o r t , "A Comparison of F l e x i b l e and Rigid
Ring B a f f l e s f o r S l o s h Suppression," has been r e c e i v e d . A t e s t program
t o determine t h e e f f e c t i v e n e s s of f l e x i b l e r i n g b a f f l e s a s l i q u i d s l o s h
s u p p r e s s o r s was conducted. A comparison of f l e x i b l e and r i g i d r i n g
b a f f l e s i s p r e s e n t e d i n terms of l i q u i d damping, f i r s t mode s l o s h i n g
�r e s o n a n t frequency, and maximum b a f f l e d e p t h f o r no r o t a t i o n a l s l o s h .
R e s u l t s show t h a t f l e x i b l e b a f f l e s can reduce b a f f l e weight by a cons i d e r a b l e amount; however, t h e p r o p e r t i e s of t h e b a f f l e m a t e r i a l a t
It may a l s o be necescryogenic temperatures should be b e t t e r known.
s a r y t o i n v e s t i g a t e t h e s t r e s s e s a t t h e b a f f l e i n n e r edge t o i n s u r e
t h a t t h e b a f f l e does n o t t e a r .
(DD)
i.
C o n t r a c t w i t h Lockheed
The f i n a l r e p o r t , " S o l u t i o n s of Systems of Nonlinear
Equations," p r e s e n t s t h e r e s u l t s of a s t u d y t o develop a method and
computer program f o r s o l v i n g an a r b i t r a r y , simultaneous system of nonl i n e a r a l g e b r a i c and t r a n s c e n d e n t a l e q u a t i o n s . The f i n a l r e s u l t i s a
composite computer program which encompasses a " l i m i t e d " spectrum of
b a s i c a l l y d i f f e r e n t numerical methods
g r a d i e n t , m i n i m i z a t i o n , and
s e a r c h t e c h n i q u e s . T e s t r e s u l t s a r e included a s a b a s i s f o r comparison
of t h e d i f f e r e n t methods.
(DD)
-
VIII.
FLIGHT TEST ANALYSIS DIVISION
A.
Special Projects Office
1. The AS-203 and AS-202 ~ l i ~ Ehv at l u a t i o n Reports were
distributed recently.
2. A review copy of t h e S a t u r n V F l i g h t T e s t E v a l u a t i o n P l a n ,
which has been d i s t r i b u t e d , p r e s e n t s e v a l u a t i o n procedures and i n t e r f a c e s , and t h e a n a l y s i s and r e p o r t i n g r e s p o n s i b i l i t i e s of the v a r i o u s
o r g a n i z a t i o n s r e p r e s e n t e d on t h e S a t u r n F l i g h t E v a l u a t i o n Working Group.
The p l a n i s being reviewed by a l l elements of t h e FEWG i n c l u d i n g s t a g e
c o n t r a c t o r s . FEWG s p l i n t e r meetings a t DAC and S&ID have been scheduled
f o r t h e week of December 5 , 1966 t o d i s c u s s proposed changes.
B.
F l i g h t E v a l u a t i o n Branch
1.
Saturn F
I3
a.
S-IB P r e s s u r e Environment
A d i g i t a l program, which has been w r i t t e n t o complement p r e s e n t e v a l u a t i o n programs f o r t h e S a t u r n IB p r e s s u r e environment,
w i l l be used t o e v a l u a t e b u r s t i n g l o a d s i n t h e forward compartment (SM,
SLA, e t c . ) u s i n g measured i n t e r n a l p r e s s u r e s w i t h t h e experimental
e s t e r n a l flow f i e l d . R e s u l t s from t h i s a n a l y s i s w i l l be p r e s e n t e d i n
a memorandum a l o n g w i t h measured AS-203 p r e s s u r e d i f f e r e n t i a l s .
�The Tracker E r r o r Model Study (TEMS) on AS-202 t r a c k i n g
d a t a i s b e i n g p u b l i s h e d . This s t u d y i s o l a t e s t h e i n d i v i d u a l e r r o r s t h a t
may have been p r e s e n t i n t h e a c t u a l t r a c k i n g d a t a r e c e i v e d from the
E a s t e r n T e s t Range on each v e h i c l e . By accumulating t h i s i n f o r m a t i o n
f o r s e v e r a l v e h i c l e s , we w i l l be a b l e t o use t h e d a t a more e f f e c t i v e l y ,
determine r e a l i s t i c t r u n c a t e d e r r o r models t o i n c o r p o r a t e i n t h e t r a j e c t o r y programs, and perhaps g i v e some feedback t o t h e E a s t e r n T e s t Range
on t h e a c t u a l performance of t h e t r a c k i n g systems. On AS-202, d a t a
from f i v e r a d a r s , P a t r i c k , M e r r i t t I s l a n d , Grand Bahama, Grand Turk,
and Antigua, a l o n g w i t h d a t a from GLOTRAC S t a t i o n I, were a n a l y z e d .
The r e s u l t s were q u i t e encouraging i n t h a t , f o r most of t h e systems
a n a l y z e d , t h e r e were s i m i l a r i t i e s between t h e r e s u l t s o b t a i n e d on
AS-202 and t h e r e s u l t s o b t a i n e d on AS-201.
The SA-203 t r a c k i n g d a t a
a r e being a n a l y z e d ; p r e l i m i n a r y r e s u l t s should be a v a i l a b l e soon.
(1)
Emergency D e t e c t i o n System
The d e a c t i v a t i o n time f o r two-engines-out a u t o m a t i c a b o r t on AS-204 w i l l be l i f t - o f f p l u s 100 seconds.
I f one engine
f a i l s b e f o r e 40 seconds, t h e two-engines-out a u t o m a t i c a b o r t s i g n a l t o
d i s a b l e w i l l be delayed u n t i l 120 seconds. This d e c i s i o n was made i n
the E i g h t e e n t h Crew S a f e t y Panel meeting.
(2)
P r e f l i g h t Control
AS-204 i s t h e f i r s t S a t u r n 1B v e h i c l e w i t h a
" c h i - f r e e z e " program. This program w i l l b e a c t i v a t e d by a n engine
f a i l u r e which occurs b e f o r e 65 seconds of f l i g h t . Engine-out s t u d i e s
i n d i c a t e no s e v e r e c o n t r o l o r l o a d s problem i n t h e S-IB s t a g e and no
u n d e s i r a b l e p o s t s e p a r a t i o n S-IVB s t a g e dynamic t r a n s i e n t s f o r a s i n g l e
engine f a i l u r e . No c o l l i s i o n o r c o n t r o l problem e x i s t s f o r t h e nominal
o r off-nominal S-IBIS-IVB s e p a r a t i o n . A 99 p e r c e n t p r o b a b i l i t y of
successful separation exists with a single retro-rocket failure.
2.
Saturn V
a.
Emergency D e t e c t i o n System
Eleven S a t u r n V f a i l u r e modes have been i n v e s t i g a t e d
by TBC. The a n a l y s i s shows t h a t no EDS auto-.abort l i m i t is s a t i s f a c t o r y
f o r a l l f a i l u r e modes. Engine and a c t u a t o r m a l f u n c t i o n s a l l o w no p o s i t i v e warning time.
TBC recommendations a r e a s f o l l o w s :
�b.
(1)
V e r i f y t h e launch v e h i c l e s t r u c t u r a l c a p a b i l i t y .
(2)
Determine a combination of c o n t r o l system d e s i g n
and " c h i - f r e e z e " schedule t h a t improves v e h i c l e
c o n t r o l l a b i l i t y and reduces l o a d s f o r malfunctioned
vehicle.
AS-501
-
P r e f l i g h t Control
TBC has d e l i v e r e d copies of t h e AS-501 dynamics a n a l y s i s
r e p o r t . The r e p o r t i s s a t i s f a c t o r y and i s expected t o be d i s t r i b u t e d
soon. I n f l i g h t wind l i m i t s f o r t h e AS-501 have been r e c e i v e d from TBC.
A t t h e most c r i t i c a l a l t i t u d e (10 km), t h e v e h i c l e i s wind-limited t o
25, 100 and 40 m/s f o r head, t a i l and c r o s s winds, r e s p e c t i v e l y . The
p r o b a b i l i t y of n o t exceeding t h e s e l i m i t s i s 99 p e r c e n t f o r t h e months
of February and March. These wind l i m i t s may be s l i g h t l y decreased
because of a r e v i s i o n of s t r u c t u r a l l i m i t s (based on a, f3 and Mach)
p r e s e n t e d i n memorandum R-P&VE-SJ-66-264, " I n f l i g h t S t r u c t u r a l Limits
f o r S a t u r n V AS-501, AS-502, and AS-503," dated November 21, 1966.
Launch r e l e a s e wind r e s t r i c t i o n s imposed by t h e s p a c e c r a f t s t r u c t u r e
a r e a peak wind of 28 k n o t s (95 p e r c e n t ) . A t p r e s e n t , two a r e a s a r e
b e i n g i n v e s t i g a t e d f u r t h e r : l i f t o f f and c h i - f r e e z e program.
3.
S a t u r n Apollo A p p l i c a t i o n s
A proposed p l a n f o r p r o c e s s i n g and handling of d a t a f o r
Apollo A p p l i c a t i o n s Experiments i s being prepared. There i s a n a p p a r e n t
need f o r a n organized system of p r o c e s s i n g and handling of t h i s e x p e r i ment d a t a because of t h e l a r g e q u a n t i t y and t h e complexity of d a t a
involved. Once a n o r g a n i z a t i o n i s s e t u p f o r t h i s purpose, i t can
o p e r a t e more e f f i c i e n t l y f o r a l l experiments than t h e i n d i v i d u a l e x p e r i ments done independently. Problems faced on each i n d i v i d u a l experiment
can c o n t r i b u t e t o improvements on succeeding experiments i f t h e same
o r g a n i z a t i o n handles a l l of t h e experiments. This would n o t be t r u e i f
each experiment were handled by d i f f e r e n t o r g a n i z a t i o n s s i n c e they would
n o t have t h e advantage of p a s t e x p e r i e n c e .
The proposed p l a n f o r p r o c e s s i n g and handling of e x p e r i mental d a t a c a l l s f o r R-AERO-F and R-COMP t o be "base" o r g a n i z a t i o n s of
a working group on a l l experiment d a t a . These o r g a n i z a t i o n s w i l l be
supplemented by o r g a n i z a t i o n s concerned w i t h each i n d i v i d u a l experiment.
This means t h a t ,from one experiment t o t h e n e x t , t h e o r g a n i z a t i o n s w i l l
change e x c e p t f o r t h e two "base" o r g a n i z a t i o n s (R-AERO-F and R-COMP)
.
�4.
Contracts
a.
S a t u r n IB Systems C o n t r a c t (CCSD, New O r l e a n s )
(1)
AS-202 P o s t f l i g h t T r a j e c t o r y
CCSD has p u b l i s h e d t h e p o s t f l i g h t t r a j e c t o r y
r e p o r t on AS-202.
It was due O c t o b e r 25 ( l a u n c h p l u s 60 d a y s ) . It
was completed f o r MSFC r e v i e w a week e a r l y .
The r e p o r t was e x c e l l e n t ,
d e m o n s t r a t i n g t ' h a t CCSD h a s t h e c a p a b i l i t y t o assume r e s p o n s i b i l i t y o f
t h e i n t e r m e d i a t e t r a j e c t o r y (7 d a y s ) , f i n a l t r a j e c t o r y (14 d a y s ) and
t h e t r a j e c t o r y r e p o r t (60 d a y s ) b e g i n n i n g w i t h AS-204.
(2)
AS-202 S-IB S t a g e P r o p u l s i o n F l i g h t S i m u l a t i o n
The AS-202, S-IB performance a n a l y s i s of t h e s t a g e
p r o p u l s i o n s y s tem conducted by CCSD (Michoud) and MSFC (AERO-FFR) w i t h
Some d i f f i c u l t y was
t h e f l i g h t s i m u l a t i o n programs has b e e n completed.
e n c o u n t e r e d i n m a t c h i n g t h e Observed Mass P o i n t T r a j e c t o r y (OMPT)
b e c a u s e o f t h e r o u g h n e s s o f t h e a c c e l e r a t i o n s from OMPT d u r i n g t h e
f i r s t 25 s e c o n d s of f l i g h t .
The problem was s o l v e d by u s i n g a c c e l e r a t i o n s from t h e ST-124M g u i d a n c e s y s tem.
The a c c e l e r a t i o n s d u r i n g t h i s
from OMPT produced a n u n r e a l i s t i c s h a p e i n t h e aerodynamic d r a g c o e f f i c i e n t which i n t u r n a f f e c t e d t h e p r o p u l s i o n p a r a m e t e r c o r r e c t i o n s .
CCSD and MSFC a g r e e w i t h i n a b o u t 0 . 1 p e r c e n t on
t h e p r o p u l s i o n s y s t e m performance a n a l y s i s .
This agreement demonstrates
t h a t CCSD has t h e c a p a b i l i t y t o assume t h e r e s p o n s i b i l i t y f o r d e t e r mining p r o p u l s i o n s y s t e m performance by f l i g h t s i m u l a t i o n f o r a l l
f u t u r e S a t u r n IB v e h i c l e s .
b.
S a t u r n V Systems C o n t r a c t (The Boeing Company)
TBC i s s c h e d u l e d t o assume t h e p o s t f l i g h t t r a j e c t o r y
Only
r e s p o n s i b i l i t y on t h e S a t u r n V v e h i c l e s b e g i n n i n g w i t h AS-504.
r e c e n t l y h a s TBC r e a l i z e d a l l of t h e d e t a i l s and c o m p l e x i t i e s i n v o l v e d
i n t h i s r e s p o n s i b i l i t y . Biweekly m e e t i n g s a r e now b e i n g h e l d t o r e v i e w
work done by TBC and t o e n s u r e t h e i r moving i n t h e p r o p e r d i r e c t i o n .
TBC i s s c h e d u l e d t o do a p a r a l l e l e f f o r t w i t h MSFC on AS-501.
They
w i l l u s e MSFC-developed programs i n t h e p o s t f l i g h t t r a j e c t o r y a r e a .
Much work r e m a i n s t o b e done t o d e v e l o p t h e TBC c a p a b i l i t y t o t h e
p o i n t where a p a r a l l e l e f f o r t c a n be performed.
�C.
F l i g h t Mechanics Branch
1.
Saturn V
The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h a "Cape
tape" and t h e accompanying p r i n t - o u t , t h e r e v i s e d g u i d a n c e p r e s e t t i n g s ,
and t h e f i n a l r a n g e s a f e t y document. The g u i d a n c e p r e s e t t i n g s have
b e e n d i s t r i b u t e d t o R-ASTR-NG.
The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h t h e p r e l i m i n a r y d i s p e r s i o n a n a l y s i s document and a n e r r a t u m o f t h e d i s p e r s i o n
a n a l y s i s . A l l n e c e s s a r y d a t a have b e e n g i v e n t o t h e Boeing Company s o
t h a t t h e y c a n complete t h e f i n a l o p e r a t i o n a l t r a j e c t o r y r e p o r t and
dispersion analysis.
A l l n e c e s s a r y i n f o r m a t i o n h a s been g i v e n t o TBC s o
t h a t t h e y c a n b e g i n work on t h e g u i d a n c e p r e s e t t i n g s .
The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h t h e
g u i d a n c e p r e s e t t i n g s , which a r e b e i n g v e r i f i e d .
The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h a "Cape
t a p e " and t h e accompanying p r i n t - o u t and t h e p r e l i m i n a r y r a n g e s a f e t y
document.
d.
General
Work h a s begun on r e v i s i n g o u t p u t i n t h e new f o r m a t of
t h e B-7 t a p e as a r e s u l t o f m e e t i n g s w i t h MSC r e p r e s e n t a t i v e s , who h a v e
r e q u e s t e d us t o add a b o u t 40 words t o t h e t a p e .
The B-7 t a p e f o r m a t r e v i s i o n has b e e n completed and
t h e f o r m a t h a s b e e n d i s t r i b u t e d . A t h r e e - s t a g e Marves s i m u l a t i o n w i t h
IGM i n t o o r b i t h a s b e e n checked o u t and is i n p r o d u c t i o n .
2.
S a t u r n IB
The d i s p e r s i o n a n a l y s i s i s r e a d y f o r d i s t r i b u t i o n .
The
f i n a l "Cape t a p e " h a s b e e n r e c e i v e d from CCSD b u t was r e t u r n e d f o r c o r rection.
It s h o u l d b e r e t u r n e d by O c t o b e r 31 and r e a d y t o s h i p t o KSC
and MSC.
�A memo h a s b e e n p u b l i s h e d on AS-204 t w o - e n g i n e - o u t
c a p a b i l i t y and what s h o u l d b e e x p e c t e d i f t h e S-IB LOX v e n t v a l v e f a i l s
t o open. Graphs were f u r n i s h e d t o show t h e e n g i n e - o u t c a p a b i l i t y , which
i n c l u d e d SPS b u r n t o o r b i t . Should t h e LOX v e n t v a l v e f a i l t o o p e n ,
t h r u s t would d r o p 3 p e r c e n t and m i x t u r e r a t i o would d r o p by 2 p e r c e n t .
The t o t a l e f f e c t would be 2,400 pounds o f S-IVB r e s e r v e s consumed.
The "AS-204 Launch V e h i c l e O p e r a t i o n a l T r a j e c t o r y
D i s p e r s i o n A n a l y s i s ," h a s b e e n d i s t r i b u t e d . The f i n a l "Cape t a p e " and
r a n g e s a f e t y r e p o r t have a l s o b e e n d i s t r i b u t e d . New p r o p u l s i o n and mass
p r e d i c t i o n s h a v e b e e n r e c e i v e d , and t h e i r e f f e c t s on S-IVB r e s e r v e s a r e
being inves t i g a ted.
Two hundred and t h i r t y c o p i e s of t h e p r e l i m i n a r y
o p e r a t i o n a l t r a j e c t o r y have b e e n r e c e i v e d from CCSD. The f i n a l
o p e r a t i o n a l t r a j e c t o r y has been g e n e r a t e d .
The o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s , and
r a n g e s a f e t y a n a l y s i s have b e e n completed based on t h e o l d m i s s i o n .
The e f f e c t s caused by p l a c i n g t h e 205 i n t o t h e 207 m i s s i o n a r e b e i n g
evaluated
.
Two hundred and t h i r t y c o p i e s o f t h e p r e l i m i n a r y
o p e r a t i o n a l t r a j e c t o r y have b e e n r e c e i v e d from CCSD. The d i s p e r s i o n
a n a l y s i s and r a n g e s a f e t y r e p o r t s a r e a b o u t 5 0 p e r c e n t c o m p l e t e .
D.
T r a c k i n g and O r b i t a l A n a l y s i s Branch
1. M r . R. Benson a t t e n d e d t h e F l i g h t Mechanics P a n e l M e e t i n g
O c t o b e r 19-20, 1966, a t MSC. The d e c a y and l i f e t i m e p r e d i c t i o n s f o r
AS-209 were p r e s e n t e d . Memorandum R-AERO-FT-50-66 documents t h e AS-209
presentation.
2 . A d e c a y a n a l y s i s of t h e SA-8, SA-9, and SA-10 o r b i t s f o r
t h e p e r i o d J u l y 15 t h r o u g h August 1 , 1966, h a s been d e l i v e r e d by
Lockheed under t h e M i s s i o n S u p p o r t C o n t r a c t .
The p u r p o s e o f t h i s
r e p o r t is t o determine t h e r a t i o of the apparent atmospheric d e n s i t y
t o t h e 1959 ARDC d e n s i t y i n t h e p e r i g e e a l t i t u d e r e g i o n 490-520 km and
f o r t h e p e r i o d s t u d i e d . The r e s u l t s i n d i c a t e t h a t t h e 1959 ARDC d e n s i t y
i s a p p r o x i m a t e l y 8 t o 20 t i m e s t h a t o f t h e a p p a r e n t d e n s i t y under t h e
SA-8, SA-9, and SA-10 o r b i t a l c o n d i t i o n s . The s p r e a d i n t h e r a t i o i s
due t o t h e d i f f e r e n c e s i n t h e p o s i t i o n of t h e p e r i g e e s and t h e d i u r n a l
b u l g e . These r e s u l t s c o n f i r m t h e d e n s i t y p r o f i l e c u r r e n t l y b e i n g used
by t h i s b r a n c h f o r t h e l i f e t i m e and d e c a y p r e d i c t i o n s of o t h e r s p a c e
miss ions
.
�3. R-AERO-FT p r e s e n t e d a summary of t h e l i f e t i m e work and
a s s o c i a t e d s u b j e c t s t o D r . G e i s s l e r on October 26. The b a s i c t h e o r y
of t h e l i f e t i m e model, t h e e q u a t i o n s , t h e a t m o s p h e r i c d e n s i t y model,
and t h e s o l a r c y c l e p r e d i c t i o n t e c h n i q u e used by R-AERO-FT were
discussed.
R-AERO-FT recommended t h a t more e f f o r t s h o u l d b e expended
i n t h e a r e a s of s o l a r c y c l e p r e d i c t i o n , c o e f f i c i e n t of d r a g d e t e r m i n a t i o n , and o r b i t a l a t t i t u d e p r e d i c t i o n .
4. The r e s t u d y on t h e l i f e t i m e p r e d i c t i o n s of t h e 39 s a t e l l i t e s u s i n g a p r e d i c t i o n o f t h e s o l a r a c t i v i t y c y c l e was completed.
Only 2 o f t h e 39 c a s e s produced l i f e t i m e p r e d i c t i o n s w h e r e i n t h e a c t u a l
l i f e t i m e f e l l o u t s i d e t h e k22a l i m i t s . The mean o f t h e r a t i o of t h e
a c t u a l l i f e t i m e t o t h e p r e d i c t e d l i f e t i m e was 0.978 w i t h a s t a n d a r d
d e v i a t i o n of 1 1 . 7 p e r c e n t . This compares f a v o r a b l y w i t h t h e mean and
s t a n d a r d d e v i a t i o n o b t a i n e d when t h e a c t u a l s o l a r c y c l e was used i n
the lifetime predictions.
The mean and s t a n d a r d d e v i a t i o n s f o r t h i s
s t u d y w e r e 1.00 and 8 . 2 p e r c e n t , r e s p e c t i v e l y .
These r e s u l t s were
included i n a l e t t e r t o D r . Mueller.
' .
5 . During t h e Guidance and Performance Subpanel Meeting h e l d
November 8 , 1966, a t MSFC, a d i s c u s s i o n of AS-205 o r b i t a l l i f e t i m e
r e v e a l e d a n MSC i n t e r e s t i n t h e a t m o s p h e r i c model used by R-AERO t o
o b t a i n t h i s i n f o r m a t i o n . The MSC r e p r e s e n t a t i v e s s t a t e d t h a t , by
u s i n g R-AERO'S method o f m o d i f y i n g t h e 1962 U . S . S t a n d a r d , e x c e l l e n t
r e s u l t s had b e e n o b t a i n e d f o r t h e Gemini m i s s i o n s .
They were v e r y
i n t e r e s t e d i n u s i n g o u r deck a s t h e i r s t a n d a r d and wanted t o i n v e s t i g a t e t h e p o s s i b i l i t y o f u s i n g i t a t t h e Cape f o r r e a l - t i m e a n a l y s i s .
They s t a t e d t h e y would c a l l s o o n t o a r r a n g e a m e e t i n g on t h e s u b j e c t .
6. T r a c k i n g c o v e r a g e f o r t h e s p e c i a l AS-501 t r a j e c t o r y p r o f i l e s was p r e p a r e d f o r p r e s e n t a t i o n t o t h e O p e r a t i o n S u p p o r t Requirements
Subpanel a t KSC (December 1 - 2 , 1 9 6 6 ) . M r . Benson i s a t t e n d i n g t h i s
meeting.
7 . Memorandum R-AERO-FT-53-66 was s e n t t o R-AERO-YS, M r . S m i t h ,
s p e c i f y i n g t h e maximum and minimum e x p e c t e d d e n s i t i e s which could be
e x p e c t e d from t h e R-AERO-FT O r b i t a l L i f e t i m e Model.
�PUBLICATIONS
I.
Fox, P . A . and D . W. Camp, " P e r c e n t a g e L e v e l s of Wind Speed
D i f f e r e n c e s Computed b y Using Rawinsonde Wind Data from S a n t a
Monica, C a l i f o r n i a , NASA TM X-53528, O c t o b e r 21, 1966, U n c l .
2.
H a u s s l e r , J . B . , " S a t u r n SA-203 P o s t f l i g h t T r a j e c t o r y , " NASA
TM X-53554, November 4 , 1966, Uncl.
3.
K r a u s e , F . R . , S . S . Hu, and A . J. Montgomery, "On Crossed-Beam
M o n i t o r i n g o f Atmospheric Winds and T u r b u l e n c e w i t h Two O r b i t i n g
T e l e s c o p e s , " NASA TM X-53538, November 1 4 , 1966, U n c l .
4.
W a l k e r , W. H. , "A Method f o r t h e D e t e r m i n a t i o n of E m p i r i c a l
Formulas f o r Launch V e h i c l e Angle of A t t a c k and Engine D e f l e c t i o n , " Aero-Astrodynamics I n t e r n a l Note 16-66, O c t o b e r 6 , 1966,
Unclassified.
5.
York, Randy J . , "A Method f o r t h e S e n s i t i v i t y A n a l y s i s o f R i g i d
Body S a t u r n V Dynamics," Aero-Astrodynamics I n t e r n a l Note 17-66,
O c t o b e r 6 , 1966, Uncl.
6.
Redus, J . R . , " S t a b i l i t y of Motion o f a Launch V e h i c l e C o n s i d e r i n g
t h e R a t e o f Change of t h e P a t h Angle," Aero-Astrodynamics I n t e r n a l
Note 18-66, November 1 7 , 1966, Uncl.
�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
December 1 2 , 1966
APPROVAL:
,.
D e p u t y 6 i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y
L
E . D. G e i s s l e r
D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y
DISTRIBUTION
R-AERO-DIR
Dr. G e i s s l e r
Mr. J e a n
R-AERO-A
(20)
R-AERO-G
(5)
R-AERO-R
M r . B u t l e r (4)
Mrs. Hightower
R-AERO-Y
(5)
R-AERO-F
(8)
R-AERO-T
Mr. Murphree
M r . Cumrnings
Mr. D i c k e y
Dr. Heybey
Mr. L a v e n d e r
Mr. Jandebeur
Dr. L i u
Dr. Krause
M r . von P u t t k a m e r
R-AERO-X
(2)
R-AERO-P
(8)
R- AERO-D
(16)
R-DIR, M r . C o o k
PAO, M r . K u r t z
MS-H, M i s s J e r r e l l (3)
I-V-P,
Harold Price
�
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000042
Title
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: December 12, 1966."
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George C. Marshall Space Flight Center
Date
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1965-12-12
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1960-1969
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Saturn Project (U.S.)
NASA space programs
Project management
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Progress reports
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Saturn V Collection
Box 19, Folder 44
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
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spc_stnv_000027_000050
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http://libarchstor2.uah.edu/digitalcollections/files/original/20/990/spc_stnv_000043.pdf
b19b01e420bc4d1180a282e116827fca
PDF Text
Text
AERO-ASTRODYNBMIGS LABOKATQRY
MONTHLY PROGRESS REPORT
November 2 . 1965
Page
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1
TECHNICAL AND SCIENTIFIC STAFF
1
PROJECTS OFFICE
1
1
Saturn HB
2,,
Saturn V . . . . . . . . . . . . . . . . . . . ~ . O I D . o . . . . . . . . . . . . . . . . ~ . . . .1
2
3
General
3
AEROSPACE E3SVIRQWENT OPFHGE
3
A.
Space Environment Group
4
B
T e r r e s t r i a l E n v i m m e n t Group
4
C
Environmental Applications Group
5
D. Atmospheri.e Pleasuring Group
5
ASTRODYNmHCS AhD GUHDAXCE THEORY DIVISIOX
5
A
Astrodynamfcs Branch
6
B. Guidance Theory Branch
8
C
Optimization Theory Branch
10
AERODYNAMICS DIVISION
. . . . e u . . . u . . . . . o . . . . .
10
A
Aerodynamic Design Branch
10
l 8 Saturn BB
11
2
Saturn V
12
3
General
12
B.
E l e c t r o m ~ c h a n i c a l Branch
14
C
F a c i l i t i e s Branch
15
D.
Thermal Environment Branch
15
P
Saturn 1
15
2
Saturn I B
17
3
Saturn centaur
18
4
Saturn V
19
5
General
22
E
Unsteady Aerodynamics Branch
24
DYNAMICS AND FLIGHT MECJ3AlYPCS DIVISION
24
A
Dynamics Analysis Branch
24
1
Saturn I B
25
2
Saturn V . . . . . . . . . . . . . . . . . . . O O e . . . . . . . . . . . . . . . . . . . . .
26
3
General
26
4
Contractors
27
B
Control Theory Branch
27
1 Saturn HB
28
2
Saturn ~ ~ / ~ e n t a u r
28
3
Saturn V
29
4
General
29
5. Contractors
..
.
. ..
..
.
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�.......... 3434
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36
.
...........................................
37
.
.......................................
38
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42
.
.........
V I I.
43
...............................
43
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44
.
..........................................
44
.................... 464 6
.
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............................... 4747
..
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49
. .
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50
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50
.
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50
........................................... 50
51
PUBLICATIONS .................................................
. 1.
2.
Applied Guidance and F l i g h t Mechanics Branch
Saturn I B
Saturn V
3
General
4
Contractors
D
Advanced P r o j e c t s Study Branch
FLIGHT EVALUATION ANI> OPERATIONS STUDIES DIVISION
A.
Special Projects Office
B e P l i g h t Evaluation Branch
1 Saturn I
2 . Saturn PI3 and V Data Processor
3
Contracts
C.
F l i g h t Mechanics Branch
1 Saturn PB
2
Saturn V
D
Operations Studies Branch
1
Saturn HB
2
Saturn V
3 0 General
C
�AERO-ASTRODYNAMICS LABORATORY
MONTHLY PROGRESS REPORT
November 2, 1965
I.
TECHNICAL AND SCIENTIFIC STAFF
1. A paper on a c o u s t i c a l zero l e v e l f o c i formed by r a y s r e t u r n i n g
from t h e t h i r d atmospheric l a y e r has been r e v i s e d and w i l l be p u b l i s h e d
s h o r t l y . A computer program based on t h i s i n v e s t i g a t i o n has been
developed and t r i e d (Beybey).
2. The Fehlberg power s e r i e s method has been a p p l i e d ' t o t h e
r e s t r i c t e d problem of t h r e e bodies.
P e r i o d i c s o l u t i o n s of 2 2 - d i g i t
accuracy ( f o r t h e i n i t i a l c o n d i t i o n s ) a f t e r one f u l l p e r i o d were
produced d e s p i t e t h e f a c t t h a t t h e t r a j e c t o r i e s were s e n t p u r p o s e l y
c l o s e t o and below t h e s u r f a c e of t h e moon. These r e s u l t s exceed what
has been r e p o r t e d i n t h e l i t e r a t u r e and i l l u s t r a t e t h e power of t h e
Pehlbesg methods when coupled w i t h t h e extended p r e c i s i o n f e a t u r e of
t h e IBM I620 Computer ( P e a s l e y ) .
11.
PROJECTS OFFICE
1,
S a t u r n PB
CCSD A e r o b a l l i s t i c s Q u a r t e r l y Review: The f i r s t FY-66 Q u a r t e r l y
Review of t h e C h r y s l e r C o r p o r a t i o n Space D i v i s i o n " (CCSD) e f f o r t i n
s u p p o r t o f t h e Aero-Astrodynamics Laboratory was h e l d a t MSFC on October
19, 1965. This t e c h n i c a l review covered t h e work performed under mod 208,
item I H I b of c o n t r a c t NAS8-4016.
CCSD has 126 personnel onrboard o u t
of t h e 128 a u t h o r i z e d . A l l t e c h n i c a l a n a l y s e s a r e p r o g r e s s i n g smoothly.
2.
Saturn V
a.
D i r e c t Ascent Mode
The p r e s e n t a t i o n of t h e r e s u l t s of t h e d i r e c t a s c e n t s t u d i e s
t o D r , von Braun has been delayed because of t h e heavy work load w i t h i n
t h e Laboratory. A new d a t e f o r t h e d i r e c t a s c e n t d r y r u n and p r e s e n t a t i o n
i s being c o o r d i n a t e d .
b,
Engine Out
The major problems a s s o c i a t e d w i t h S a t u r n V engine-out a r e
being f u l l y i n v e s t i g a t e d . They a r e i n t h e a r e a s of s t r u c t u r a l l o a d s and
t h e S - I 1 h e a t s h i e l d , The s t a g e c o n t r a c t o r s have been asked t o impact
�t h e c o s t and s c h e d u l e s f o r i n c r e a s i n g d e s i g n l o a d s c a p a b i l i t y f o r
engine-out.
Since t h e S - I 1 s t a g e h e a t s h i e l d w i l l be t e s t e d f o r
engine-out c o n d i t i o n s about t h e f i r s t of 1966, S a t u r n V engine-out
e f f o r t s a r e being f i n a l i z e d .
3.
General
a.
Incentive Contracts
-
Performance C r i t e r i a
The S-IVB p l a n f o r i n c o r p o r a t i n g f l i g h t performance i n t o
t h e i n c e n t i v e c o n t r a c t i s n e a r i n g completion. This p l a n w i l l p r o v i d e
f o r a measure of t h e payload c a p a b i l i t y , t h e m i s s i o n accomplishment,
and t h e t e l e m e t r y d a t a r e c e i v e d ,
The miss i o n accomplishment p o r t i o n
of t h e p l a n w i l l i n c l u d e a s s u r a n c e o f sub-system performance.
The
S-IC and S - I 1 p l a n s a r e n o t a s w e l l developed a s t h e S-IVB a t t h i s
time; however, p l a n s t o a s s u r e f l i g h t performance f o r t h e s e s t a g e s
a r e being formulated w i t h t h e a s s i s t a n c e o f o t h e r l a b o r a t o r i e s .
b.
F l i g h t Mechanics Panel A c t i v i t i e s
The Fourteenth F l i g h t Mechanics Panel Meeting was h e l d on
October 5 and 6 , 1965. The minutes of t h i s meeting a r e documented i n
~ ~ 6 / ~ 3 3
d a1t e,d October 6 , 1965.
c.
P r o p e l l a n t U t i l i z a t i o n System
- Guidance
System I n t e r a c t i o n
Recent r e s u l t s from t h e S-IVB b a t t l e s h i p t e s t s and t h e S-IVB
201 s t a g e acceptance f i r i n g have r e v e a l e d t h r u s t o s c i l l a t i o n s o f peak-to60 seconds.
peak magnitude o f up t o 12,000 pounds w i t h a p e r i o d of 50
The o s c i l l a t i o n s r e s u l t from n o n l i n e a r i t i e s i n t h e p r o p e l l a n t u t i l i z a t i o n
probe.
The i t e r a t i v e guidance mode (IGM) developed f o r S a t u r n i s based
on c o n s t a n t t h r u s t . The IGM s t e e r i n g program i s a s t r o n g f u n c t i o n o f
F/M, and t h u s t h e v e h i c l e e x p e r i e n c e s an a t t i t u d e h i s t o r y , X, v e r y
similar t o the thrust history.
The commanded a t t i t u d e r a t e , X, i s
restricted to
one degree p e r second. Therefore, t h e t h r u s t o s c i l l a t i o n
r e s u l t s i n d e v i a t i o n s from t h e optimized p a t h which cannot always be
c o r r e c t e d by t h e commanded a t t i t u d e program.
For t h e S a t u r n I B program,
s o f t w a r e m o d i f i c a t i o n s t o t h e guidance mode r e s u l t i n a f i x t h a t seems
a c c e p t a b l e f o r AS-201 s i n c e guidance accuracy and performance a r e n o t
v e r y s t r i n g e n t f o r t h i s f l i g h t . M o d i f i c a t i o n of system g a i n s by R-P&VE
a f f o r d some a l l e v i a t i o n f o r AS-202 and subsequent f l i g h t s ; however, i t
was f e l t a t a r e c e n t S-IVB Technical Review t h a t t h e t h r u s t o s c i l l a t i o n s
must be reduced d r a s t i c a l l y b e f o r e f l i g h t o f AS-204.
En t h e S a t u r n V
program, + 10,000 pound peak-to-peak t h r u s t o s c i l l a t i o n s i n t h e burn-out
o f o r b i t by t h e S-IVB r e s u l t i n i n j e c t i o n f l i g h t p a t h a n g l e e r r o r s o f
about 0.75 d e g r e e s ( s i x times t h e hardware e r r o r ) . When t r a n s l a t e d t o
t h e l u n a r r a d i u s t h i s r e s u l t s i n 4,000 krn e r r o r , t h u s c a l l i n g f o r a AV
c o r r e c t i o n o f about 50 m/sec.
Since t h i s i s e s s e n t i a l l y t h e t o t a l AV
-
+
�budget s e t a s i d e f o r t h e l u n a r m i s s i o n , it i s t o t a l l y unacceptable. T h i s
problem has been brought t o t h e a t t e n t i o n of t h e top management o f MSFC
and DAC andanMSFC-DAC t a s k team has gone t o Minneapolis-Honeywell, t h e
probe m a n u f a c t u r e r , t o e x p e d i t e a s o l u t i o n .
PHI.
AEROSPACE ENVIRONMENT OFFICE
A,
Space Environment Group
1. M r . Robert E. Smith a t t e n d e d a meeting on t h e thermosphere
probe program ( o r b i t a l a l t i t u d e d e n s i t y measurements) a t Kennedy Space
Center w i t h p e r s o n n e l from t h e U n i v e r s i t y of Michigan, Thiokol Chemical
C o r p o r a t i o n and r e p r e s e n t a t i v e s from ETR and KSC. F a c i l i t i e s and s e r v i c e s
t o be provided by KSC and ETR were d i s c u s s e d i n d e t a i l , e s p e c i a l l y t h e
c a p a b i l i t y of t h e ETR i n t r a c k i n g t h e Nike Tomahawk, and were found t o be
satisfaetsry.
P l a n s a r e being formulated t o Paunch s i x o r seven probes
on a s i n g l e day i n May o r J u n e , depending upon t h e a v a i l a b i l i t y o f t h e
ETR, f o r maximum use of d a t a measurements.
2. M r . R. E. Smith and M r . J. 0. B a l l a n c e , R-AERO-A, v i s i t e d
t h e U n i v e r s i t y o f Michigan t o d i s c u s s p r o g r e s s o f t h e thermosphere probe
program and a s s o c i a t e d problems concerning d a t a r e d u c t i o n and i n t e r p r e tation.
Progress i s s a t i s f a c t o r y .
3. The d r a f t copy of t h e r e p o r t on t h e Space Environment
C r i t e r i a c o n t r a c t was r e t u r n e d t o A e r o j e t General C o r p o r a t i o n f o r
revision.
The f i n a l r e p o r t should be p u b l i s h e d by December 1, 1965.
4. A paper e n t i t l e d "Decrease i n E l e c t r o n Density i n t h e
Ionosphere Following t h e Passage of S a t u r n I , " by M r . J, K. F e l k e r and
M r . W. T. Roberts has been accepted f o r p r e s e n t a t i o n a t t h e Second AAS
Symposium on I n t e r a c t i o n of Space Vehicles w i t h an Ionized Atmosphere
t o be h e l d i n Miami Beach, F l o r i d a , i n November.
5 , A r e p o r t e n t i t l e d 'Neasurement o f Winds by Chemical R e l e a s e s
i n t h e Upper Atmosphere," by M r . Hugh Morgan i s being prepared f o r
publication.
6. A r e p o r t e n t i t l e d "An Environmental Model f o r Van A l l e n
B e l t P r o t o n s , " by M r , W. T. Roberts was completed and i s being reviewed.
7.
A model o f a c o l d t r a p gauge f o r measuring t h e mass d e n s i t y
a t o r b i t a l a l t i t u d e s was d e l i v e r e d by t h e C e l e s t i a l Research Corporation.
The f i n a l r e p o r t on t h i s f e a s i b i l i t y s t u d y i s b e i n g completed and w i l l
be p u b l i s h e d a s a c o n t r a c t o r r e p o r t i n December.
�B.
T e r r e s t r i a l Environment Group
1, The f i n a l r e p o r t ( P a r t IV), "Mathematical Wind P r o f i l e s ' "
has been r e c e i v e d from t h e Lockheed C a l i f o r n i a Company. This r e p o r t ,
which p r e s e n t s d e t a i l e d procedures f o r p r e d i c t i n g a f u t u r e v e c t o r wind
p r o f i l e from p r e s e n t and p a s t wind p r o f i l e s f o r a p p l i c a t i o n a t Cape
Kennedy, F l o r i d a , i s being reviewed, along w i t h t h e o t h e r t h r e e p a r t s ,
f o r NASA p u b l i c a t ion.
2. A r e v i s i o n t o TM X-53023, v n T e r r e s t l - i a lEnvironment ( C l i m a t i c )
C r i t e r i a G u i d e l i n e s f o r u s e i n Space Vehicle DeveBopment, i s being
prepared i n f i n a l form.
This r e p o r t , a l o n g w i t h a s i m i l a r r e p o r t on
space environment c r i t e r i a , i s used by MSFC i n program d e s i g n s t u d i e s .
C,
Environmental A p p l i c a t i o n s Group
1, Work ccntinued cn t h e i n v e s t i g a t i o n of atmospheric t u r b u l e n c e
f c r space v e h i c l e s ,
S p e c t r a of s m a l l - s c a l e motions p r e s e n t En t h e d e t a i l e d
wind p r o f i l e s t h a t a r e n o t included i n t h e r a w i ~ s o n d emeasurements have
been c a l c u l a t e d far a s i z e a b l e sample, and t h e p r o b a b i l i t y o f energy
c o n t e n t a s a f u n c t i o n of frequency has been e s t a b l i s h e d , This w i l l
permit t h e s p e c i f i c a t i o n of s p e c t r a l d e n s i t i e s of t h e s m a l l - s c a l e
motions on a p r o b a b i l i t y b a s i s .
S i m i l a r s p e c t r a a r e a l s o being computed
f o r t h e t o t a l wind speed p r o f i l e s up t o wave l e n g t h s of 4000 meters, A
j o i n t program i s under way w i t h R-AERO-D t o i n v e s t i g a t e v a r i o u s methods
f o r h a n d l i n g t u r b u l e n c e i n p u t s f o r v e h i c l e response c a l c u l a t i o n s .
2.
It was r e c e n t l y r e q u e s t e d t h a t t h e T r a v e l e r s Research
C e n t e r , I n c . , under c o n t r a c t NAS8-18450, p r e p a r e a complete t e s t p l a n
i n c l u d i n g equipment, number o f personnel needed, number and type of
experiments, methods o f s o u r c e s i m u l a t i o n , and c o s t s f o r conducting
f u l l - s c a l e atmospheric d i f f u s i o n f i e l d t e s t s . This t e s t p l a n w i l l be
completed by December 31, 1965, and forwarded t o NASA Headquarters
(OART and OSSA) f o r t h e i r review and comments, Such t e s t s a r e r e q u i r e d
t o p r o p e r l y e v a l u a t e t h e atmospheric hazards a s s o c i a t e d w i t h t h e u s e of
toxic propellants.
The r e s u l t s o f t h e f i e l d t e s t s , i f conducted, w i l l
s e r v e t o v e r i f y t h e atmospheric models formulated by TRC under t h i s
contract.
D e f i n i t i v e i n f o r m a t i o n on t h e d i f f u s i o n of t o x i c exhaust
byproducts i s q u i t e l i m i t e d , e s p e c i a l l y w i t h r e g a r d t o t h e p o s s i b l e
use of f l u o r i n e a d d i t i v e t o f u e l s a s i s being proposed.
I f FLOX i s
used, t h e f i e l d t e s t s must be conducted t o b e t t e r d e f i n e such problems
a s atmospheric chemistry a s s o c i a t e d w i t h FLOX, buoyant t r a n s p o r t , downwind
p a r t i c u l a t e d i s p e r s i o n , i n t e g r a t e d and peak c o n c e n t r a t i o n s w i t h r e l a t i o n
t o d i s t a n c e , and lower atmospheric c o n d i t i o n s .
3 . NASA" 150-meter Meteorological Tower F a c i l i t y l o c a t e d on
t h e ' M e r r i t t I s l a n d Launch Area (MILA) i s o n l y p a r t i a l l y o p e r a t i o n a l .
E l e c t r o n i c and mechanical d i f f i c u l t i e s r e l a t e d t o i n s t a l l a t i o n and
�o p e r a t i o n of t h e anemometers have caused l e n g t h y d e l a y s . When winds
reached magnitudes of 10-20 m/sec, t h e anemometer cups s e p a r a t e d from
t h e i r transducer units.
The manufacturer s p e c i f i e s t h a t t h e s e cup
A l l cup
systems a r e a b l e t o w i t h s t a n d approximately 40 m/sec winds.
u n i t s had t o be r e d e s i g n e d causing s e v e r a l weeks delay. Other f a c t o r s
such a s e l e v a t o r m a l f u n c t i o n s , s e v e r e weather, low p r i o r i t y o f work,
e t c . , have c o n t r i b u t e d t o t h e p r e s e n t i n o p e r a t i v e n e s s of t h i s met tower
f a c i l i t y . A c o n c e r t e d e f f o r t i s being made t o g e t t h e f a c i l i t y o p e r a t i o n a l .
D.
Atmospheric Measuri.ng Group
No c o n t r i b u t i o n received.
HV.
ASTRBDPNA&llCS
A.
Am
G U I D m C E TBEORY DBVSS ION
Astrodynamics Bran.&
1.
Cislunar Trajectory Studies
-
a , Contractor
A r e p o r t "Ephemeral Design Parameters f o r
C i s l u n a r O r b i t a l T r a j e c t o r i e s " has been prepared by Lockheed. T h i s r e p o r t
documents much of t h e d a t a generated i n t h e c i s l u n a r o r b i t s t u d y and
d i s c u s s e s t h e v a r i o u s parameters which have major e f f e c t s on t h e o r b i t
The study has a l s o been extended t o a n a n a l o g i n v e s t i perigee history.
g a t i o n o f parameters (such a s o r b i t a l elementq), which have n o t y e t been
c o n s i d e r e d , and a c o n c u r r e n t r e e v a l u a t i o n of p r e v i o u s l y g e n e r a t e d d a t a
i n terms of new parameters.
-
In-House
An e r r o r found i n t h e T r i c e computer program
b.
f o r t h e e l l i p t i c a l - t h r e e - b o d y model i s bei.ng c o r r e c t e d . The s t u d y .of
s e p a r a t e p e r t u r b a t i o n s on c i s l u n a r o r b i t s u s i n g t h e e l l i p t i c a l three-body
model i s c o n t i n u i n g w i t h t h e use o f IBM 7094 d i g i t a l o u t p u t programs;
however, t h i s approach i s slower w i t h o u t t h e T r i c e program t o p r o v i d e
t h e groundwork.
-
A preliminary c a l c u l a t i o n of
2. Conic I n t e r p l a n e t a r y Program
Earth-to-Mercury t r a j e c t o r i e s u s i n g t h e new c o n i c t r a j e c t o r y program i s
continuing.
This s t u d y i s s t i l l uncovering p a r t i c u l a r l y small e r r o r s
i n t h e program which a r e n o t r e v e a l e d by t h e b a s i c checkout procedure.
It i s a l s o p r o v i d i n g f a m i l i a r i z a t i o n of new branch p e r s o n n e l w i t h t h e
deck and w i t h i n t e r p l a n e t a r y t r a j e c t o r y c a l c u l a t i o n .
-
I n connection
3 . P r e c i s i o n I n t e r p l a n e t a r y T r a j e c t o r y Program
w i t h t h e c o n t r a c t which was awarded Auburn U n i v e r s i t y f o r i n c l u d i n g
t h r u s t i n a p r e c i s i o n i n t e r p l a n e t a r y program, t h e program was formulated
t o be s u i t a b l e f o r a d a p t a t i o n and was given t o Auburn.
I n a d d i t i o n some
e d u c a t i o n of d i v i s i o n p e r s o n n e l i n t h e formation of r e c u r s i o n r e l a t i o n s
h a s been provided s o t h a t e f f e c t i v e c o n t r a c t monitoring w i l l be p o s s i b l e .
�B.
Guidance Theory Branch
a.
Northrop Schedule Order No. 7
A comprehensive t r a j e c t o r y and guidance system e r r o r
a n a l y s i s of t h e Centaur Voyager m i s s i o n t o p a r k i n g o r b i t has been
completed under t h e assumption t h a t I G M c o n t r o l s t h e Centaur s t a g e .
The launch window
T h i s work w i l l be p u b l i s h e d a s a Northrop r e p o r t .
and launch azimuth v e r s u s time problem i s being s t u d i e d , and computer
r u n s w i l l be made on t h e Centaur c o n f i g u r a t i o n t o g a i n experience.
Machine time demands a r e c o n s i d e r a b l e s i n c e t h e f l i g h t must go from
pad t o Mars, and p r i o r i t y r e q u e s t s do not seem j u s t i f i e d .
b.
S t u d i e s were continued on s t a t i s t i c a l a n a l y s i s of
guidance systems.
P a r t i c u l a r emphasis i s being placed on Monte C a r l o
a n a l y s i s a s a p p l i e d t c ~s i m u l a t i o n .
S t u d i e s of s t a t i s t i c a l a n a l y s i s o f
midcourse maneuvers a r e a l s o being c a r r i e d o u t . A t p r e s e n t , t h i s e f f o r t
i s l a r g e l y one of r e a d i n g and study t o develop background i n c o r r e c t
s t a t i s t i c a l a n a l y s i s o f guidance systems and t r a j e c t o r y e r r o r s .
2.
&ow Thrust Guidance and Performance
Northrop Schedule Order No. 6: Attempts have been made t o
measure t h e l o s s of e f f i c i e n c y i n f o l l o w i n g low t a n g e n t i a l t h r u s t t o
Thus f a r , i t has
escape by computing a n optimum COV escape t r a j e c t o r y .
been impossible t o converge w i t h t h e COV deck i f no end c o n d i t i o n s o t h e r
t h a n escape energy a r e s p e c i f i e d , a l t h o u g h t h e computation i s being
c a r r i e d o u t i n o r b i t element c o o r d i n a t e s . An a t t e m p t i s being made t o
s p e c i f y a d d i t i o n a l c o n d i t i o n s a t t h e end, such a s p a t h a n g l e , t o s e e i f
convergences can be o b t a i n e d f o r a l e s s optimum t r a j e c t o r y .
This problem
i s being attempted in-house i n r e c t a n g u l a r c o o r d i n a t e s u s i n g a more
e f f i c i e n t i s o l a t i o n procedure t o see i f convergence can be o b t a i n e d .
There i s no p r o g r e s s t o r e p o r t i n t h e low t h r u s t guidance a r e a .
3.
Implementation S t u d i e s
a. M o d i f i c a t i o n s t o ~ e w t o n ' smethod ( w i t h e x a c t v a l u e s
f o r t h e p a r t i a l d e r i v a t i v e s ) t o i n c l u d e f i x e d s t a g i n g times have been
completed. The computer program s o l v e s t h e boundary v a l u e problem
a s s o c i a t e d w i t h t h e o p t i m i z a t i o n of t r a j e c t o r i e s from b o o s t e r c u t o f f
t o o r b i t w i t h up t o 10 s t a g e s allowed, M o d i f i c a t i o n s f o r s w i t c h i n g
f u n c t i o n s t o allow t h e d e t e r m i n a t i o n of optimal s t a g i n g p o i n t s a r e a l s o
b e i n g programmed.
b.
The a p p l i c a t i o n o f ~ e w t o n ' smethod t o t h e d e t e r m i n a t i o n
of an o p t i m a l g e o c e n t r i c low t h r u s t t r a j e c t o r y from o r b i t t o escape i s
being attempted.
Some problems w i t h ' t h e accuracy of t h e i n t e g r a t i o n of
�t h e d i f f e r e n t i a l e q u a t i o n s have been encountered. More e f f i c i e n t
numerical i n t e g r a t i o n techniques a r e b e i n g s t u d i e d t o overcome t h e
prob lem.
4.
Contracts
a.
Aeronutronics (NAS8-20150)
P r i n c i p a l i n v e s t i g a t o r , M r . Rishard AuePmann, v i s i t e d
MSFC on October 2 1 t o d i s c u s s work on t h e c o n t r a c t . P r i n c i p a l l y , t h e
c o n t r a c t has provided t h e r e s u l t s of s i m p l i f i e d s t e e r i n g e q u a t i o n s f o r
t h e performance problem and o r b i t t r a n s f e r miss i o n w i t h one c o a s t period.
This o p p o r t u n i t y was t a k e n t o r e o r i e n t t h e work along l i n e s of d e t e r m i n i n g
a feedback l o g i c f o r t h e guidance problem i n t h e hope t h a t a simple
sub-optimal guidance procedure w i l l be found f o r t h e p l a n a r o r b i t
t r a n s f e r problem.
While p r e v i o u s work has been o f good q u a l i t y i n t h e
development o f p e r t u r b a t i o n s o l u t i o n s t o t h e e q u a t i o n s of motion, i t
seems t o be somewhat academic. C e r t a i n a c t i v i t i e s i n c o n n e c t i o n w i t h
e s t a b l i s h i n g t h e accuracy of t h e p e r t u r b a t i o n s o l u t i o n s w i l l continue.
The s i m p l i f i c a t i o n of c o n s t a n t engine a c c e l e r a t i o n has been assumed i n
a l l work t h u s f a r and may be somewhat u n r e a l i s t i c f o r t h i s reason.
b.
Auburn U n i v e r s i t y (NAS8-1548)
This c o n t r a c t has been r e - d i r e c t e d t o t h e a r e a of low
t h r u s t t r a j e c t o r y o p t i m i z a t i o n . A t p r e s e n t , no p r o g r e s s has been r e p o r t e d .
c,
Hayes I n t e r n a t i o n a l (NAS8-20176)
Many d i f f i c u l t i e s i n o b t a i n i n g a s o l u t i o n t o t h e low
t a n g e n t i a l t h r u s t problem i n a form simple enough f o r the a p p l i c a t i o n
o f a p e r t u r b a t i o n procedure have been r e p o r t e d .
These d i f f i c u l t i e s
have l e d t o study o f a p e r t u r b a t i o n procedure u s i n g t h e t a r g e t o r b i t
f o r the o r b i t t r a n s f e r mission as a reference.
The p r e s e n t problem
r e q u i r e s t h e e v a l u a t i o n s f s e v e r a l i n t e g r a l s which i s now under study.
There i s l i t t l e p r o g r e s s t o r e p o r t i n low t h r u s t guidance pending a
more s a t i s f a c t o r y s ~ l u t i o nt o t h e t r a j e c t o r y computation problem.
Numerical s t u d y o f p a t h a d a p t i v e guidance polynomials
i s c o n t i n u i n g t o a t t e m p t t o d i s c o v e r t h e r e l a t i o n s h i p between nonconvergent
p e r t u r b e d c a s e s and t h e t r a j e c t o r y volume used t o d e f i n e t h e guidance
polynomial,
d.
I l l i n o i s I n s t i t u t e of Technology (NAS8-20129)
It has been found t h a t t h e l a s t two t u r n s o f a s p i r a l
escape t r a j e c t o r y can be approximated f a i r l y c l o s e l y by simple e x p o n e n t i a l
f u n c t i o n s . Using t h e s e approximations, a velocity-to-be-gained s t e e r i n g
�has been formulated t o be checked o u t i n t h e f u t u r e . The c o n t r o l w i l l
a t t e m p t t o s a t i s f y v e l o c i t y d i r e c t i o n v e r s u s d e p a r t u r e time w i t h v e l o c i t y
magnitude remaining f r e e . A r e l a t i v e l y simple velocity-to-be-gained
s t e e r i n g h a s a l s o been formulated f o r t h e r e v e r s e c a p t u r e s p i r a l - t o c i r c u l a r o r b i t . Numerical work w i l l begin on t h e s e and some o t h e r
f a i r l y simple sub-optimum s t e e r i n g laws.
e,
U n i v e r s i t y sf North C a r o l i n a (lVAS8-20106)
Work was continued o n t h e development of a n o v e r - a l l
a l g e b r a i c m a n i p u l a t i o n package, and s e v e r a l l a r g e - s c a l e t e s t s on product i o n were run.
The t r i g o n o m e t r i c simpkif i c a t i s n s were extended t o change
f u n c t i o n s of n e g a t i v e q u a n t i t i e s t o t h e corresponding f u n c t i o n s of
positive quantities.
The f a c t o r i n g a l g o r i t h m was extended t o f a c t o r
o u t t r i g o n o m e t r i c f u n c t i o n s and t o a l s o r e c o g n i z e e q u i v a l e n t p a r e n t h e s i z e d
e x p r e s s i o n s a s t h e same, The m a j o r i t y sf t h e m o d i f i c a t i o n s were made
due t o a d e t a i l & e v a l u a t i o n cf t h e e n t i r e e f f o r t f o r p r e p a r a t i o n of a
techlfcal report.
C.
O p t i m i z a t i o n Theory Branch
1.
Mininax Des ign Technique
A minimax d e s i g n technique f o r c o n t r o l systems w i t h
d i s t u r b a n c e s i s being developed based on a theory of d i f f e r e n t i a l
games.
The p r i n c i p a l advantage o f t h i s technique i s t h a t t h e e f f e c t s
of a worst d i s t u r b a n c e i n a c e r t a i n c l a s s can be i n c o r p o r a t e d i n t o t h e
i n i t i a l s y n t h e s i s o f t h e c o n t r o l system, By use of t h i s technique,
c o n v e n t i o n a l d e s i g n a i d s such a s t h e r o o t l o c u s method can be a d j u s t e d
t o i n c l u d e d i s t u r b a n c e e f f e c t s . The technique i s being a p p l i e d t o
launch v e h i c l e models, and t h e study i s b e i n g documented.
2.
Northrop Schedule Order No.
1
O b ~ e c t i v e s : ( a ) To i . n v e s t i g a t e aria-design techniques
f o r l i n e a r systems; and ( b ) t o i n v e s t i g a t e Load r e l i e f systems f o r a
h i g h l y aerodynamically u n s t a b l e v e h i c l e .
~ u g h e s ' and ~ o r t h r o p ' sa n a l y t i c d e s i g n methods have been
a p p l i e d t o a f i f t h o r d e r b o o s t e r model.
The systems designed by each
method were e v a l u a t e d by s t a n d a r d a n a l y s i s techniques.
Both achieved
t h e s p e c i f i e d performance.
However, i n g e n e r a l , t h e systems designed
by Hughes method were sounder i n t h e sense o f being l e s s s e n s i t i v e t o
Some e x p e r i e n c e
parameter v a r i a t i o n s and being e a s i e r t o implement.
was n e c e s s a r y even w i t h t h e Hughes method t o achieve good e n g i n e e r i n g
design. An a t t e m p t w i l l be made t o determine what s p e c i f i c a t i o n s should
be made i n the Hughes method t o a s s u r e soundly designed systems.
As
soon a s t h e n e c e s s a r y programs a r e r e a d y , Hughes method w i l l be extended
�t o h i g h e r o r d e r systems t o determine i f i t r e t a i n s i t s a t t r a c t i v e
f e a t u r e s . Because t h e Northrop method r e q u i r e s l e s s computation, i t
would be more d e s i r a b l e , i f i t s l i m i t a t i o n s could be overcome.
M o d i f i c a t i o n s t o t h e method were suggested t o Northrop, which t h e y
a r e attempting t o incorporate.
Bending moment r e d u c t i o n g o a l s based on l o a d i n g e q u i v a l e n t
t o burnout c o n d i t i o n s were e s t a b l i s h e d f o r t h e s t u d y v e h i c l e , and bending
moments were computed f o r t h e s t a n d a r d wind p r o f i l e and load r e l i e f
c o n t r o l systems.
These bending moments were about 200 p e r c e n t s f t h e
d e s i g n goal.
Allowable winds f o r which t h e g o a l i s met w i l l be e s t a b l i s h e d ;
a l s o , work w i l l c o n t i n u e i n reducing t h e bending moment f o r t h e s t a n d a r d
wind p r o f i l e , a l t h o u g h i t i s c l e a r t h a t t h e g o a l cannot be reached f o r
t h i s wind.
3.
Contracts
O b j e c t i v e : To i n v e s t i g a t e t h e f e a s i b i l i t y and o p e r a t i o n
o f t h e d i g i t a l a d a p t i v e f i l t e r , a c u r v e - f i t t i n g procedure f o r e l i m i n a t i n g
f l e x u r e components from t h e c o n t r o l s i g n a l .
The d r a f t of t h e f i n a l r e p o r t was r e c e i v e d . Although
i t i s a thoroughly documented r e p o r t , i t i s d i f f i c u l t t o r e a d and
important c o n c l u s i o n s a r e n o t c l e a r l y s t a t e d . Quite an e x t e n s i v e
r e w r i t i n g would be d e s i r a b l e . Review i s continuing.
b.
North American A v i a t i o n (NAS8-20056)
O b j e c t i v e : To improve t h e accuracy and speed o f t h e
d i g i t a l frequency i d e n t i f i c a t i o n system
an a d a p t i v e s t a b i l i z a t i o n
system
and t o extend i t s a p p l i c a t i o n t o a c t i v e s t a b i l i z a t i o n o f
f l e x u r e modes.
-
-
Trajectory simulations reported i n the l a t e s t progress
r e p o r t show l a r g e e x c u r s i o n s of both a n g l e - o f - a t t a c k and engine d e f l e c t i o n .
I n v e s t i g a t i o n i s being conducted t o determine the cause of t h e s e e x c u r s i o n s ,
It i s f e l t t h a t t h e s e a r e probably not due t o t h e a d a p t i v e f i l t e r .
However, system r e d e s i g n t o reduce t h e engine a n g l e might p l a c e more
s e v e r e r e s t r i c t i o n s on t h e f i l t e r s t h a n e x i s t a t p r e s e n t .
c.
C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s (NAS8-20067)
O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g
l i n e a r o p t i m a l c o n t r o l t h e o r y t o t h e s y n t h e s i s of launch v e h i c l e c o n t r o l
systems.
�A meeting was h e l d w i t h C o r n e l l r e p r e s e n t a t i v e s a t
which t h e r e s e a r c h was summarized and f u t u r e d i r e c t i o n of t h e work was
d i s c u s s e d . A d e s i g n procedure was p r e s e n t e d f o r a two-bending-mode
model which i n c l u d e s measures o f a t t i t u d e e r r o r , both bending mode
d e f l e c t i o n s , and c o n t r o l v a r i a b l e i n t h e performance index, Two s y n t h e s i s
methods f o r t h e r e s u l t i n g o p t i m a l c o n t r o l law were p r e s e n t e d . One depends
on proper placement of two blended r a t e gyros t o a c h i e v e t h e d e s i r e d g a i n
r a t i o s between t h e v e h i c l e parameters.
The o t h e r method i n v o l v e s reformul a t i o n o f t h e s t a t e v a r i a b l e s t o i n c l u d e measurable q u a n t i t i e s . This
second method appears t o be p r e f e r a b l e .
Some p r e l i m i n a r y w ~ r khas been done o n t h e c o n s t r a i n e d
feedback g a i n problem, and a f e a s i b l e s o l u t i o n technique i s being sought
Future e f f o r t s w i l l i n c l u d e an. i n v e s t i g a f o r one promising formulation.
t i o n of t h e model-in-performance-index approach.
A.
Aerodynamic Design Branch
1.
Saturn I B
a. Apollo-Saturn LB S p a c e c r a f t Compartment Venting: During
t h e p a s t week, P&VE and v a r i o u s c o n t r a c t o r s have i n v e s t i g a t e d t h e e f f e c t
of r e d u c i n g t h e i n - f l i g h t v e n t a r e a i n the s p a c e c r a f t compartment o f t h e
AS-201 and AS-202 v e h i c l e s .
The r e s u l t s show t h a t i n no c a s e i s the
s t r u c t u r a l b u r s t c a p a b i l i t y o f t h e s e r v i c e module LEM a d a p t e r , I U , o r
S - I n forward s k i r t exceeded. However, MSC has s t a t e d t h a t t h e AP load
on t h e s e a l between t h e command module and s e r v i c e module i s marginal
and h a s s t i p u l a t e d t h a t i f t h e v e n t a r e a i s reduced t o 100 square i n c h e s ,
Since t h e
t h e I U leakage should n o t be reduced from 15.4 s q u a r e inches.
maximum p r e d i c t e d i n t e r n a l p r e s s u r e i s n o t dependent on l e a k a g e s , MSC has
been asked t o determine i f t h e i r s t r u c t u r e can w i t h s t a n d t h e maximum
compartment p r e s s u r e h i s t o r y f o r a 100-square-inch v e n t a r e a a s p r e s e n t e d
i n R-AERO-AD-65-46.
Based on the S a t u r n V t e s t d a t a , t h e e x t e r n a l p r e s s u r e s
over t h e S-IVB forward s k i r t a r e somewhat h i g h e r on t h e S a t u r n V v e h i c l e
interstage
t h a n a n t h e S a t u r n I B because of t h e i n f l u e n c e o f t h e S-II/S-IV
frustum, Since t h e S a t u r n I B and S a t u r n V v e h i c l e d e s i g n maximum and
minimum e x t e r n a l p r e s s u r e s a r e p r e s e n t l y based on t h e PSTL-2 ( S a t u r n IB)
d a t a , t h e S a t u r n V d i s t r i b u t i o n s w i l l be updated t o c o r r e c t t h i s p o r t i o n
of t h e d a t a . P&VE has been n o t i f i e d o f t h i s d i s c r e p a n c y and w i l l i n c o r p o r a t e t h e c o r r e c t e d d i s t r i b u t i o n i n t o t h e r e d e s i g n o f t h e S-IVB forward
skirt,
�b. Apollo-Saturn I B Aerodynamic C h a r a c t e r i s t i c s : The
f i n a l aerodynamic c h a r a c t e r i s t i c s of t h e Apollo-Saturn I B v e h i c l e s a r e
complete. Included i n t h i s r e p o r t w i l l be t o t a l v e h i c l e s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s , l o a d d i s t r i b u t i o n s , and component
This w i l l be a c o m p i l a t i o n and r e f i n e m e n t
aerodynamic c h a r a c t e r i s t i c s
o f t h e d a t a t o be used f o r design confirmation. These d a t a a r e being
p u b l i s h e d i n a NASA TMX.
.
c. AmesD S a t u r n ~ ~ I C e n t a uP r e s s u r e Test: The l a r g e s c a l e
S a t u r n centaur p r e s s u r e t e s t scheduled f o r Ames wind t u n n e l f a c i l i t i e s
has been postponed because of t h e r e c e n t changes i n t h e Voyager spacec r a f t requirements.
These t e s t s t o be conducted by CCSD w i l l be
rescheduled f o l l o w i n g a d e c i s i o n o n t h e Centaur payload c o n f i g u r a t i o n .
d. S a t u r n I ~ / C e n t a u rMod i f i c a t i o n Study: As r e q u e s t e d by
JPL, MSFC r e c e n t l y conducted a s t u d y t a determine the f e a s i b i B i t y of
i n c r e a s i n g t h e payload volume of the Saturn 1 8 I ~ e n t a u r v e h i c l e .
Because
of t h e l imited time a l l o t t e d f o r t h e s t u d y , o n l y two o f t h r e e proposed
c o n f i g u r a t i o n s were s t u d i e d , one b e i n g s i m i har t o the p r e s e n t S a t u r n PB/
Centaur v e h i c l e w i t h a 176-inch c y l i n d r i c a l shroud extension. and t h e
o t h e r having a hammerhead (298-inch d i a m e t e r ) payload shroud. The
aerodynamic c h a r a c t e r i s t i c s f o r t h e s e v e h i c l e s were e s t i m a t e d , and the
d a t a a r e being prepared f o r p u b l i c a t i o n .
2.
Saturn V
a. Load D i s t r i b u t i o n s : Pre liminary load d i s t r i b u t i o n s
f o r t h e S a t u r n V v e h i c l e with a Voyager payload have been r e q u e s t e d by
t h e Dynamics and P l i g h t Mechanics D i v i s i o n . These d i s t r i b u t i o n s a r e
being assembled by the Northrop Space L a b o r a t o r i e s , Three c o n f i g u r a t i o n s a r e being considered; 260-inch c y l i n d e r s of 20, 40, and 60 f e e t
a r e being i n s e r t e d between t h e I U and t h e Voyager payload. A Mach
1 . 7 i s b e i n g considered.
r a n g e of 1.5
-
be S-Hc/s-II
I n t e r s t a g e T e s t : T e s t s w i l l be conducted i n
t h e MSFC 14-inch t u n n e l to determine t h e s t a t i c aerodynamic c h a r a c t e r i s t i c s of t h e S a t u r n V S-PC/S-11
i n t e r s t a g e ring.
These d a t a a r e r e q u i r e d
f o r p r e d i c t i o n of impact a r e a s .
P r e l i m i n a r y model d e s i g n i s i n p r o g r e s s .
Based on e s t i m a t e d hardware d e l i v e r y d a t e s , the t e s t s w i l l be conducted
i n February 1966.
c. Hinge Moment: A p r e l i m i n a r y a n a l y s i s r e p o r t of t h e
Phase II Lewis h i n g e moment t e s t r e s u l t s has been r e c e i v e d from Boeing.
The r e p o r t i s being reviewed by t h e Experimental Aerodynamics Section.
The model f o r t h e Phase I11 t e s t a t Lewis i s n e a r l y
complete, Plans a r e t o s h i p t h e model t o Lewis t h e week o f October 1 8 ,
1965. T e s t i n g i s scheduled t o b e g i n approximately December 1, 1965.
�d.
Fin-Shroud I n t e r f e r e n c e - F r e e Aerodynamics : A meeting
was h e l d a t C o r n e l l A e r o n a u t i c a l Laboratory t o d i s c u s s d e t a i l s o f t h e
forthcoming S a t u r n V fin-shroud i n t e r f e r e n c e - f r e e aerodynamic i n v e s t i g a t i o n i n t h e 8 - f o o t t r a n s o n i c t u n n e l . The meeting was concerned mainly
w i t h model d e s i g n , c o n s t r u c t i o n , and t e s t i n g .
The scheduled t e s t d a t e
w i l l be dependent upon t h e time r e q u i r e d f o r C o r n e l l t o d e s i g n and b u i l d
They now have a 6-week t u n n e l s c h e d u l i n g l e a d time
t h e r e q u i r e d models.
which could p o s s i b l y correspond t o t h e time n e c e s s a r y f o r model d e s i g n
and c o n s t r u c t i o n once t h e c o n t r a c t i s f i n a l i z e d .
3.
General
a. O r i f i c e C o e f f i c i e n t Study: A r e v i s e d t e s t program and
p r e t e s t r e p o r t a r e being prepared by Northrop Space L a b o r a t o r i e s .
This
document w i l l i n c l u d e t h e changes and a d d i t i o n s which were d i s c u s s e d
d u r i n g t h e p r e s e n t a t i o n made t o the branch by Nsrthrop.
This r e p o r t
w i l l r e p r e s e n t t h e b a s i s f o r o u r j u s t i f i c a t i o n t o Ames d u r i n g t h e planned
f e a s i b i l i t y conference which w i l l be scheduled t o t a k e p l a c e a t Ames
w i t h i n approximately two weeks.
b. Lockheed T r i s o n i c Program: The f i n a l t e s t phase which
began September 24, 1965, i n t h e MSFC 14-inch t u n n e l i s c o n t i n u i n g
satisfactorily.
T e s t s a r e scheduled t o be completed by October 27, 1965.
Data a n a l y s i s and p r e s e n t a t i o n a r e t o be f i n a l i z e d by September 1966.
c. J P L ' t o o l Wall" T e s t : Model checkout and b a l a n c e
c a l i b r a t i o n a r e i n p r o g r e s s a t JPL f o r t h e forthcoming S a t u r n IBIS-ID
s t a g e "cool w a l l " s t a t i c s t a b i l i t y i n v e s t i g a t i o n ,
T e s t s a r e scheduled
i n t h e 21-inch hypersonic t u n n e l beginning November 22, 1965.
B.
Electromechanical Branch
1.
TASF Equipment Development
A memorandum d a t e d October 25, 1965, gave t h e s t a t u s s f
equipment being developed f o r t h e Thermo-Acoustic Simulation F a c i l i t y
(TASF). The major items a r e a s follows:
I n s t r u m e n t a t i o n Systems
Tank Farm I n t e r c o n n e c t i o n s
Cold Flow Duct
Cold Flow C o n t r o l
Cold Flow Models
Cold Flow Measuring C a r t
Hot Flow Models
Hot Flow Measuring C a r t
Equipment Foundation
Flow V i s u a l i z a t i o n
Gas Sampling
Temperature
Pressure
A l l items a r e about t w o - t h i r d s complete and should be f i n i s h e d near t h e
end o f t h e year.
�2.
50K H e r t z Data A c q u i s i t i o n
A s i x - c h a n n e l magnetic t a p e system f o r r e c o r d i n g d a t a t o
50K Hertz w i t h time f i d e l i t y s u f f i c i e n t f o r c r o s s c o r r e l a t ion on playback
has been checked o u t . The s i g n a l - t o - n o i s e r a t i o of approximately 36db
i s v e r y good f o r t h e wide band (1.5 Mega H e r t z ) e l e c t r o n i c s .
3.
Residual Gas Analyzer
The d e s i g n has been completed f o r a gas m o n i t o r i n g system
f o r t h e Low Density Chamber, This r e s i d u a l gas a n a l y z e r i s designed
t o o p e r a t e a t p r e s s u r e s i n t h e range of 1 0 " ~ t o r r when t h e chamber i s
o p e r a t i n g a t p r e s s u r e s up t o 1 0 " t~o r r w i t h v a r i o u s g a s e s i n t h e n o z z l e
in-flow.
A unique d e s i g n concept i s i n t r o d u c e d f o r a d j u s t i n g t h e conduct a n c e t o p r o v i d e t h e a p p r o p r i a t e p r e s s u r e drop.
4.
Automatic Boundary Layer Probe
This probe, designed f o r t h e 14" t u n n e l , has completed
checkout and i s scheduled f o r use w i t h i n 30 days. A r e p o r t on t h e
equipment w i l l be i s s u e d b e f o r e use.
This p r e c i s i o n - c o n t r o l led probe
has a 2-inch t r a v e r s e w i t h m u l t i p l e a d j u s t a b l e p r e s e l e c t e d p o s i t i o n s
a c c u r a t e t o P 0.001 inches, To account f o r t u n n e l w a l l motion i n t h e
porous w a l l t r a n s o n i c t e s t s e c t i o n , t h e probe w i l l a u t o m a t i c a l l y s e n s e
t h e w a l l and r e f e r e n c e a l l measurements from t h e a c t u a l p o s i t i o n .
5.
Image Plane Model Support
The d e s i g n o f a m i r r o r image model s u p p o r t f o r t h e 14"
t u n n e l i s 60 p e r c e n t complete. The system w i l l i n c l u d e a s p l i t t e r
p l a t e s u p p o r t f o r comparative and supplementary t e s t i n g .
T h i s technique
i s needed f o r 0
180 d e g r e e a n g l e - o f - a t t a c k t e s t s and o t h e r work.
The
e l i m i n a t i o n o f m u l t i p l e models and s t i n g s and s t i n g e f f e c t s i s p o s s i b l e .
It i s a n t i c i p a t e d t h a t t h e image model w i l l produce b e t t e r r e s u l t s t h a n
t h e c o n v e n t i o n a l h a l f model.
The most s e v e r e problem w i l l be s u i t a b l e
gap c o n t r o l between t h e model halves.
Completed equipment i s expected
i n February 1966.
-
6.
Dynamic Damping Balance
Continued development o f e l e c t r i c a l l y d r i v e n dynamic damping
balance has brought t h e frequency t o 130 cps a t r e a s o n a b l e amplitudes.
The s t r u c t u r a l i n t e g r i t y i s t h e most d i f f i c u l t a s p e c t o f r a i s i n g t h e
o p e r a t i n g frequency.
Following p r e l i m i n a r y t e s t i n g d u r i n g t h e month of
November, o t h e r models and r o t a t i o n a l c e n t e r s w i l l be d e v i s e d f o r a f u l l
t e s t range c a p a b i l i t y .
�C.
F a c i l i t i e s Branch
1.
Impulse Base Flow F a c i l i t y
The S - I 1 program was completed i n e a r l y October. This
program confirmed h i g h nozzle-wall h e a t i n g r a t e s f o r small gimbal angles.
The model High Reynolds Number F a c i l i t y was then i n s t a l l e d .
Checkout
of t h e t r a n s o n i c f e a s i b i l i t y i s underway.
Although flow t r e n d s i n t h e supply tube a r e a s expected,
some p e c u l i a r i t i e s do e x i s t .
E x p l o r a t i o n of t h e s e p e c u l i a r i t i e s i s
expected a f t e r i n s t a l l a t i o n o f a d d i t i o n a l p r e s s u r e i n s t r u m e n t a t i o n .
Subsonic and s u p e r s o n i c t e s t s a r e expected t o b e g i n i n
e a r l y November.
2.
1 4 X 14-Tach T r f s o n i c Wind T u m e %
Phase I1 of 'TWT 295 occupied t h e 14-Fneh t u n n e l d u r i n g
October. This was a n i n v e s t i g a t i o n by Lockheed t o determine t h e e f f e c t s
of a s y s t e m a t i c v a r i a t i o n of geometric parameters on t h e l i n e a r aerodynamic
l o a d s of a cone-cylinder f r u s t u m - c y l i n d e r model c o n f i g u r a t i o n . Radial
and s u r f a c e p r e s s u r e d i s t r i b u t i o n s a r e t o be determined f o r a n g l e s o f
attack.
The t e s t i s i n p r o g r e s s w i t h a n a n t i c i p a t e d completion d a t e
of e a r l y November.
T o t a l r u n s t o d a t a a r e 1028,
3.
7 X 7-Inch B i s o n i c Wind Tunnel
An i n v e s t i g a t i o n by Wyle L a b o r a t o r i e s i s c o n t i n u i n g i n t h e
BWT on t h e s e r i e s o f w a l l mounted, s e m i c i r c u l a r s e c t i o n c y l i n d e r - f l a r e c y l i n d e r models t o determine, by flow v i s u a l i z a t i o n methods, t h e r e g i o n s
o f s e p a r a t e d flow and o s c i l l a t i n g shocks. T o t a l r u n s t o d a t e a r e 127.
4.
Thermal and Acoustic Simulation F a c i l i t y
Work i s s t e a d i l y p r o g r e s s i n g on support items such a s f a c i l i t y
h i g h p r e s s u r e p i p i n g and e l e c t r i c a l power i n s t a l l a t i o n , The c o n c r e t e pads
t o mount t h e r e c e n t l y a c q u i r e d s u r p l u s high p r e s s u r e t a n k s should be
f i n i s h e d i n time t o accommodate tank d e l i v e r y .
D e l i v e r y o f t h e h e a t e r i s s t i l l scheduled f o r mid-November,
b u t i t i s expected t o s l i p a t l e a s t one week because o f mechanical
It i s expected t h a t f i n a l p l a n t checkout
problems i n t h e f i n a l assembly.
Because of t h e a d d i t i o n
of t h e h e a t e r w i l l be made around mid-November,
o f a c o l d flow f a c i l i t y t o t h e same b u i l d i n g occupied by t h e helium h e a t e r ,
c e r t a i n m o d i f i c a t i o n s have been requested.
These items i n c l u d e an a d d i t i o n a l r o l l - u p door i n s t a l l e d i n t h e middle bay, a l a r g e c o n c r e t e pad
r e q u i r e d t o support a s s o c i a t e d heavy equipment, and a n a c o u s t i c a l l y i n s u l a t e d i n s t r u m e n t a t ion room,
�5.
Hot Flow T e s t F a c i l i t y
F i n a l m o d i f i c a t i o n s have been completed t o t h e h e a t e r .
T e s t i n g i s scheduled by R-AERO-AT a s t e s t hardware becomes a v a i l a b l e .
6.
Hypersonic Shock Tunnel
Diaphragms i n both C o r b l i n compressors were r e p l a c e d t o
avoid contaminating t h e g a s h a n d l i n g system w i t h o i l . Upon removing
t h e diaphragms, it was discovered t h a t two o f t h e t h r e e i n t h e 15,000
p s i machine had a l r e a d y f a i l e d . New diaphragms r e c e i v e d from t h e
manufacturer were i n s p e c t e d and r e t u r n e d because of i n f e r i o r q u a l i t y .
A s t u d y i s b e i n g conducted t o determine t h e b e s t m a t e r i a l a v a i l a b l e
w i t h t h e thought i n mind of f a b r i c a t i n g diaphragms in-house.
The helium p u r i f i c a t i o n system has n o t worked p r o p e r l y
It appears t h a t t h e timing mechanism i n s i d e t h e u n i t i s
thus f a r .
v e r y c r i t i c a l and was shaken o u t o f p o s i t i o n d u r i n g t r a n s p o r t a t i o o .
A f a c t o r y r e p r e s e n t a t i v e i s r e p a i r i n g the unit.
The 20 mm shock tube f a c i l i t y was p u t i n t o o p e r a t i o n a l
s t a t u s i n p r e p a r a t i o n f o r experimental t e s t i n g r e q u e s t e d by R-AERO-AE,
a s s o c i a t e d w i t h measurement of shock t u n n e l s t a g n a t i o n temperature by
o p t i c a l means.
Work i s c o n t i n u i n g on development o f an e x t e r n a l l y a c t i v a t e d
n o z z l e plug v a l v e .
I n i t i a l r e s u l t s a r e q u i t e promising.
D.
Thermal Environment Branch
1.
Saturn I
The summary r e p o r t of t h e thermal d a t a e v a l u a t i o n f o r t h e
S a t u r n I v e h i c l e s has been d r a f t e d . An p r e l i m i n a r y copy was forwarded
t o MSFC f o r review.
P u b l i c a t i o n of t h i s r e p o r t (CCSD TN-AE-65-115) i s
scheduled f o r November. P r e p a r a t i o n s have been i n i t i a t e d f o r t h e AS-201
flight.
2.
Saturn I B
a.
Stage S e p a r a t i o n Thermodynamics
Work i s p r o g r e s s i n g on p r e d i c t i n g p r e s s u r e on f l a t
p l a t e s caused by t h e impingement of a r o c k e t motor exhaust; axisymmetric
and two-dimensional models a r e being used i n an e f f o r t t o match e x i s t i n g
experimental d a t a . Moderate s u c c e s s has been o b t a i n e d w i t h t h e axisymm e t r i c model i n t h a t t h e p r e s s u r e p r o f i l e shape i s matched r e a s o n a b l y
w e l l ; however, t h e magnitudes o f t h e p r e s s u r e s a r e too l a r g e .
�Heat r a t e s and p r e s s u r e d i s t r i b u t i o n s on t h e S-IBIS-IVB
i n t e r s t a g e caused by impingement o f t h e S-IB retro-motor were p r e d i c t e d .
The p r e s s u r e d i s t r i b u t i o n s were o b t a i n e d u s i n g a Newtonian flow assumption;
h e a t i n g r a t e s were p r e d i c t e d u s i n g a f l a t p l a t e t u r b u l e n t flow a n a l y s i s .
A more e x t e n s i v e a n a l y s i s ~ f t h e problem i s under way.
b.
Thermal Environmental A n a l y s i s
An a n a l y s i s determining t h e maximum aerodynamic h e a t i n g
environment f o r t h e SA-207 v e h i c l e w i t h 205K t h r u s t engines was completed.
R e s u l t s show t h a t t h e magnitude o f t h e thermal environment w i l l be about
3 p e r c e n t g r e a t e r t h a n t h a t p r e v i o u s l y determined f o r t h e S a t u r n
v e h i c l e (200K e n g i n e s ) , Because o f t h e s i m i l a r i t y between t h e 205K
environment w i t h t h e 20QK d e s i g n c r i t e r i a environment, s e p a r a t e environmental d e s i g n c r i t e r i a f o r t h e 205K s e r i e s o f v e h i c l e s w i l l n o t be
established.
An i n v e s t i g a t i o n s f aerodynamic h e a t i n g p r e d i c t i o n
t e c h n i q u e s f a r hypersonic v e h i c l e s a t high a l t i t u d e s has been delayed.
The a p p r o p r i a t e e q u a t i o n s f o r c a l c u l a t i n g aerodynamic h e a t i n g i n f r e e molecular and s l i p f l a w w i l l be programmed a s time permits.
Continuum
flow w i l l be assumed a t p r e s e n t f o r c a l c u l a t i n g t h e upper s t a g e environments, T h i s procedure w i l l y i e l d s l i g h t l y c o n s e r v a t i v e h e a t i n g r a t e s .
Engine b e l l and a s p i r a t o r d a t a r e c e i v e d from c a l o r i m e t e r s
mounted o n t h e SA-9 and SA-10 v e h i c l e s have been i n v e s t i g a t e d and compared
w i t h p r e d i c t e d thermal environments used i n p r i o r a n a l y s e s (CCSD TB-AE-65191). S l i g h t adjustments were made i n t h e p r e v i o u s l y proposed a s p i r a t o r
and h e a t exchanger environments, I n a d d i t i o n , environments have been
e s t a b l i s h e d f o r each o f t h e s u p p o r t i n g bands on both the inboard and
outboard engines. These proposed H-1 engine environments on t h e S a t u r n
I B a r e scheduled t o be published i n November.
A more complete examination of t h e d a t a o b t a i n e d d u r i n g
t r a n s o n i c o p e r a t i o n a t AEDC has i n d i c a t e d t h a t t h e expected Mach number
and a l t i t u d e were n o t o b t a i n e d . T r a n s i e n t e x t e r n a l flow d u r i n g t h e
combustion e v e n t makes a l l d a t a q u e s t i o n a b l e , The t e s t i s c o n t i n u i n g ,
and a t t e m p t s w i l l be made t o o b t a i n v a l i d i n f o r m a t i o n a t a Mach number
o f 1,6.
A r e p o r t describing the r e s u l t s of the thin-film
r e s i s t a n c e thermometer c a l i b r a t i o n t e s t s r u n a t Hy-Cal Engineering i s
n e a r i n g completion, This r e p o r t w i l l be p u b l i s h e d a s CCSD TN-AE-65-113,
A t e c h n i c a l n o t e concerned w i t h t h e H-1 engine r a d i a t i o n
f o r nonequilibrium c o n d i t i o n s was completed i n rough d r a f t form.
Several
mathematical and computational d i f f i c u l t i e s encountered i n t h e c a l c u l a t i o n
o f t h e e m i s s i v i t y f o r s o l i d carbon p a r t i c l e s have been overcome.
Form
f a c t o r s f o r t h e g e n e r a l r a d i a t i o n program a r e being formulated.
�The s t u d y of t u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g i s
continuing.
P r e l i m i n a r y r e s u l t s have been o b t a i n e d f o r t h e c o n s t a n t
p r e s s u r e a n a l y s i s assuming chemical e q u i l i b r i u m c o n d i t i o n s . A t e c h n i c a l
b u l l e t i n t o be i s s u e d i n December p r e s e n t s t h e d e t a i l s o f t h e a n a l y s i s ,
a s w e l l a s a comparison of r e s u l t s f o r t h e f r o z e n and f l a m e - f r o n t
chemistry c a s e s .
c.
R e t r o r o c k e t Impingement Heating o n S-IB/S-IVB
Interstage
Aft
Heating r a t e s on t h e S-PB/S-IVB
a f t i n t e r s t a g e due t o
r e t r o r o c k e t exhaust impingement have been analyzed f o r P&VE by t h i s branch
(memo R-AERO-AT-65-3O),to determine whether t o add K o r ~ t h e r mi n s u l a t i o n
Since t h e h e a t i n g r a t e s agreed f a i r l y w e l l w i t h
to the a f t interstage.
Douglas-calculated h e a t i n g r a t e s , i t was decided t o add i n s u l a t i o n t o
v e h i c l e 201 and p o s s i b l y 202, A more d e t a i l e d a n a l y s i s of h e a t i n g t o
t h i s r e g i o n w i l l be performed i n a n a t t e m p t t o reduce h e a t i n g r a t e s .
There i s a danger t h a t , i f t h e i n s u l a t i o n i s l e f t on t h e f i r s t o r b i t a l
c o a s t m i s s i o n ( v e h i c l e 2 0 3 ) , t h e r e t r o r o c k e t s w i l l a b l a t e and e r o d e t h e
Korotherm i n s u l a t i o n such t h a t t h i s m a t e r i a l w i l l impinge upon and
contaminate t h e S-IVB t a n k w a l l s , This w i l l i n c r e a s e t h e a b s o r p t i v i t y
o f t h e p o i n t on t h e w a l l s r e s u l t i n g i n more s o l a r h e a t i n g t o t h e S-IVB,
t h u s i n c r e a s i n g t h e amount of hydrogen b o i l - o f f ,
R e s u l t s of t h e C o r n e l l
r e t r o r o c k e t t e s t s (memo R-AERO-AT-65-20) a r e expected t o be a v a i l a b l e
by February; it i s hoped t h a t t h i s experimental i n v e s t i g a t i o n , a s w e l l
a s t h e more d e t a i l e d a n a l y t i c a l study, w i l l b r i n g the h e a t i n g r a t e s down.
3.
Saturn ~B/Centaur
a.
Thermal Envi ronmental A n a l y s i s
An a n a l y s i s was s t a r t e d t o determine t h e maximum
aerodynami c h e a t i n g environment a s s o c i a t e d w i t h t h e proposed S a t u r n
U B / ~ e n t a u r c i s l u n a r Pegasus t r a j e c t o r y , C a l c u l a t i o n s show t h a t the
t o t a l aerodynamic h e a t i n g r e s u l t i n g from t h i s t r a j e c t o r y w i l l be l e s s
t h a n h a l f t h a t produced by t h e d e s i g n c i r t e r i a environment f o r t h e
AS-201 and AS-202 v e h i c l e s . Analyses were i n i t i a t e d i n an e f f o r t t o
r e f i n e t h e p u b l i s h e d aerodynamic h e a t i n g environment o f t h e S a t u r n
I ~ / ~ e n t a uVoyager
r
miss ion.
b.
H a Venting Study
The hazards a s s o c i a t e d w i t h t h e v e n t i n g of gaseous
hydrogen from t h e Centaur s t a g e o f t h e S a t u r n P ~ / ~ e n t a uhave
r
been
studied.
The r e s u l t s i n d i c a t e no flame hazard t o t h e v e h i c l e from t h e
vented H2 gas and v i r t u a l l y no p o s s i b i l i t y o f d e t o n a t i o n r e s u l t i n g from
e n t r a i n i n g t h e gaseous plume i n t h e c l u s t e r e d tank r e g i o n of t h e S-IB
stage.
These r e s u l t s w i l l be used i n determining t h e v e n t scheme t o
be used on t h e v e h i c l e .
�4.
Saturn V
a.
Plume R a d i a t i o n Study
A computer program has been w r i t t e n which a r r a n g e s a
l a r g e number of axisymmetric and two-dimensional m e t h o d - o f - c h a r a c t e r i s t i c s
plume s o l u t i o n s i n t o a n approximation o f t h e plume flow f i e l d f o r t h e
S-IC and S - I 1 s t a g e s , The o u t p u t from t h i s flow f i e l d program w i l l be
used i n t h e a n a l y s i s o f plume r a d i a t i o n , A flow f i e l d has r e c e n t l y
been c a l c u l a t e d and w r i t t e n on t a p e t o a s s i s t GE i n t h e development and
checkout of t h e r a d i a t i o n computer program,
b.
Base P r e s s u r e and Environment
The p o r t ion o f t h i s s t u d y cur r e n t l y under i n v e s t i g a t i o n
i n v o l v e s t h e t u r b u l e n t boundary l a y e r growth on nozzle w a l l s w i t h mass
injection.
The e f f e c t on t h e boundary l a y e r growth due t o t u r b i n e
exhaust gas i n j e c t i o n i n t h e F-1 engine i s being examined.
The F-1
c u r r e n t l y i n j e c t s t h e t u r b i n e exhaust i n t o t h e nozzle over approximately
t h e downstream h a l f of t h e contour through a s e r i e s o f 24 s l o t s . A
t u r b u l e n t boundary l a y e r program, i n c o r p o r a t i n g mass i n j e c t i o n through
d i s c r e t e s l o t s , w i l l be u t i l i z e d t o g e t an i n i t i a l approximation o f t h e
e f f e c t of the injection.
Because o f t h e e x t e n s i v e approximations i n
t h i s a n a l y s i s , a n o t h e r method assuming continuously d i s t r i b u t e d i n j e c t i o n
w i l l be programmed and t h e r e s u l t s compared w i t h t h e d i s c r e t e s l o t
a n a l y s i s . An e x t e n s i v e s e a r c h i s being conducted f o r the nozzle and
t u r b i n e exhaust c o n d i t i o n s a s r e q u i r e d f o r r e a l i s t i c i n p u t t o t h e above
programs.
The d i s c r e t e s l o t i n j e c t i o n program i s ready t o r u n and
w i l l be used a s soon a s the n e c e s s a r y i n p u t d a t a a r e assembled. A
s u b r o u t i n e w i l l then be w r i t t e n t o i n c o r p o r a t e t h e d i s t r i b u t e d i n j e c t i o n
a n a l y s i s i n t o t h e program,
c,
Heat T r a n s f e r and P r e s s u r e Measurements i n a Cavity
Formed by a Rocket Engine Exhaust
The l u n a r c a v i t y experimental program i s proceeding
a c c o r d i n g t o schedule, The t e s t s w i l l s t a r t immediately a f t e r completion
of t h e h i g h Reynolds number p i l o t s t u d y , which i s expected t o be November
15. I n i t i a l h e a t t r a n s f e r and p r e s s u r e c a l c u l a t i o n s have been s u p p l i e d
t o R-AERO-AFG f o r c a l i b r a t i o n purposes, and a drawing o f t h e sample
l u n a r c a v i t y has been g i v e n t o F a b r i c a t i o n f o r c o n s t r u c t i o n .
�d.
S-IC Stage ( S h o r t D u r a t i o n Base Heating T e s t )
The d e t a i l e d a n a l y s i s o f t h e t e s t d a t a from t h e Lewis
Research @ e n t e r \ 8 by 6 Foot Supersonic Tunnel has been completed and
w i l l soon be r e l e a s e d . A document i s now being w r i t t e n which w i l l
i n c l u d e a l l d a t a o b t a i n e d u s i n g t h e s h o r t d u r a t i o n S-IG model.
e.
S - I I Stage (Base Heating T e s t s )
The S - I 1 base h e a t i n g t e s t s a t MSFC were completed on
October 15, It i s planned t h a t t h e S-I1 model w i l l be used i n r e s e a r c h
t e s t s on c r a t e r h e a t i n g and then be r e t u r n e d to CAL f o r t e s t s t o d e t e r mine t h e f o r c e and p r e s s u r e on t h e i n t e r s t a g e s k i r t d u r i n g second p l a n e
separation.
5.
General
a.
A b l a t i o n Program
A d i g i t a l computer program i s being formulated f o r
a n a l y z i n g a b l a t i n g thermal p r o t e c t i o n systems, The program i s being
developed i n two phases.
Phase 1 w i l l produce a "Working Toolq>rogram
t o handle m a t e r i a l s f o r which experimental d a t a a r e a v a i l a b l e , w h i l e
Phase 11 w i l l produce a program having d i v e r s i f i e d t h e o r e t i c a l
capabilities.
The "Working Tool" program i s n e a r i n g product i o n s t a t u s .
Numerous checkout r u n s a r e being made t o e x e r c i s e a l l c a p a b i l i t i e s o f
t h e program, and t o a s c e r t a i n t h a t t h e l o g i c t o r u n c a s e s "back-to-back"
i s o p e r a t i n g properly.
The u s e r " Manual i s being published.
Two problems have r e c e n t l y been analyzed u s i n g t h i s
program.
The f i r s t involved d e t e r m i n a t i o n o f temperatures a t v a r i o u s
l o c a t i o n s on an R. O.T, type v e h i c l e f o r two r e - e n t r i e s .
Angle-of-attack
e f f e c t s were included. The second involved determining c o n v e c t i v e
h e a t i n g r a t e s on t h e Apollo Command Module f o r two S a t u r n V AS-501
re-entry trajectories.
Also, a s e p a r a t e h e a t p r o t e c t i o n system weight
t r a d e - o f f s t u d y i s being conducted u s i n g t h e "Working Tool? program.
b.
Thermo-Methods Analysis
- Flat-Plate
Modification
F u r t h e r p r o g r e s s has been made i n o b t a i n i n g t r a n s f o r m a t i o n s
which can be a p p l i e d t o f l a t - p l a t e s o l u t i o n s of t h e t u r b u l e n t momentum
i n t e g r a l e q u a t i o n t o o b t a i n axisymmetric s o l u t i o n s . Comparisons a r e being
made between t h i s transform method o f determining t h e t u r b u l e n t momentum
t h i c k n e s s on axisymrnetric bodies and a more complicated computer method
based on an i t e r a t i v e s o l u t i o n of t h e momentum i n t e g r a l equation.
P r e l i m i n a r y comparisons have i n d i c a t e d t h a t t h e transforms appear v a l i d .
More e x a c t and e x t e n s i v e comparisons a r e t o follow.
�c.
E q u i l i b r i u m Real Gas/Normal Shock Program f o r
S t a g n a t i o n P o i n t Heating
The g o a l of t h i s s t u d y i s t o develop t h e * c a p a b i l i t y t o
c a l c u l a t e s t a g n a t i o n p o i n t h e a t i n g - r a t e s f o r a blunt> body i n an e q u i l i b r i u m
r e a l gas flow f i e l d . E f f o r t was dev6ted t o s o l v i n g t h e laminar boundary
Two numerical
l a y e r e q u a t i o n s i n t h e s t a g n a t i o n r e g i o n o f t h e b l u n t body.
t e c h n i q u e s were used t o s o l v e the two-point boundary v a l u e problem r e s u l t i n g
from t h e f o r m u l a t i o n o f t h e boundary l a y e r e q u a t i o n s . D i g i t a l computer
programs were w r i t t e n f o r b o t h t e c h n i q u e s , and t h e r e s u l t i n g programs
were checked o u t .
S e v e r a l t e s t c a s e s were examined, and the r e s u l t s were
found t o a g r e e w i t h r e s u l t s p u b l i s h e d by o t h e r workers, T r a n s p o r t
p r o p e r t y c o r r e l a t i o n s were added t o both programs t o allow p r e d i c t i o n s
of h e a t i n g r a t e s i n a i r . Work continued on t h e g e n e r a l problem of
p r e d i c t i n g t r a n s p o r t p r o p e r t i e s f o r an a r b i t r a r y gas m i x t u r e ,
d,
Thermal Analysis s f t h e LFV P a r t i a l l y Enclosed Engine
Cluster
An a n a l y s i s has been i n i t i a t e d t o p r e d i c t t h e s t e a d y
s t a t e temperature d i s t r i b u t i o n s on r a d i a t i v e l y cooled r o c k e t n o z z l e s
which a r e c l u s t e r e d and p a r t i a l l y enclosed.
The v a r i o u s d i g i t a l computer programs t o be used i n
t h i s a n a l y s i s a r e being checked o u t on t h e MSFC computer system.
Version 1 3 ) .
(Fortran I V
-
e.
Cold Flow-Base Flow V i s u a l i z a t i o n T e s t s
An experimental program i s t o begin a t AEDC i n the
s p r i n g of 1966 which w i l l be used t o e v a l u a t e i n s t r u m e n t a t i o n techniques
i n t h e s e v e r e environment of t h e h i g h s h e a r , t u r b u l e n t flow r e g i o n
c r e a t e d by a four-nozzle c l u s t e r . A s p e c i a l t e s t c e l l w i l l be c o n s t r u c t e d
t h a t w i l l a l l o w r a t i o s of the c e l l ambient p r e s s u r e t o nozzle t o t a l
p r e s s u r e o f t h e o r d e r of 10 x lom4., This p r e s s u r e r a t i o i s s u f f i c i e n t
t o achieve a f u l l y "choked" c o n d i t i o n i n the base r e g i o n , Design
c o n s i d e r a t i o n s and c r i t e r i a o f t h e model and t e s t c e l l a r e d i s c u s s e d
i n MsFc/NASA Memorandum R-AERO-AT-65-18.
I n s t r u m e n t a t i o n techniques t h a t w i l l be e v a l u a t e d i n
t h i s t e s t program a r e a s follows:
(1)
-
developing r e l a t i v e l y
Boeing (NAS8-20079)
c o n v e n t i o n a l i n s t r u m e n t s t o measure p r e s s u r e ,
d e n s i t y , and flow d i r e c t ions.
�f.
-
(2)
P h i l c o (NAS8-20503)
developing a two-wire h o t w i r e
probe t o measure v e l o c i t y and flow d i r e c t i o n .
(3)
Brown (NAS8-20145)
developing a system t o measure
flow v e l o c i t y by doppler s h i f t of l i g h t s c a t t e r e d
from a l a s e r beam d i r e c t e d through t h e flow f i e l d .
(4)
Other systems and techniques a r e being e v a l u a t e d
f o r p o s s i b l e a p p l i c a t i o n t o t h e AEDC t e s t d .
-
Thermodynamics and Chemistry o f Reacting Gases
The s t u d y o f t h e gas mixing problem i s being conducted
along t h e following l i n e s :
(1)
Determine what a r e t h e m e c h a n i s t i c chemical
e q u a t i o n s d e s c r i b i n g t h e combustion p r o c e s s .
(2)
Determine which o f t h e two major methods o f
h a n d l i n g t h e chemistry o f t h e mixing problem i s
most r e a d i l y g e n e r a l i z e d .
(3)
Determine how t h e ~AsA/Lewis thermochemical program
can be segmented, (A computer program d e s c r i b i n g
t h e dynamics of mixing w i l l use a segment of t h e
Lewis program f o r t h e s o l u t i o n t o t h e chemistry
p a r t of t h e problem.)
A f i n i t e r a t e chemistry computer program was o b t a i n e d
through ~AsA/Lewis. T h i s program i s being made o p e r a t i o n a l on MSFC'S
computers f o r use i n t h e study o f I3rayqs f r e e z i n g c r i t e r i a .
g.
Computer Programs
An e n g i n e e r i n g r e p o r t i s b e i n g prepared t o document t h e
u t i l i z a t i o n o f a computer program, o b t a i n e d from NASA Lewis Research
C e n t e r , f o r the computation o f chemical e q u i l i b r i u m compositions of
r o c k e t exhaust plumes, P u b l i c a t i o n of t h i s r e p o r t i s scheduled f o r
December.
Work i s c o n t i n u i n g on t h e m o d i f i c a t i o n t o t h e c a l o r i m e t e r
d a t a r e d u c t i o n computer program (CU0014) on a low p r i o r i t y b a s i s . During
t h e p r e c e d i n g month, a l l o f t h e SA-10 s l u g c a l o r i m e t e r d a t a and one SA-10
membrane c a l o r i m e t e r d a t a were reduced w i t h t h e modified program. A
c u r s o r y examinat ion o f t h e d a t a i n d i c a t e s t h a t t h e r e d u c t i o n p o r t i o n of
t h e program i s o p e r a t i o n a l .
To d a t e , t h e p l o t r o u t i n e s have n o t been
added. P u b l i c a t i o n o f t h e s e m o d i f i c a t i o n s i s scheduled f o r December
1965, a s CCSD TN-AE-65-82.
�Documentation of c@NDA i s c o n t i n u i n g on a low p r i o r i t y
b a s i s , and i s approximately s i x t y p e r c e n t complete.
E.
Unsteady Aerodynamics Branch
1.
I n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Environment
Preliminary estimates of the Saturn V i n f l i g h t a c o u s t i c
environments have been completed. The environments cover a Mach range
of - 8 t o 2.2 f o r t h e v e h i c l e a t zero a n g l e o f a t t a c k , These environments
a r e being prepared f o r publication,
Wind
f l a r e b o d i e s have
t e s t s the effects
on s e p a r a t e d flow
t u n n e l s t u d i e s of s e p a r a t e d flow on cone c y l i n d e r
been i n i t i a t e d i n t h e MSFC 7-inch t u n n e l , From t h e s e
o f Reynolds number, Mach number, and model geometry
w i l l be d e l i n e a t e d ,
Base p r e s s u r e f l u c t u a t i o n measurements have been implemented
o n t h e t e s t "Saturn V Cold Flow Nozzle Aerodynamic Hinge Moment T e s t
AD3-64."
There w i l l be e i g h t f l u c t u a t i n g p r e s s u r e measurements l o c a t e d
i n one quadrant o f t h e base.
2.
Launch S i t e Acoustic Environment
The p r e d i c t i o n program f o r t h e s p a t i a l c o r r e l a t i o n f u n c t i o n s
on t h e v e h i c l e s u r f a c e f o r both t h e s t a t i c f i r i n g and launch, engine
g e n e r a t e d a c o u s t i c environment has been completed, Attempts t o reduce
t h e computing time have n o t been s u c c e s s f u l . The fundamental e q u a t i o n
i s being s i m p l i f i e d ,
A technique f o r p r e d i c t i n g t h e sound p r e s s u r e l e v e l r e c e i v e d
a t a f a r - f i e l d l o c a t i o n from a n a c o u s t i c , broadband, d i r e c t i o n a l , p o i n t
s o u r c e r a d i a t i n g i n t o a n inhomogeneous medium has been developed.
I n i t i a l r e s u l t s from t h i s program, r e c e i v e d t h i s week, a r e being compared
t o measured v a l u e s , P r e d i c t e d and measured r e s u l t s w i l l be compared
under a wide v a r i e t y o f c o n d i t i o n s t o e v a l u a t e t h e accuracy o f t h i s
technique.
3.
Panel F l u t t e r Aerodynamics
P r e l i m i n a r y p a n e l f l u t t e r t e s t s were conducted a t Langley
Research Center October 18 through October 22, 1965, on p a n e l s s i m i l a r
t o t h o s e on t h e S-IVB forward s k i r t . The p a n e l s t e s t e d had an a s p e c t
r a t i o (L/w) of 4.5 and were .032 inch t h i c k , The t e s t s were conducted
a t Mach 1.96 under v a r i o u s compressive s t r e s s and b u r s t i n g d i f f e r e n t i a l
pressure conditions.
�The r e s u l t s show t h a t t h e p a n e l s f l u t t e r e d w e l l below
dynamic p r e s s u r e s encountered d u r i n g f l i g h t (maximum dynamic p r e s s u r e
b e i n g 780 p s f ) . With z e r o p r e s s u r e d i f f e r e n t i a l , f l u t t e r was encountered
a t 180 p s f when t h e p a n e l was loaded t o c r i t i c a l buckling c o n d i t i o n s .
Applying a p r e s s u r e d i f f e r e n t i a l o f .25 p s i had no e f f e c t on t h e minimum
f l u t t e r q , and a A p of .35 p s i had l i t t l e e f f e c t . However, when a
p r e s s u r e d i f f e r e n t i a l of .40 p s i t o .50 p s i was a p p l i e d , f l u t t e r was
o b t a i n e d a t a q of 720 p s f , b u t t h i s i s n o t t h e minimum f l u t t e r q s i n c e
t h e p a n e l s could n o t be loaded t o t h e c r i t i c a l buckling Bsad w i t h t h i s
pressure d i f f e r e n t i a l applied.
The a d d i t i o n o f a v i s c o - e l a s t i c compound was a l s o t e s t e d .
When a compound t h i c k n e s s o f .070 inch was a p p l i e d , t h e p a n e l f l u t t e r e d
a t 400 p s f , under c r i t i c a l buckling load and z e r o p r e s s u r e d i f f e r e n t i a l
conditions.
No n o t i c e a b l e e f f e c t was recorded when t h e p r e s s u r e
d i f f e r e n t i a l was increased.
4.
S a t u r n V Ground Winds
A p r e s e n t a t i o n was g i v e n t o c e n t e r management by R-AERO and
R-P&VE on t h e S a t u r n V ground wind problem, The r e s u l t i n g a c t i o n items
a r e summarized below:
a. A l l v e h i c l e f r e e - s t a n d i n g c o n d i t i o n s a t KSC should be
used t o measure wind-induced o s c i l l a t i o n .
b.
P&VE w i l l i n v e s t i g a t e t h e a d d i t i o n o f mechanical dampers
f o r use a s s a f e t y devices.
c. R-AERO w i l l i n v e s t i g a t e t h e a d d i t i o n o f aerodynamic
" f i x e s " t o r e l i e v e t h e problem.
d.
The bending moments f o r 1.5 p e r c e n t s t r u c t u r a l damping
w i l l be p r e d i c t e d .
e.
MSC w i l l be n o t i f i e d o f t h e probable ground winds program.
f . Wind r e s t r i c t i o n s f o r S a t u r n v e h i c l e s 501, 502, and 503
should be analyzed and e v a l u a t e d .
5.
S a t u r n I ~ / ~ e n t a uGround
r
Winds Model
R-AERO-AU has r e c e i v e d a d e s i g n drawing o f t h e S a t u r n
m / c e n t a u r ground winds model from Atkins and M e r r i l l , Inc.
Upon
approval of t h e drawing by R-AERO-AU, Atkins and M e r r i l l w i l l s t a r t
c o n s t r u c t i o n of t h e model.
�Atkins and M e r r i l l has r e q u e s t e d a t h i r t y - d a y e x t e n s i o n
t o t h e model d e l i v e r y d a t e . This was approved by R-AERO-AU because
Marshall was approximately one month l a t e i n supplying them w i t h f u l l
s c a l e d e s i g n information.
The d e l i v e r y d a t e i s now s e t f o r January 30,
1966.
6.
A e r o e l a s t i c C h a r a c t e r i s t i c s o f Vehicle 203
Correspondence was r e c e i v e d from M r . E r i c i s s o n r e l a t i n g t o
It i s M r . E r i c i s s o n o s o p i n i o n t h a t
a p o t e n t i a l problem of v e h i c l e 203.
i f t h e v e h i c l e f l i e s a t a nominal 4 O a n g l e s f a t t a c k through t h e Mach
1.0, t h e v e h i c l e w i l l e x p e r i e n c e s e v e r e aerodynamic
number range o f 0,8
i n s t a b i l i t y . The p r o b a b i l i t y o f occurrence o f i n s t a b i l i t y d u r i n g 203
a s c e n t i s f a i r l y low s i n c e t h e v e h i c l e must meet t h e c o n d i t i o n s o u t l i n e d
above. N e v e r t h e l e s s , a l i m i t e d experimental program has been i n i t i a t e d
t o v e r i f y M r . Ericisson's hypothesis.
-
7.
Two-Dimens i o n a l Cylinder
Data r e d u c t i o n i s c o n t i n u i n g a t t h e M a r t i n Company. Recent
correspondence on MSFC c o n t r a c t s i n d i c a t e s t h a t t h e c o n t r a c t o r e x p e c t s
o v e r r u n o f approximately $30,000.
Since t h e o v e r r u n was n o t a n t i c i p a t e d ,
no allowance was made i n t h e ranch's budget.
It i s p o s s i b l e t h a t a
p o r t i o n of t h e amount may be o b t a i n e d from t h e Center fund f o r c o n t r a c t
overruns
VI,
DYNAMICS AND FZIGHT MECHANICS DIVISION
A.
Dynamics A n a l y s i s Branch
1.
Saturn I B
a. A memo has been completed r e p o r t i n g t h e r e s u l t o f
a d d i t i o n a l s l o s h i n g parameters f o r S a t u r n LB. A bending a n a l y s i s of
AS-205 f i r s t f l i g h t s t a g e has been completed and w i l l be d i s t r i b u t e d
A mem d e s c r i b i n g the e f f e c t o f t h e
w i t h i n t h e n e x t r e p o r t period.
c o n t r o l system on v e h i c l e n a t u r a l f r e q u e n c i e s has been published.
Sloshing parameters f o r t h e two s t a g e s of f l i g h t o f t h e
b.
AS-205 v e h i c l e i s n e a r i n g completion.
The parameters t h u s f a r c a l c u l a t e d
i n c l u d e ( 1 ) parameters of t h e f i r s t mode o f o s c i l l a t i o n f o r t h e 70" Lox
Tanks, 70" Fuel Tanks and 105" Lox Tank and ( 2 ) parameters o f t h e f i r s t ,
second, and t h i r d modes f o r t h e S-IVB s t a g e tanks. A r e p o r t w i l l be
d i s t r i b u t e d w i t h i n t h e n e x t month according t o t h e schedule agreed upop
by R-AERO-D and R-ASTR-F.
A s i m i l a r s t u d y f o r AS-206 has been s t a r t e d
and w i l l be completed w i t h i n t h e n e x t month. A bending a n a l y s i s o f t h e
second f l i g h t s t a g e o f AS-202 and AS-203 i s n e a r i n g completion.
�2.
Saturn V
a. A s t u d y has been made u s i n g t h e computer program developed
e a r l i e r which c a l c u l a t e s t h e c o n t r o l g a i n s w i t h f i l t e r s f o r t h e rigid-body
A
case.
The m i s s i l e c o n f i g u r a t i o n used was t h e S a t u r n AS-504 v e h i c l e .
comparative s t u d y was made a t t = 75.117 and 83.633 sec. f o r t h e c a s e
w i t h o u t f i l t e r s and f o r a body-fixed accelerometer u s i n g two d i f f e r e n t
The c o n t r o l frequency was v a r i e d between 0.85 cps
f i l t e r configurations.
and 0.20 c p s , and t h e e f f e c t s f v a r y i n g t h e accelerometer h o e a t i o n and
t h e damping was shown. The r e p o r t i s being prepared.
b, The RSS bending moment d e s i g n d a t a f o r AS-506 a r e being
computed f o r a nominal t r a j e c t o r y u s i n g a new s y n t h e t i c wind p r o f i l g f o r which
t h e l i n e a r wind buildup begins a t ground l e v e l and blends t a n g e n t i a l l y
i n t o t h e s h e a r buildup envelope. The g u s t i s r e p r e s e n t e d by a one-minusc o s i n e b u i l d u p and t a i l - o f f w i t h a c o n s t a n t p l a t e a u i n between, Ten
time p o i n t s have been chosen f o r i n v e s t i g a t i o n f o r t h i s s t u d y , which i s
being conducted t o determine t h e wind p r o f i l e e f f e c t on t h e d e s i g n
response values.
c. A t r a j e c t o r y - c o n t r o l s i m u l a t i o n program on t h e h y b r i d
computer i s being developed, A major problem caused by t h e s h o r t a g e o f
memory l o c a t i o n s i n t h e p r e s e n t equipment i s t h e s i m p l i f i c a t i o n of t h e
assumptions and e q u a t i o n s normally used. A more complete s i m u l a t i o n
f o r t h e new hybrid computer scheduled t o a r r i v e i n June i s a l s o being
developed.
d. A complete f i r s t s t a g e t r a j e c t o r y has been r u n on t h e
DYNASAR six-degrees-of-freedom t r a j e c t o r y - c o n t r o l s i m u l a t i o n . A few
programming and d a t a i n p u t e r r o r s found a r e b e i n g c o r r e c t e d .
A good r u n
i s a n t i c i p a t e d s h o r t l y , completing t h e f i r s t phase o f t h e program.
e. Work i s c o n t i n u i n g on an e l a s t i c body response program
which c o n s i d e r s g u s t p e n e t r a t i o n e f f e c t s .
f , The study o f t h e S a t u r n V d e t a i l wind p r o f i l e s i s
c o n t i n u i n g on h i g h speed computers. The purpose o f t h i s s t u d y i s two-fold:
(1) t o determine t h e c h a r a c t e r i s t i c s and e v a l u a t e t h e v a r i o u s S-V c o n t r o l
systems, and ( 2 ) t o h e l p develop a b e t t e r wind p r o f i l e and s t a t i s t i c a l
approach f o r v e h i c l e response s t u d i e s .
B a s i c r e s u l t s show t h a t accelerometer c o n t r o l y i e l d s
5-7 p e r c e n t bending moment r e d u c t i o n w h i l e A minimum guidance y i e l d s
about 2-4 p e r c e n t bending moment r e d u c t i o n .
g. Phase r o o t l o c i s t u d i e s f o r t h e v a r i o u s c o n t r o l system
f o r AS-501 have been completed.
The r e s u l t s a r e being p l o t t e d , and a
r e p o r t i s being w r i t t e n ,
�h. A bending mode and s h e l l - f l u t t e r a n a l y s i s o f t h e S - I D
s h e l l s t r u c t u r e i s i n progress.
Plans a r e n e a r i n g completion f o r f u r t h e r
t e s t i n g o f the Apollo s p a c e c r a f t t o e s t a b l i s h t h e bending c h a r a c t e r i s t i c s
S e r v i c e Module I n t e r f a c e . These t e s t s w i l l be
o f t h e Command Module
performed by C h r y s l e r ; t e s t requirements a r e b e i n g s e t by t h e CDSF
committee.
T e s t d a t a from t h e o n e - f o r t i e t h s c a l e Langley model have
been r e c e i v e d .
P r e p a r a t i o n s a r e underway t o analyze t h i s model i n
support of t h e ground winds e f f e c t s t u d i e s of R-AERO-AU.
-
i, A study has been made t o determine t h e e f f e c t s o f
i n c l u d i n g t h e LEM f l e x i b i l i t y v i b r a t i o n a n a l y s e s of t h e S a t u r n V
vehicle.
A l l f l i g h t s t a g e s were included i n t h e study. The r e p o r t
on t h i s s t u d y w i l l be d i s t r i b u t e d w i t h i n t h e n e x t r e p o r t p e r i o d , The
p r e t e s t a n a l y s i s o f t h e Conf. III (S-IVIB and above) dynamic t e s t s has
been r e c e i v e d from Boeing f o r review, S e v e r a l e r r o r s were found, which
t h e c o n t r a c t o r was i n s t r u c t e d t o c o r r e c t .
j,
A bending mode and s h e l l - f l u t t e r a n a l y s i s , i n c l u d i n g
t h e e f f e c t s of r i n g s and s t i n g e r s , has been completed f o r t h e forward
s k i r t o f t h e S - I 1 s t a g e s , R e s u l t s o f t h i s a n a l y s i s have been published.
3.
General
a. A s t u d y i s being made t o c a l c u l a t e t h e c o n t r o l g a i n s
w i t h f i l t e r s t h a t i n c l u d e t h e bending v i b r a t i o n of t h e v e h i c l e .
The
e q u a t i o n s a r e being d e r i v e d , and e v e n t u a l l y a computer program w i l l be
w r i t t e n t o c a l c u l a t e t h e c o n t r o l gains. A study w i l l t h e n be made t o
c a l c u l a t e t h e c o n t r o l g a i n s and t h e r i g i d body case w i l l be compared
with t h e e l a s t i c case,
b.
The r o t a r y s l o s h problem w i t h a n o n l i n e a r s p r i n g and
o s c i l l a t i n g mass p o i n t s r o l l i n g on a guided s u r f a c e of p a r a b o l i c form
i s b e i n g i n v e s t i g a t e d f o r S a t u r n V, The r e p o r t was s t u d i e d f o r g e n e r a l
i n f o r m a t i o n and t h e e q u a t i o n s of motion were w r i t t e n f o r a r i g i d v e h i c l e
study. The e q u a t i o n s a r e being programmed f o r t h e analog computer,
c, A study t o determine optimum g a i n s f o r r i g i d body
r e s p o n s e i s n e a r i n g completion, The f i n a l computer r u n s w i l l be made
s h o r t l y and t h e r e s u l t s r e l e a s e d i n a r e p o r t .
d. A program i s b e i n g checked o u t which w i l l i n c l u d e t h e
e l a s t i c e f f e c t s i n t h e d e t e r m i n a t i o n of optimum g a i n s f o r v e h i c l e response.
4.
Contractors
a.
Northrop
Work i s c o n t i n u i n g on t h e low g s l o s h study d u r i n g S-IVB
o r b i t , No r e s u l t s have been o b t a i n e d a t t h i s time. An e x t r a p o l a t e d low
g s l o s h model i s used f o r t h i s s t u d y ,
�b,
General Dynamics
The work on t h e n o n l i n e a r c h a r a c t e r is t i c s o f s l o s h i n g
p r o p e l l a n t i s c o n t i n u i n g , b u t no new r e s u l t s a r e y e t a v a i l a b l e .
A c o n t r a c t was l e t t o conduct a parameter s t u d y o f t h e
low g s l o s h models d u r i n g S - I n o r b i t t o determine a more r e a l i s t i c
s l o s h model,
c.
North American
A semi-annual r e p o r t c o n t a i n i n g r e s u l t s f o r t h e f r e e
o s c i l l a t i o n i n a c y l i n d r i c a l tank was r e c e i v e d . The b a s i c r e s u l t s
i n d i c a t e t h a t t h e frequency i s n o n l i n e a r o n l y i n t h e second o r d e r ; t h e
f i r s t o r d e r form i s missing.
The development o f a numerical procedure f o r s o l v i n g
n o n l i n e a r a l g e b r a i c e q u a t i o n s i s proceeding.
Some d i f f i c u l t y i s being
experienced i n g e t t i n g good convergence of some r o o t s .
A multi-beam bending program was d e l i v e r e d d u r i n g t h e
work p e r i o d .
There a r e s t i l l e r r o r s i n t h e program which should be
c o r r e c t e d soon.
B.
C o n t r o l Theory Branch
1.
Saturn I B
a. A s t u d y o f AS-206 t o determine t h e e f f e c t o f d i r e c t i o n a l
winds o n bending moments and v e h i c l e r e s p o n s e s f o r t h e max q a time p o i n t
i s i n progress.
The d a t a o b t a i n e d from t h i s s t u d y w i l l be f u r n i s h e d
P&VE t o determine i f t h e s t r u c t u r a l a j p l i m i t s a r e changed due t o t h e
v a r i a t i o n i n Mach number and dynamic p r e s s u r e r e s u l t i n g from t h e v a r i o u s
wind d i r e c t i o n s and wind speeds. Upon r e c e i p t of t h e a l p l i m i t a t i o n s ,
wind speed r e s t r i c t i o n s ( i f any) w i l l be determined f o r each wind d i r e c t i o n .
~ mff3,
b, Using t h e AS-206 d a t a , t h e c o e f f i c i e n t s , m ' and
have been i n v e s t i g a t e d t o g a i n some i n s i g h t i n t h e i r u s e s and t o determine
t h e e f f e c t s of s m a l l changes i n i n p u t d a t a .
The behavior o f m ' f 3 / ~ ' a s
a f u n c t i o n o f mass l o s s was determined. Also, methods f o r e a s i e r h a n d l i n g
of t h e aerodynamic d i s t r i b u t i o n s f o r p e r t u r b e d v a l u e s o f normal f o r c e
c o e f f i c i e n t and c e n t e r o f p r e s s u r e have been i n v e s t i g a t e d .
c. Vehicle responses and bending moments f o r f l i g h t times
corresponding t o Mach 1, max q , a n d j u s t b e f o r e inboard engine c u t o f f
a r e b e i n g determined f o r a cross-wind a t v a r i o u s wind speeds.
These d a t a
w i l l s u p e r s e d e d a t a p r e v i o u s l y published i n R-AERO-DCC-26-65, August 1 2 ,
1965.
�d , A g e n e r a l updating of t h e S a t u r n I B r i g i d body c o n t r o l
r e s p o n s e s t u d i e s w i l l be i n i t i a t e d when new mass and t r a j e c t o r y d a t a
based on updated c o n t r o l w e i g h t s a r e r e c e i v e d ,
e. A study has been i n i t i a t e d t o determine t h e maximum
i n f t i a l c o n d i t i o n s a t s e p a r a t i o n due t o a c r i t i c a l l y timed engine
f a i l u r e i n t h e I B s t a g e , T h i s s t u d y w i l l be s i m i l a r t o t h a t performed
on S a t u r n V,
f , The documentation of t h e SA-203 s e p a r a t i o n c o n t r o l
s t a t i s t i c a l a n a l y s i s has been completed, The r e s u l t s show t h a t b i a s i n g
t h e a n g l e of a t t a c k s t r o n g l y i n f l u e n c e s t h e s t a t i s t i c a l c h a r a c t e r i s t i c s
o f t h e p o s t s e p a r a t i o n a t t i t u d e and a t t i t u d e r a t e e x c u r s i o n s , The
documentation c a r r Fes a recommendat ion t h a t t h e SA-203 £1i g h t p r o f i l e
be shaped such a s t o b i a s o u t t h e no-wind a n g l e of a t t a c k a t f i r s t
stage separation.
g.
S t a b i l i t y s t u d i e s a r e s t i l l i n p r o g r e s s on v e h i c l e s
SA-203 and AS-204 u s i n g p r e l i m i n a r y g a i n s and f i l t e r s ,
2.
u rt
S a t u r n 1 ~ / ~ ea n
Estimated r i g i d body c o n t r o l responses and bending moments
September 30, 1965.
have been documented i n Memo No. R-AERO-DCC-30-65,
These d a t a a r e f o r time p o i n t s corresponding t o max qCl and max q f o r t h e
proposed c o n f i g u r a t i o n s I I B ( t h e lengthened v e r s i o n ) and 111 ( t h e
lengthened and widened v e r s i o n ) .
3.
Saturn V
a. A s t u d y has been performed t o i n v e s t i g a t e t h e maximum
t r a n s i e n t s o c c u r r i n g a t S-Ic/s-11s e p a r a t i o n due t o a n engine f a i l u r e
o c c u r r i n g a t such a time b e f o r e s e p a r a t i o n a s . t o cause t h e l a r g e s t
magnitude o f t h e t r a n s i e n t t o occur a t t h e time o f p h y s i c a l s e p a r a t i o n .
R e s u l t s o f t h e study i n d i c a t e t h a t maximum p i t c h r a t e s r e a c h approximately
4 d e g r e e s p e r second and the a t t i t u d e e r r o r approaches 12 d e g r e e s a t
separation.
The s t u d y was documented i n Memo No, R-AERO-DCC-34-65.
b. An i n v e s t i g a t i o n h a s been made t o determine t h e impact
t h a t a s t a g g e r e d shutdown sequence f o r t h e S-IC s t a g e e n g i n e s might have
on s t a g e s e p a r a t i o n . As was expected, t h e s t a g g e r e d shutdown sequence
has no s i g n i f i c a n t e f f e c t on t h e s e p a r a t i o n dynamics. The r e s u l t s of
t h e i n v e s t i g a t i o n have been documented,
c. The s t u d y t o determine t h e maximum e x c u r s i o n s a t
s e p a r a t i o n due t o a c r i t i c a l l y timed engine f a i l u r e b e f o r e s e p a r a t i o n
i s b e i n g extended t o determine t h e engine f a i l u r e i n t e r v a l which w i l l
l e a d t o second s t a g e a t t i t u d e e x c u r s i o n g r e a t e r than 35 d e g r e e s , t h e
p l a t f o r m l i m i t i n yaw.
�4.
General
a.
The development o f a d i g i t a l program t h a t w i l l compute
t h e e x a c t c o n t r o l g a i n s f o r any s p e c i f i e d c o n t r o l frequency and damping
and a l s o t h e r e s u l t i n g t r a n s i e n t response t o a g i v e n wind i n p u t has been
initiated.
The feedback ( c o n t r o l law) can c o n t a i n any combination o f t h e
f o l l o w i n g sensed v a r i a b l e s : a t t i t u d e , a t t i t u d e r a t e , a c c e l e r a t i o n , v e l o c i t y ,
p l a t f o r m a c c e l e r a t i o n , p l a t f s r m v e l o c i t y , and a n g l e o f a t t a c k . The t r a n s f e r
f u n c t i o n s t h a t w i l l be used i n t h i s program a r e being d e r i v e d .
b. A c o n t r o l system w i t h bending c o o r d i n a t e feedback and a n
i d e a l t h r u s t v e c t o r c o n t r o l was e f f e c t i v e i n reducing t h e bending moment.
However, w i t h t h e a d d i t i o n o f engine dynamics, t h e system becomes u n s t a b l e
f o r the g a i n s v a l u e s r e q u i r e d t o reduce t h e bending moment. The i n c l u s i o n
of a second o r d e r f i l t e r d i d n o t e f f e c t i v e l y s t a b i l i z e t h e system w i t h
a c t u a t o r dynamics, The r e s u l t s s f t h i s s t u d y have been summarized i n a
memorandum,
c. An Aero I n t e r n a l Note d e s c r i b i n g t h e a n a l y t i c a l method
and t h e d i g i t a l program used i n t h e s e p a r a t i o n c o n t r o l s t a t i s t i c a l
a n a l y s i s i s being w r i t t e n ,
d o A four-week course i n d i g i t a l computer l o g i c was a t t e n d e d .
An i n s i g h t i n t o t h e o p e r a t i o n of d i g i t a l c o n t r o l s was gained by t h e
a t t e n d e e through s t u d y o f g a t i n g , l o g i c , and a r i t h m e t i c c i r c u i t s .
e , The d i g i t a l runs f o r t h e minimum d r i f t c o n s t r a i n e d
bending moment problem have been e s s e n t i a l l y completed, and t h e d a t a
are b e i n g reduced, P r e l i m i n a r y work on a write-up has been s t a r t e d .
f . The problem o f d e s i g n i n g i d e a l c o n t r o l systems f o r
nonautonomous p l a n t s w i t h q u a d r a t i c performance c r i t e r i a i s b e i n g
continued.
The d i g i t a l program f o r t h e IBM 7094 i s being debugged and
a t e s t c a s e r u n f o r a checkout. I n p u t d a t a a r e being prepared f o r a
system i n c l u d i n g two bending modes and a c t u a t o r dynamics.
The p o s s i b i l i t y o f u s i n g Ericksons method o f unsteady
g.
a i r l o a d s i n t h e r e s p o n s e and s t a b i l i t y c a l c u l a t i o n s was i n v e s t i g a t e d .
P r e l i m i n a r y s t u d i e s i n d i c a t e t h a t i t w i l l be p o s s i b l e t o i n c l u d e t h e
e f f e c t o f flow s e p a r a t i o n i n response s t u d i e s f o r t h e S a t u r n I B v e h i c l e
and good agreement between t h e o r y and experiment w i l l r e s u l t .
Preliminary
r e s u l t s were covered b r i e f l y i n t h e l a s t q u a r t e r l y review.
5.
Contractors
a.
Lockheed
The S a t u r n ~ ~ / @ e n t a iunrs u l a t i o n p a n e l s s e p a r a t i o n s t u d y
has been completed.
Results indicate t h a t the panels w i l l separate
satisfactorily.
�Documentation of t h e f i l t e r s and o t h e r m o d i f i c a t i o n s t o
t h e B-2 deck has been d r a f t e d , Copies o f t h e d i g i t a l deck which produces
t h e n e c e s s a r y f i l t e r i n p u t d a t a t o t h e B-2 deck have been r e c e i v e d .
A t a s k assignment h a s been made t o e v a l u a t e t h e e f f e c t
o f t h e f i l t e r s on t h e r i g i d body responses so t h a t e s t i m a t i o n s of t h e
f i l t e r e f f e c t s can be a p p l i e d t o p r e v i o u s s t u d i e s performed without t h e
f i l t e r simulations,
Lockheed has developed a n o n l i n e a r f i l t e r t h a t p r o v i d e s
i n f i n i t e a t t e n u a t i o n of s i g n a l s whose frequency i s above t h e f i l t e r
c u t o f f frequency. The purpose of t h i s s t u d y i s t o (1) improve t h e
f i l t e r , ( 2 ) d e f i n e f i l t e r l f m i t a t i o n s , ( 3 ) e v a l u a t e t h e f i l t e r 5 performance, and ( 4 ) i n v e s t i g a t e t h e f i l t e r f o r u s e i n t h e c o n t r o l system o f a
S a t u r n type v e h i c l e .
Since t h i s s t u d y has j u s t begun, no p r o g r e s s
r e p o r t s have been r e c e i v e d .
b.
-
Northrop
NAS8-20082, (Schedule Order 4/71, "Bending
and S l o s h i n g Analysf s , S a t u r n I B V e h i c l e , SA-203
Booster F l i g h t ' "
The o b j e c t i v e o f t h i s study i s t o determine t h e s t a b i l i t y
requirements f o r t h e SA-203 v e h i c l e f o r f i r s t s t a g e f l i g h t .
The f o l l o w i n g
t a s k s were accomplished b e f o r e t h i s r e p o r t i n g p e r i o d :
(1)
Raw d a t a was processed t o o b t a i n parameters f o r
i n p u t t o r o o t l o c u s d i g i t a l program.
(2)
S e v e r a l computer programs were modified and checked
t o handle a d d i t i o n a l bending modes and s l o s h modes.
(3)
The h i g h e r bending modes and s l o s h modes were
i n v e s t i g a t e d f o r coupling e f f e c t s and a p r a c t i c a l
s t a b i l i t y a n a l y s i s procedure was devised.
(4)
S t a b i l i t y and g a i n requirements f o r gyro c o n t r o l
a t t h e 20 s e c . , 80 sec., and 100 sec. time p o i n t s
were determined and t h e s t a b i l i t y o f t h e upper
bending modes was v e r i f i e d .
The f o l l o w i n g t a s k s were accomplished d u r i n g t h i s
r e p o r t i n g period:
(1)
Gain s e l e c t i o n and f i l t e r d e s i g n a t t h e 60 sec.
time p o i n t was completed and the s t a b i l i t y o f t h e
upper bending modes checked.
�c.
(2)
A r o o t l o c u s study t o determine g a i n and f i l t e r
requirements a t t h e 60 sec. and 80 sec. time p o i n t s
f o r accelerometer c o n t r o l and t h e 140 sec. time
p o i n t f o r gyro c o n t r o l i s p r o g r e s s i n g s a t i s f a c t o r i l y .
(3)
A s t u d y t o determine t h e i n p u t requirements f o r t h e
f l e x i b l e body t r a n s i e n t response program was i n i t i a t e d .
Lockheed
- NAS8-20082,
(Schedule Order #2)
(1) Task A ( a ) , "Study t o Reduce Bending Moments Via
C o n t r o l System Design, " Constant C o e f f i c i e n t Case
Converged r u n s have been made f o r a t e n t h degree
performance c r i t e r i o n over a 38-second i n t e r v a l .
The i n p u t d i s t u r b a n c e
The
was of t r i a n g u l a r form w i t h t h e 8.5' peak o c c u r r i n g a t 15 seconds.
c o n t r o l f o r t h i s r u n a t t a i n e d a m a x i m u m v a l u e o f 52 p e r c e n t o f t h e l i m i t
v a l u e and produced a maximum d r i f t r a t e of 1.74 m/s,
A comparative r u n
u s i n g a t t i t u d e c o n t r o l produced maximm d r i f t r a t e o f 20 m/s,
A curve f i t o f t h e c o n t r o l a s a f u n c t i o n o f t h e
s t a t e v a r i a b l e s produced a t h i r d - d e g r e e polynomial (no c r o s s product
terms were allowed) w i t h a v e r y good f i t except a t t h e upper end p o i n t s .
E f f o r t s w i l l be continued t o f i n d a curve f i t t h a t i n c l u d e s t h e c r o s s
product terms.
A r u n w i l l be made t o o b t a i n t h e system r e s p o n s e
t o t h e wind i n p u t u s i n g a d r i f t minimum c o n t r o l . The responqes o b t a i n e d
by use of d r i f t minimum and performance c r i t e r i a w i l l be compared f o r
performance c h a r a c t e r i s t i c s .
(2)
Task A(b) , V a r i a b l e C o e f f i c i e n t Case
A comparison was made of t h e r e s u l t s o b t a i n e d from
t h e Ames deck, which u s e s an i t e r a t i o n procedure t o o b t a i n a s o l u t i o n ,
and t h e continuous i n t e g r a t i o n s o l u t i o n o f the d i f f e r e n t i a l e q u a t i o n s .
This comparison i n d i c a t e d t h a t t h e u s e o f a r e l a t i v e l y s h o r t time s t e p
i s r e q u i r e d i n t h e Ames deck f o r c o r r e c t r e s u l t s .
F u r t h e r u s e of t h e Ames deck w i t h t h e s h o r t t i m e
s t e p s n e c e s s i t a t e s a reprogramming o f t h e t a p e s t o r a g e i n p u t - o u t p u t
procedure t o p r o v i d e more e f f i c i e n t use o f machine time.
( T h i s work i s
b e i n g performed.)
Also, t h e p r e v i o u s l y used r e l a t i v e w e i g h t i n g s i n t h e
performance c r i t e r i o n a r e i n e r r o r and must b e r e d e f i n e d ,
Runs w i l l be
made u s i n g t h e r e d e f i n e d we i g h t i n g s and o t h e r t y p i c a l i n p u t winds t o
determine t h e degree o f s e n s i t i v i t y o f t h e c o n t r o l law t o t h e i n p u t .
�(3)
Task B , "Generation o f a Graphical o r A n a l y t i c a l
Formulation o f Peak Vehicle ~ e s p o n s e s "
The o b j e c t i v e of t h i s study i s t o determine a
It was determined
g e n e r a l method f o r p r e d i c t i n g peak v e h i c l e responses.
t h a t t h e maximum moment u s i n g r i g i d body e q u a t i o n s w i t h c o n s t a n t c o e f f i c i e n t s w i l l occur a t t h e f i r s t break i n t h e wind curve ( t l ) o r a t a l a t e r
time ( t 2 ) depending onby on t h e c o n t r o l frequency and v e h i c l e v e l o c i t y ,
Maximum v a l u e s o f t h e a n g l e of a t t a c k and t h e engine gimbal a n g l e a t
t h e s e two times can t h e n be o b t a i n e d from a l i n e a r combination o f t h r e e
s t a t e variables.
The s t a t e v a r i a b l e s a r e e v a l u a t e d from c o e f f i c i e n t s
p l o t t e d v e r s u s c o n t r o l frequency, v e h i c l e v e l o c i t y , and a s p e c i f i e d d r i f t r o o t .
Use of t h e s e g r a p h i c a l d a t a p e r m i t s d i r e c t c a l c u l a t i o n of bending
moments,
This study i s almost complete, and t h e r e s u l t s a r e being
documented,
(4)
Task D, "Nonlinear Accelerometer f o r b a d ~ e l i e f "
The o b j e c t i v e o f t h i s t a s k i s t o determine t h e
bending moment r e d u c t i o n o b t a i n a b l e through t h e use o f n o n l i n e a r
accelerometer feedback.
The f o u r t h and s i x t h o r d e r systems w i t h v a r i o u s
g a i n combinations and accelerometer l i m i t s e t t ings has been i n v e s t i g a t e d .
Bending moment r e d u c t i o n between t h e one-lag ( f o u r t h o r d e r system) and
t h e t h r e e - l a g ( s i x t h o r d e r system) systems i s comparable. A f i n a l r e p o r t
i s b e i n g prepared.
(5)
Task E (Schedule Order $ / l o ) , " U t i l i z a t i o n of
V e l o c i t y Feedback from P l a t f o r m Mounted Accelerometer
f o r Control o f S a t u r n V-LOR1'
The g e n e r a l o b j e c t i v e o f t h i s study i s t o determine
t h e l i m i t a t i o n s and/or a d d i t i o n a l problems encountered i n r e p l a c i n g t h e
body-mounted accelerometer by t h e platform-mounted accelerometer and
i n t e g r a t i n g t o o b t a i n v e l o c i t y feedback f o r c o n t r o l of t h e S a t u r n V.
A s e t o f r o o t l o c u s p l o t s was made t o determine
t h e p o s i t i o n o f t h e r i g i d body r o o t s a s a f u n c t i o n o f t h e g a i n s a o s a l
and the v e l o c i t y g a i n el.
Rigid body responses were r u n f o r both c o n s t a n t
and time-varying c o e f f i c i e n t s u s i n g t h e MSPC d e s i g n wind p r o f i l e .
The
v e l ~ c i t yfeedback appears t o be o n l y moderately e f f e c t i v e i n r e d u c i n g
bending moments.
The b e s t l o a d r e d u c t i o n was about 15 p e r c e n t below
t h e bending moments o c c u r r i n g w i t h a t t i t u d e and a t t i t u d e r a t e feedback,
It a p p e a r s t h a t a d d i t i o n a l compensation w i l l be r e q u i r e d i n t h e v e l o c i t y
feedback loop i f a d d i t i o n a l load r e d u c t i o n i s r e q u i r e d .
�d.
Chrysler
I n t h e a r e a of g e n e r a l s t u d i e s f o r S a t u r n I B r i g i d body
c o n t r o l , s e p a r a t i o n motion a n a l y s e s were continued f o r double engine
f a i l u r e and e a r l y shutdown o f a l l engines w i t h a d e l a y between t h e inboard
and outboard engines.
Three major m o d i f i c a t i o n s have been i n c o r p o r a t e d i n t o
(1) e q u a t i o n s
t h e B-2 S i x DOP t r a j e c t o r y r o u t i n e and a r e checked o u t :
f o r s i m u l a t i n g c o n t r o l system f i l t e r s , (2) e q u a t i o n s d e s c r i b i n g n o n l i n e a r
aerodynamics, and ( 3 ) e q u a t i o n s f o r computing a x i a l l o a d s and " c r i t i c a l "
bending moments.
Ten p a r c e l s s f e q u a t i o n s , each c o n s t i t u t i n g a subprogram,
have now been submitted f o r programming i n t h e development o f t h e new
six-degrees-of-freedom t r a j e c t o r y r o u t i n e , The two p a r c e l s submitted i n
October a r e "The G r a v i t a t i o n a l Force, t h e Canting o f Thrust Vectors, and
t h e Summation o f Forces and Momentsooand "Variable I n t e r v a l o f I n t e g r a t i o n s . "
A t e s t problem was submitted f o r programming checkout o f t h e f o u r t h p a r c e l ,
"Control System Equations, Guidance and Control Table Look-@ and
Manipulat i o n *
The engine-out c o n t r o l P a b i P i t y s t u d i e s f o r t h e SA-203
v e h i c l e a r e near completion. The d a t a a r e being processed and prepared
f o r publication.
The study o f l i f t - o f f motion f o r the S a t u r n 1?3/~entaur
v e h i c l e was completed.
The r e p o r t was w r i t t e n and should be p u b l i s h e d
i n t h e f i r s t week o f November.
A s t u d y was made t o compare f l e x i b l e body l o a d s w i t h
r i g i d body l o a d s f o r t h e AS-201 v e h i c l e .
Two r e a l winds were s e l e c t e d
These r e s u l t s
from January winds measured w i t h FPS-16 radar/Jimsphere.
w i l l be documented i n a C h r y s l e r Technical B u l l e t i n t o be p u b l i s h e d i n
t h e e a r l y p a r t o f n e x t month.
e.
-
General Dynamics /Convair
NAS8-11494, "Design C r i t e r i a
f o r Space V e h i c l e s During t h e Launch Phase o f F l i g h t "
The d r a f t copy of t h e monograph, $701. 11, P a r t 2,
"Nonlinear Systems," has been reviewed.
The document, a l o n g w i t h t h e
suggested r e v i s i o n s and c o r r e c t i o n s , has been r e t u r n e d t o GD/C t o be
r e w r i t t e n and r e s u b m i t t e d i n t h e f i n a l form, i n accordance w i t h
c o n t r a c t u a l requirements.
The d r a f t monograph, Vol. I, P a r t 1, "Short P e r i o d
Dynamics," has been r e c e i v e d , b u t has n o t been reviewed.
This monograph
c o n t a i n s d a t a on g e n e r a l e q u a t i o n s o f motion, E u l e r a n g l e s , f o r c e s and
moments, e q u a t i o n s o f p e r t u r b e d motion, and s i m p l i f i e d t r a n s f e r f u n c t i o n s .
�I n a n t i c i p a t i o n of work on t h e monographs 'Nan i n t h e
Loop" and "Abort," t h e names o f s e v e r a l people f o r c o n t a c t s were forwarded
t o M r . A. L. G r e e n s i t e , t h e p r i n c i p a l i n v e s t i g a t o r f o r t h i s study.
f.
-
Douglas
NAS8-20087, "Study of Bending Feedback C o n t r o l
System," Via ~ a l m a n ' sP r e d i c t i o n and F i l t e r i n g Methods
The s t a t e - s p a c e e q u a t i o n s p r e s e n t e d i n t h e second
(August) p r o g r e s s r e p o r t were i n c o r r e c t , p r imar i l y i n the terms i n v o l v i n g
s l o s h modes.
These e q u a t i o n s were c o r r e c t e d , and the r e v i s e d v e r s i o n s
were p r e s e n t e d t o D r . T, R. Blackburn, t h e p r i n c i p a l i n v e s t i g a t o r , i n a
subsequent phone c o n v e r s a t i o n ; a c o r r e c t e d copy of t h e e q u a t i o n s was
a l s o s e n t t o Douglas.
During t h e t h i r d (September) p e r i o d , s i m p l i f i e d models
were i n v e s t i g a t e d t o develop i n s i g h t i n t o t h e l a r g e r system behavior.
Linear t r a n s f o r m a t ions were made on t h e s t a t e so t h a t the measurable
system o u t p u t s and d e r i v a t i v e s o f o u t p u t appear a s s t a t e v a l u e s ; t h e r e f o r e ,
any unobservable s t a t e v a r i a b l e s a r e r e p l a c e d by measurable v a r i a b l e s .
The Kalman f i l t e r e q u a t i o n s can be a p p l i e d t o t h e transformed s t a t e .
g.
-
Honeywell
NAS8-20155, "Design o f a Load R e l i e f Control
System, I ' Via S t a t i s t i c a l Techniques
The purpose o f t h i s s t u d y i s t o develop a c o n t r o l l e r
t h a t w i l l maximize t h e p r o b a b i l i t y of m a i n t a i n i n g t h e bending moment
w i t h i n a c c e p t a b l e bounds d u r i n g f l i g h t and of a c h i e v i n g a n a c c e p t a b l e
terminal s t a t e ,
A s t a t i s t i c a l wind p r o f i l e of a n e x p o n e n t i a l - c o s i n e - s i n e
form has been g e n e r a t e d by f i t t i n g the c o r r e l a t i o n s o b t a i n e d from NASA
TN D-561.
The computer s o l u t i o n was o b t a i n e d by minimizing t h e e r r o r
between t h e computed c o r r e l a t i o n and t h e d a t a c o r r e l a t i o n , weighted by
the number o f o b s e r v a t i o n s .
P l o t s contained i n t h e August P r o g r e s s
Report, Honeywell Report 12013-PR 3 , show t h e g i v e n and t h e computed
East-West c o v a r i a n c e s v e r s u s a l t i t u d e . As expected, t h e computed
covar iances a r e smoother t h a n t h e a c t u a l covar i a n c e s
.
Computat i o n a l d i f f i c u l t i e s have been encountered i n
g e n e r a t i n g t h e q u a d r a t i c c o e f f i c i e n t s f o r t h e performance index t h a t
w i l l be used f o r t h i s study.
C.
Applied Guidance and F l i g h t Mechanics Branch
1.
Saturn I B
a , The payload c a p a b i l i t y o f S a t u r n I B v e h i c l e s . , based
upon October c u r r e n t w e i g h t s , was t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s ,
�b. Optimized t r a j e c t o r i e s f o r S a t u r n HB p o l a r o r b i t s have
been generated f o r b o t h a t h r e e - s t a g e d i r e c t a s c e n t i n t o a 200 n. m i .
c i r c u l a r p o l a r o r b i t and f o r a f l i g h t p r o f i l e w i t h a s u b o r b i t a l s t a r t
o f t h e S e r v i c e Module i n t o an 80 n. m i . x 200 n. m i . e l l i p s e c i r c u l a r i z e d
a t apogee u s i n g a second burn o f the SM. Documentation i s b e i n g reviewed,
Work c o n t i n u e s t o i n c l u d e a 14-day o r b i t and d e - o r b i t t o t h e r e - e n t r y
point.
c , T r a j e c t o r i e s have been completed f o r a S a t u r n IB v e h i c l e
two s t a g e d i r e c t a s c e n t i n t o a 200 n. m i . c i r c u l a r o r b i t f o r Apollo
a p p l i c a t i o n s o r b i t a l experiments. One v e h i c l e would be used f o r a f u e l
t r a n s f e r experiment, w h i l e t h e o t h e r v e h i c l e would house an o r b i t a l
workshop i n t h e empty S-IVB p r o p e l l a n t tanks.
d.
SA-203 O r b i t a l Venting Tracking Analysis: Work t o
determine t h e e f f e c t s o f S-IVB and Instrument Unit d i s c r e t e and continuous
v e n t s upon t r a c k i n g s t a t i o n a c q u i s i t i o n time i s i n p r o g r e s s .
e. A s t u d y has been i n i t i a t e d t o d e f i n e the m o u n t s f f l i g h t
performance r e s e r v e s r e q u i r e d t o g u a r a n t e e S a t u r n 93 payloads when t h e
S e r v i c e Module i s used a s a t h i r d s t a g e . A nominal t r a j e c t o r y has been
determined based upon a n 80.,n.m, by 107 n. m i . e l l i p s e and t h e f l i g h t
performance r e s e r v e s t u d y i s beginning.
f.
Extensive s t u d i e s were made w i t h t h e extremely c o o p e r a t i v e
h e l p of R-AERO-FM and R-P&VE t o demonstrate t h e e f f e c t o f t h e n o n l i n e a r i t y
o f t h e LOX probe i n t h e PU system on t h e t h r u s t p r o f i l e and subsequently
on t h e t h r u s t a t t i t u d e p r o f i l e .
The e x c u r s i o n s on t h e t h r u s t p r o f i l e
caused a d e g r a d a t i o n i n t h e n e a r p e r f e c t accuracy and performance o f t h e
guidance scheme. The e q u a t i o n s f o r AS-201 have been modified such t h a t
t h e guidance scheme does n o t sense t h e s e extreme t h r u s t o s c i l l a t i o n s and
such t h a t the a l t i t u d e c o n s t r a i n t i s r e l a x e d approximately 50 seconds
before cutoff.
S i n c e t h e AS-201 f l i g h t is imminent, t h e m o d i f i c a t i o n
o f t h e guidance e q u a t i o n s i s t h e o n l y s o l u t i o n without schedule s l i p p a g e .
The r e s u l t s were p r e s e n t e d t o t h e S-HW review (Dr. Rees) October 20,
1965 and a g a i n t o Douglas A i r c r a f t C o r p o r a t i o n October 21, 1965.
Vehicle d a t a f o r AS-207 have been f u r n i s h e d t o MIT t o
s i m u l a t e i n t h e i t e r a t i v e guidance scheme e q u a t i o n s which have been
programmed s u c c e s s f u l l y by MIT f o r backup s t u d i e s , Close communication
i s being maintained i n t h e e v e n t t h a t problem a r e a s may a r i s e .
The payload c a p a b i l i t y o f S a t u r n 1 ~ I C e n t a u rv e h i c l e s ,
based upon October c u r r e n t w e i g h t s , was computed and t r a n s m i t t e d t o
I n d u s t r i a l Operations.
Performance changes due t o i n d i v i d u a l p e r t u r b a t ions of
t h e s t a g e a n d v e h i c l e c h a r a c t e r i s t i c s o f t h e S a t u r n ~ ~ / ~ e n t av euhri c l e
have been determined. Docunentation i s t o be included i n a NASA Technical
�Memorandum covering t h e g e n e r a l performance survey. Release of t h e NASA
a u r
Technical Memorandum w i l l complete t h e S a t u r n ~ ~ / ~ e n t performance
analysis effort,
2.
Saturn V
a , The payload c a p a b i l i t y of S a t u r n V v e h i c l e s , based upon
October c u r r e n t weights, was t r a n s m i t t e d t o I n d u s t r i a l Operations.
b, The p r o b a b i l i t y o f t h e S-HVB impacting t h e moon s t u d y
i s complete and i s being documented.
c.
S-IVB p l a n e change c a p a b i l i t y : An e x i s t i n g c a l c u l u s
of v a r i a t i o n s computer r o u t i n e w i t h m o d i f i c a t i o n s to c u t o f f on C 3 and
i s o l a t e a n i n j e c t i o n p l a n e has been checked o u t , Work w i l l resume
when a n a l y s e s o f h i g h e r p r i o r i t y problems have been completed.
d. The e f f e c t s upon continuous o p e r a t i o n of t h e S-I'D
oxygen-hydrogen b u r n e r (modified S-IV helium h e a t e r ) upon t h e LOR m i s s i o n
p a r k i n g o r b i t a r e b e i n g i n v e s t i g a t e d , The burner w i l l be i n s t a l l e d on
AS-503 and subsequent p r i m a r i l y f o r r e p r e s s u r i z a t i o n of t h e S-IVB s t a g e .
I f t h e r e s u l t s o f SA-203 l i q u i d hydrogen experiment d a t a r e q u i r e continuous
t h r u s t t o s e t t l e S-IVB p r o p e l l a n t s , the LOX-LH,burner w i l l be used
c o n t i n u o u s l y , The burner has a t h r u s t l e v e l of 15 t o 22 pounds.
e. A s t u d y i s being conducted t o d e f i n e t h e payload
c a p a b i l i t y of t h e S a t u r n V v e h i c l e f o r a synchronous e q u a t o r i a l o r b i t .
The p a r k i n g o r b i t a l t i t u d e i s 100 n. m i . , and o r b i t a l and s u b o r b i t a l
s t a r t of t h e S-IVB s t a g e i s being i n v e s t i g a t e d .
The p l a n e change i s
b e i n g performed a f t e r t h e p a r k i n g o r b i t . A new v e r s i o n of t h e e x i s t i n g
three-degrees-of-freedom c a l c u l u s - o f - v a r i a t i o n s t r a j e c t o r y r o u t i n e i s
b e i n g checked o u t .
Problems o f o b t a i n i n g convergence have delayed t h e
g e n e r a t i o n o f a n optimum t r a j e c t o r y .
f , A study i s being completed t o d e f i n e the payload
c a p a b i l i t y o f t h e S a t u r n V v e h i c l e f o r a 200 n. m i . a l t i t u d e p o l a r
o r b i t . The document, R-AERO-DAP-104-65,
i s being prepared.
g, 5-2 t h r u s t o s c i l l a t i o n t o l e r a n c e s : P a r a m e t r i c s t u d i e s
were made t o f i n d t h e a l l o w a b l e t h r u s t o s c i l l a t i o n f o r t h e S a t u r n V m i s s i o n
due t o t h e same n o n l i n e a r i t y of t h e LOX probe mentioned under S a t u r n IB.
This LOX probe, b u i l t by Minneapolis Honeywell, i s c u r r e n t l y i n t h e S-IVB
and S - I 1 p r o p e l l a n t u t i l i z a t i o n s y s tem. P&VE recommended t h a t a t y p i c a l
t h r u s t p r o f i l e (approximately 10,000 l b s of t h r u s t peak-to-peak v a r i a t i o n )
which was assumed i n a d i r e c t a s c e n t study be used,
It was found t h a t
t h e S-I1 b u r n and t h e f i r s t burn o f t h e S-IVB i n t o a 185.2 km c i r c u l a r o r b i t
s t i l l maintained s u f f i c i e n t guidance accuracy, a l t h o u g h a l o s s of payload
of approximately 700 l b s i n o r b i t was observed.
The nondegradation o f
accuracy can be e x p l a i n e d i n t h a t a t t h e beginning of t h e f i r s t burn o f
�t h e S-IVB t h e p a t h a n g l e i s merely 0.6" a g a i n s t l o c a l h o r i z o n t a l and t h e
Therefore,
a l t i t u d e i s w i t h i n 3 km of t h e d e s i r e d i n j e c t i o n a l t i t u d e .
t h e requirement upon t h e guidance scheme i s mainly t o g a i n t h e n e c e s s a r y
v e l o c i t y magnitude f o r i n s e r t i o n .
The second S-HVB burn shows a h i g h e r s e n s i t i v i t y t o
these t h r u s t o s c i l l a t i o n s .
Their e f f e c t on t h e guidance scheme w i t h o u t
major m o d i f i c a t i o n w i l l be a n i n j e c t i o n a n g l e e r r o r of approximately 0 . 6 Q ,
which c a u s e s a 4000 km e r r o r a t t h e r a d i u s of c l o s e s t approach t o t h e
moon and i s r e f l e c t e d i n t o a r e q u i r e d midcourse v e l o c i t y c o r r e c t i o n of
approximately 40 m/s.
These r e s u l t s were a l s o p r e s e n t e d a t t h e S-IW
review on October 20, and t o Douglas p e r s o n n e l October 29.
It was agreed
t h a t t h e LOX probe should have a hardware f i x t o improve i t s l i n e a r i t y .
A v i s i t was made t o Minneapolis-Honeywell October 25 w i t h r e p r e s e n t a t i v e s
of 10, Center Labs, and Douglas i n a t t e n d a n c e t o d i s c u s s p o t e n t i a l f i x e s .
Honeywell agreed t h a t a f i x on t h e LOX probe could be made a v a i l a b l e i n
approximately 12 weeks w i t h 2K l b peak-to-peak a s an e x c u r s i o n l i m i t .
The c o s t o f such a f i x i s n o t known,
h.
S-IC Guidance and T r a j e c t o r y Shaping: Extensive s t u d i e s
have been made i n t h e i n v e s t i g a t i o n of c l o s e d loop guidance i n t h e S-HC
s t a g e , w i t h emphasis on t h e i t e r a t i v e guidance mode's b e i n g i n i t i a t e d
a t 1 2 seconds.
i. The S-BC t r a j e c t o r y was optimized w i t h load c o n s t r a i n t s ,
t h e r e s u l t s o f which gave a p r e l i m i n a r y t r a d e - o f f of payload v e r s u s
s t r u c t u r a l (bending) loads. A s i g n i f i c a n t payload g a i n can be achieved
w i t h moderate s t r u c t u r a l load i n c r e a s e . However, because o f t h e
n o n l i n e a r i t y o f t h e t r a d e - o f f f u n c t i o n , t h e s t r u c t u r a l load r e d u c t i o n
f o r a f i x e d payload i s small.
3.
General
a.
The o p e r a t i o n a l c o n s t r a i n t s a f f e c t i n g l u n a r launch
windows f o r t h e 1967-72 time p e r i o d s t u d y have been f i n i s h e d f o r about
two months.
The d e l a y i n p u b l i c a t i o n i s due t o t h e l a r g e amount of
It i s expected
graphs (72) t o be p u t i n a form s u i t a b l e f o r p u b l i c a t i o n .
t h a t t h i s work w i l l be documented about t h e l a s t of November.
b.
Launch windows f o r c i s l u n a r type m i s s i o n s s t u d i e s have
been f i n i s h e d . The r e s u l t s should be p u b l i s h e d soon.
c. A r e f e r e n c e m i s s i o n p r o f i l e f o r AAP l u n a r mapping m f s s i o n
has been e s t a b l i s h e d .
This p r o f i l e i s t o be used by North American A v i a t i o n
and Gruman A i r c r a f t i n t h e Apollo A p p l i c a t i o n Program payload i n t e g r a t i o n
document.
d. A computer program i s being developed t o determine
closed-form s o l u t i o n f o r r e c t a n g u l a r c o o r d i n a t e s of t h e two-body problem
�and t h e i r p a r t i a l d e r i v a t i v e s w i t h r e s p e c t t o t h e i r i n i t i a l v a l u e s ,
The program w i l l be used t o g e n e r a t e p e r t u r b e d t r a j e c t o r i e s and t o
determine AV c o r r e c t i o n s . S t i l l a n o t h e r problem e x i s t s w i t h t h e second
burn, While t h e v e h i c l e i s i n parking o r b i t , l i q u i d hydrogen i s b o i l i n g
o f f and being v e n t e d , t h e amount depending on which p a r k i n g o r b i t t h e
v e h i c l e l e a v e s , As a r e s u l t , an unknown amount of hydrogen w i l l be
Thus, t h e PU system w i l l cause a
p r e s e n t a t i g n i t i o n of t h e S-IVB.
step-down i n m i x t u r e r a t i o t o consume t h i s excess hydrogen u n t i l t h e
o r i g i n a l r e f e r e n c e 5.0 i s reached.
S t u d i e s a r e now being made t o
determine t h e e f f e c t on t h e time of s t e p and how t h e guidance w i l l
perform due t o t h i s u n c e r t a i n t y ,
e.
S t u d i e s a r e being made t o determine t h e e f f e c t of
uncoupling the yaw a t t i t u d e command w i t h t h e p i t c h a t t i t u d e command,
b o t h g e n e r a t e d by t h e i t e r a t i v e guidance mode, Such uncoupling h a s
no impact f o r small plane changes; however, t h e e f f e c t on accuracy
and performance f o r l a r g e p l a n e changes (up t o p o l a r o r b i t s ) i s being
i n v e s t i g a t e d , The uncoupling w i l l s i m p l i f y the e q u a t i o n s and d e c r e a s e
computer time.
The a c t u a l s i m p l i f i c a t i o n and r e d u c t ion t o a s i g n i f i c a n t
degree must be c a r e f u l l y e v a l u a t e d b e f o r e any p o s i t i v e recsmmendation
can be made.
4 , , Contractors
a.
Boeing
The S a t u r n V payload c a p a b i l i t y based upon October
c u r r e n t weights was computed and t r a n s m i t t e d , The performance e f f e c t s
of S-IC and S - I I s t a g e t h r u s t decay and t h e e f f e c t s o f c o n s t a n t p i t c h
a t t i t u d e a n g l e from S-IC c e n t e r erg ine c u t o f f t o LES j e t t i s o n were
added t o t h e v e h i c l e simulation.
The AS-501 a b o r t and a l t e r n a t e m i s s i o n document was
r e c e i v e d , has been reviewed, and w i l l be d i s t r i b u t e d i n November,
The isomax polynominal i s o l a t i o n and maximization
scheme and wind p r o f i l e have been added t o t h e t r a j e c t o r y o p t i m i z a t i o n
( s t e e p e s t a s c e n t ) program, The study has been extended t o i n c l u d e
o p t i m i z a t i o n s t a r t times a t v a r i o u s i n t e r v a l s a f t e r l i f t - o f f .
Work i s c o n t i n u i n g on d e t e r m i n a t i o n o f the AS-501
reference trajectory.
The t r a j e c t o r y i s being updated to i n c l u d e
r e v i s e d v e h i c l e aerodynamic c h a r a c t e r i s t i c s .
�An AS-503 p r e l i m i n a r y m i s s i o n pro f i l e which does n o t
i n c o r p o r a t e long c o a s t p e r i o d s i n the h i g h r a d i a t i o n b e l t s i s being
A s t u d y comparing the r a d i a t i o n exposure o f the AS-503 m i s s i o n
reviewed.
Preparations required t o
w i t h t h e nominal LOR m i s s i o n i s i n p r o g r e s s .
g e n e r a t e t h e AS-503 p r e l i m i n a r y launch v e h i c l e r e f e r e n c e t r a j e c t o r y a r e
under way,
P r e p a r a t i o n s a r e being made and deck mod i f i c a t ions a r e
being i n c o r p o r a t e d i n t o t h e j o i n t r e f e r e n c e t r a j e c t o r y deck t o g e n e r a t e
an AS-504 p r e l i m i n a r y Paunch v e h i c l e r e f e r e n c e t r a j e c t o r y ,
Boost t o
o r b i t phase i s complete.
T a r g e t i n g D e f i n i t i o n and S i m p l i f i c a t i o n : Work i s
p r o g r e s s i n g on t h e g e n e r a t i o n of t h e d e s i r e d number o f f r e e r e t u r n
t r a j e c t o r i e s f o r a l u n a r c y c l e . These d a t a a r e t o be used t o i n v e s t i g a t e
p a r k i n g o r b i t t a r g e t i n g parameters t h a t a r e m i s s i o n dependent.
The
major e f f o r t t o d a t e i s concerned w i t h the i g n i t i o n c r i t e r i a , When t h e
d e s i r e d i g n i t i o n c r i t e r i a a r e chosen, the r e s u l t i n g m i s s i o n dependent
parameters w i l l be i n v e s t i g a t e d f o r v a r i a t i o n s and methods o f mechanization
f o r t h e onboard computer.
P r e p a r a t i o n o f AS-504 Spectrum: A l l t r a j e c t o r i e s have
There i s remaining work on
been completed f o r two azimuths ( 7 z 0 , 85').
t h e 98-degree azimuth. T h i s e f f o r t i s i n r e s p o n s e t o an a c t i o n item
from t h e r e f e r e n c e t r a j e c t o r y subpanel, Documentation w i l l be a j o i n t
e f f o r t between MSPC and MSC,
The guidance e q u a t i o n s f o r t h e AS-501 have been
documented approximately two months behind schedule because t h e
c o n t r a c t o r changed the guidance e q u a t i o n s provided by R-AERO w i t h o u t
good r e a s o n s and w i t h o u t a u t h o r i z a t i o n .
F u r t h e r s l i p p a g e i n docurnentat i o n
w i l l r e s u l t , u n l e s s t h i s procedure i s changed. U n f o r t u n a t e l y , t o g e t any
u s e f u l r e s u l t s under t h e p r e s e n t arrangement p l a c e s an e x c e s s i v e work
load on c i v i l s e r v i c e personnel.
The S a t u r n I B payload c a p a b i l i t y f o r a l l m i s s i o n s and
v e h i c l e s , based upon October c u r r e n t w e i g h t s , was computed and t r a n s m i t t e d .
AS-204 launch v e h i c l e r e f e r e n c e t r a j e c t o r y : The f l i g h t
c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements
document i s being reviewed b e f o r e p u b l i c a t i o n .
The documentation o f the AS-205 and 206 launch v e h i c l e
p r e l i m i n a r y r e f e r e n c e t r a j e c t o r i e s has been completed. Work i s i n p r o g r e s s
t o g e n e r a t e a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance
r e s e r v e requirements f o r AS-206.
The AS-206 d e s i g n t r a j e c t o r i e s , £1i g h t
c o r r i d o r , e t c . , have been t r a n s m i t t e d .
�An SA-203 r e v i s e d launch v e h i c l e r e f e r e n c e t r a j e c t o r y
has been g e n e r a t e d , and d o c m e n t a t i o n has been received. Work t o p r e p a r e
a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e
requirements i s under way,
An AS-207 p r e l i m i n a r y launch v e h i c l e r e f e r e n c e t r a j e c t o r y
has been determined, Documentat i o n has been r e c e ived. Work t o determine
a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , f l i g h t performance r e s e r v e s
requirements i s under way.
Documentation of t h e r e s u l t s of t h e s i n g l e and d u a l
S-IB engine-out s t u d i e s f o r t h e SA-203 and AS-204 v e h i c l e s i s i n p r o g r e s s .
A p r e l i m i n a r y d r a f t of t h e SA-203 engine-out a n a l y s i s has been r e c e i v e d
and i s be ing r e v iewed ,
Three-degrees-of-freedom computer r o u t ine:
c o n t i n u i n g t o i n c o r p o r a t e o u t p u t and p r o c e s s i n g modules.
Work i s
S a t u r n 6B guidance e q u a t i o n s and guidance scheme ( n o t
i n c l u d i n g hardware) e r r o r a n a l y s e s a r e being produced on a n e a r - r o u t i n e
bas i s .
Since C h r y s l e r has a deck which s i m u l a t e s i n d e t a i l the
PU system, a l a r g e amount o f t h e i r d a t a was used i n t h e argument f o r a
f i x on t h e LOX probe,
Guidance hardware e r r o r a n a l y s e s f o r each S a t u r n I B
a r e b e i n g generated,
c,
Northrop
The Monte Carlo technique h a s been a p p l i e d t o a guidance
system hardware e r r o r a n a l y s i s f o r S a t u r n V, The r e s u l t s i n terms o f
The
midcourse v e l o c i t y d i f f e r from t h e "root-sum-square" by 0 - 1 m / s .
c l o s e n e s s of t h e s e r e s u l t s l o o b a s i f every i n p u t had a normal d i s t r i b u t i o n ,
which i s n o t c o r r e c t , I n v e s t i g a t i o n s a r e being made t o determine t h e
v a l i d i t y o f t h e s e numbers,
A program s i m u l a t i n g braking maneuvers i n t o a l u n a r o r b i t
u s i n g t h e i t e r a t i v e guidance mode has been completed.
Programming f o r an e a r t h o r b i t a l rendezvous deck has
been completed,
The hardware e r r o r a n a l y s i s deck i s being modified t o
s i m u l a t e two guidance system6 f o r t h e Apollo backup guidance s t u d y ,
Abort and a l t e r n a t e m i s s i o n s t u d i e s i n t h i s same v e i n a r e being
investigated.
�E r r o r a n a l y s e s a r e being made on braking i n t o l u n a r
o r b i t and on t h e e a r t h o r b i t a l rendezvous study.
d,
Lockheed
The r e s u l t s o f a study u s i n g t h e i t e r a t i v e guidance
scheme i n t h e S - I n and t h e s e r v i c e module look g u e s t i s n a b l e w i t h
r e s p e c t t o accuracy check e a s e s and w i l l have tis he r u n inhause t o
t r y t o a s c e r t a i n t h e problem. Work c o n t i n u e s on improving t h e guidance
scheme f o r v a r i o u s miss ion pro f i l e s . However, u n t i l t h e problems
Lockheed has w i t h t h e b a s i c i t e r a t i v e guidance scheme a r e r e s o l v e d ,
t h e r e s u l t s on e x t e n d i n g i t a r e meaningless.
e,
North American Aviation
The f i r s t monograph o f t h e Guidance Design C r i t e r i a
Handbook was d e l i v e r e d on schedule and deemed a c c e p t a b l e by R-AERO-DA.
However, NASA Headquarters judged i t nonacceptable because a c e r t a i n
format o f headings was n o t followed.
This r e s t r i c t i o n d i d not appear
i n t h e c o n t r a c t , The format of t h e monograph follows the r e q u i r e d format
w i t h r e s p e c t t o s u b j e c t m a t t e r b u t s t r i c t adherence t o headings was n o t
maintained. A s a r e s u l t , t h e c o n t r a c t must be changed t o r e q u i r e t h i s
s t r i c t adherence and t o l e t t h i s monograph s l i p t o November 2 ( f o r m e r l y
August 2 7 ) t o conform w i t h Headquarters' p o l i c y .
f
.
Ling-Temco-Voug h t
Lunar Launch Window Study: The mid-term review f o r t h i s
s t u d y was h e l d on October 23. It i s f e l t t h a t t h e c o n t r a c t o r i s somewhat
behind s c h e d u l e , probably because o f personnel problems.
They have l o s t
two people who were assigned t o t h e study. They should be a b l e t o g e t
back on schedule, however, because t h e y have been a b l e t o d e c r e a s e t h e
computer r u n time on t h e program used t o do t h e study.
g.
~ o r t h r o p / ~ o c k h e e(Miss
d
ion Support)
A l l S a t u r n JB and S a t u r n ~ B / ~ e n t a uperformance
r
c a p a b i l i t y d a t a f o r p l a n a r launches have been completed.
The
d e t e r m i n a t i o n of nonplanar performance c a p a b i l i t y i s almost complete.
P r e l i m i n a r y documents t i o n i s expected e a r l y i n November.
The payload c a p a b i l i t y of t h e S a t u r n ~ B / ~ e n t a uf ro r t h e
Voyager m i s s i o n , based upon October c u r r e n t w e i g h t s , was c a l c u l a t e d and
transmitted,
Rapid performance r o u t i n e deve lopmenta The comparison
o f machine t ime v e r s u s accuracy o f v a r i o u s e x i s t i n g performance r o u t i n e
and t h e Lockheed developed PRESTO r o u t i n e i s near completion, P r e l i m i n a r y
documentation i s expected i n November.
�The u s e o f switching f u n c t i o n theory t o determine
optimum s t a g i n g p o i n t s i s b e i n g i n v e s t i g a t e d . The s w i t c h i n g f u n c t i o n
e q u a t i o n s have been w r i t t e n and have been i n c o r p o r a t e d i n t o a n e x i s t i n g
two-dimensional vacuum computer r o u t i n e .
Checkout and a n a l y s i s a r e
under way.
D.
Advanced P r o j e c t s Study Branch
1.
Apollo A p p l i c a t i o n Program (AAP)
The October meeting o f the Mission Planning Task Force was
a t t e n d e d a t MSC on October 12 by s e v e r a l r e p r e s e n t a t i v e s o f MSFC.
Aero-Astrodynamics p e r s o n n e l were prepared t o g i v e a p r e s e n t a t i o n on
f l i g h t s 211, 507, 509, and 511 f o r t h e m i s s i o n s s p e c i f i e d i n schedule
ML65-1.
Time was n o t a v a i l a b l e f o r t h e planned d i s c u s s i o n s because t h e
NAA and GAEC p r e s e n t a t i o n s consumed t h e day.
To i n j e c t broader planning i n t o t h e AAP s t u d i e s a t MSC, a
group o f MSFC r e p r e s e n t a t i v e s headed by M r . F, L. Williams went t o MSC
on October 19 and 20, where the concept of t h e S-IVB workshop was
p r e s e n t e d . The meeting was termed a s u c c e s s , and o t h e r exchanges o f
i n f o r m a t i o n and i d e a s of t h i s type were encouraged,
The l a t e s t AAP t h i n k i n g i n Headquarters was r e c e i v e d i n the
form o f s c h e d u l e ML-65-2 from M r . W, B. Taylor. A response t o t h e new
f l i g h t and m i s s i o n assignment was r e q u e s t e d i n t h e form o f a p r e s e n t a t i o n
t o D r . Mueller on October 28. Aero-Astrodynamics Laboratory s u p p l i e d
i n p u t s t o t h e review. A l i m i t e d number of s p e a k e r s were scheduled,
p r i m a r i l y from t h e Advanced Systems O f f i c e .
2.
S-IVB Workshop
The S-IVB workshop i s going through t h e second i t e r a t i o n
w i t h R-P&VE, Aero-Astrodynamics and A s t r i o n i c s L a b o r a t o r i e s involved.
A r e f e r e n c e t r a j e c t o r y has been c a l c u l a t e d which g i v e s a 14-day l i f e t i m e
w i t h 3 0 d i s p e r s i o n s . Purged s t a g e weight and payload have been r e l e a s e d
t o R-P&VE. A f t e r t h e moments of i n e r t i a and CG l o c a t i o n a r e r e t u r n e d t o
Aero-Astrodynamics Laboratory, a c o n t r o l a n a l y s i s w i l l be performed t o
determine i f t h e s p a c e c r a f t ( s e r v i c e module) can s t a b i l i z e t h e workshop
o r i f t h e APS on t h e S-IVB w i l l be r e q u i r e d f o r t h e d u r a t i o n o f t h e
mission.
I f t h e S-IVB must f u r n i s h a t t i t u d e c o n t r o l , t h e n methods w i l l
be sought t o implement e i t h e r a "tack-ontt v a r i e t y o r an e x t e n s i o n of
t h e c u r r e n t S-IVB APS.
Through t h e S-IVB workshop team, an a r t i f i c i a l g r a v i t y
experiment i s being i n v e s t i g a t e d .
The S-IVB would be used a s a
counter-weight w i t h t h e CSM on t h e o t h e r end of c a b l e s o r on a system
of t e l e s c o p i n g tubes. MSC has placed a requirement f o r a 100-foot
�r a d i u s arm from t h e c e n t e r of g r a v i t y t o t h e working a r e a . The range of
The team i s asking A s t r i o n i c s
g r a v i t y s i m u l a t i o n i s from 0.1 t o 1.0 g k .
and Aero-Astrodynamics Laborator i e s t o develop t h e requirements f o r a n
a t t i t u d e c o n t r o l system and a spin-up and d e s p i n system. The team i s
a l s o a s k i n g A s t r i o n i c s and Aero-Astrodynamics L a b o r a t o r i e s i f t h e CSM
can perform t h e complete t a s k . When t h e proper deployment system has
been d e r i v e d by R-P&VE, t h e n t h e c o n t r o l systems w i l l be i n v e s t i g a t e d .
3.
Voyager Vehicle Comparison
A comparat ive a n a l y s i s of l auatch v e h i c l e a l t e r n a t i v e s f o r
t h e Voyager m i s s i o n has been completed. Vehicles compared i n terms o f
performance, c o s t , s c h e d u l e s , e t c . , were t h e S a t u r n V, S a t u r n IB/"O"
s t a g e , and t h e S a t u r n ~ ~ / G e n t a u r .A p r e s e n t a t i o n was g i v e n t o MSFG
management on October 24, 1965, The r e s u l t s a r e being documented and
w i l l be p u b l i s h e d i n memorandum form.
4,
Saturn V l ~ o y a g e r
An in-house e f f o r t has been i n i t i a t e d t o d e f i n e t h e S a t u r n V
launch v e h i c l e t h a t w i l l be r e q u i r e d f o r t h e Voyager program.
Close
c o o r d i n a t i o n w i t h JPL i s a n t i c i p a t e d . G u i d e l i n e s and p l a n s f o r t h e
s t u d y w i l l be d i s c u s s e d a t a ' k i c k - o f f " meeting t h e f i r s t week i n November.
VII.
FLIGHT EVALUATEON AND OPERATIONS STUDIES D PVIS I O N
A.
Special Projects Office
1. A summary r e p o r t o f the S a t u r n I launch v e h i c l e f l i g h t t e s t
has been prepared and i s b e i n g reviewed by t h e FEWG b e f o r e p u b l i c a t i o n .
This r e p o r t summarizes i n f o r m a t i o n gained from t h e S a t u r n I program i n
performance t a b l e s , graphs, and i l l u s t r a t i o n s .
The r e p o r t emphasizes
t h e performance o f t h e v e h i c l e systems compared t o a c t u a l c r i t e r i a used
i n d e s i g n i n g t h e system, A l l t e n S a t u r n I v e h i c l e s a r e included i n t h e
r e p o r t . D i s t r i b u t i o n i s planned b e f o r e January 1, 1966.
2. An FEWG meeting w i t h DAC r e p r e s e n t a t i v e s was h e l d a t MSFC
f l i g h t evaluation responsibilities
on October 6 , 1965. The S a t u r n IBIS-IVB
of DAG were d i s c u s s e d i n d e t a i l . Agreements reached a t t h i s meeting have
been inco r p o r a t e d i n t o t h e AS-201 /204 F l i g h t E v a l u a t i o n Plan.
3 . The AS-2011204 F l i g h t E v a l u a t i o n P l a n d r a f t has been reviewed
by a l l segments o f t h e FEWG. This p l a n g i v e s d e t a i l e d proeedures t o be
followed by b o t h MSFG and c o n t r a c t o r e v a l u a t i o n groups i n c o n t r i b u t i n g
t o t h e t o t a l e n g i n e e r i n g e v a l u a t i o n of t h e a f f e c t e d v e h i c l e s .
�4. Data requirements f o r AS-201 f l i g h t e v a l u a t i o n have been
Requirements have been c o o r d i n a t e d and w i l l
submitted by CCSD and DAC.
be p u b l i s h e d i n t h e Program Support Requirements Document and t h e
Processed Data Requirements Document t o o b t a i n c o r r e c t implementation.
5. A meeting o f t h e FEWG f o r S a t u r n I B f l i g h t e v a l u a t i o n
o r i e n t a t i o n and p l a n n i n g h a s been scheduled a t MSFC f o r November 30,
1965. A l l c o n t r a c t o r and MSFC e v a l u a t i o n groups w i l l b e r e p r e s e n t e d .
6. A computer program has been e s t a b l i s h e d f o r r e t r i e v a l of
The program has
major h i g h l i g h t s of t h e S a t u r n I f l i g h t t e s t program.
been implemented and o n l y l a c k s f i n a l i n p u t o f compiled d a t a . The
program o u t p u t e n t i t l e d "SAFER," S a t u r n F l i g h t E v a l u a t i o n R e t r i e v a l ,
w i l l be made a v a i l a b l e t o MSFC segments w i t h i n approximately 2 weeks.
Major headings of t h e o u t p u t format a r e a s follows:
I
I1
I11
IV
V
VI
VII
Test O b j e c t i v e
Malfunctions and D e v i a t i o n s
Launch O p e r a t i o n s
Mass C h a r a c t e r i s t i c s
Event Times
Trajectory
Propulsion
VIII
IX
X
XI
XI1
XIII
Guidance
Control
Structure
Environment
Electrical
I n s t r u m e n t a t ion
A complete l i s t i n g of t h e o u t p u t format w i l l be i s s u e d t o o r g a n i z a t i o n s
w i t h i n MSFC b e f o r e f u l l u t i l i z a t i o n of t h e program.
The program c o n t a i n s
h i g h l i g h t s of t h e t e n S a t u r n I f l i g h t s i n t a b u l a r form o n l y ; i n f o r m a t i o n
can be r e t r i e v e d from the program f o r any one o r more v e h i c l e s and from
any one o r more systems, A s i m i l a r format i s b e i n g e s t a b l i s h e d f o r f u t u r e
Saturn I B f l i g h t s .
B.
F l i g h t E v a l u a t i o n Branch
1.
Saturn I
(1)
CCSD D e t a i l e d F l i g h t E v a l u a t i o n Reports f o r SA-10
The f o l l o w i n g r e p o r t s have been p u b l i s h e d by CCSD
under c o n t r a c t t o t h e Branch.
(a)
R e s u l t s o f t h e Aerodynamic F l i g h t E v a l u a t i o n
S a t u r n SA-10 CCSD TN-AE-65-117, d a t e d
September 10, 1965
(b)
F l i g h t E v a l u a t i o n of S a t u r n SA-10, S-I Stage
Base and Aerodynamic Heating Data, CCSD TN-AE
65-111, dated September 1 5 , 1965.
�be
S-I Stage
(1)
P r o p u l s i o n Summary
A p r o p u l s i o n swnmary r e p o r t has been prepared f o r
SA-6 was e l i m i n a t e d
t h e S-I s t a g e o f t h e S a t u r n H Block I1 v e h i c l e s .
from t h e a n a l y s i s because of e a r l y shutdown. The average p r o p u l s i o n
system v a l u e s from p r e d i c t e d , engine a n a l y s i s (P&vE), and f l i g h t
s i m u l a t i o n (AERO) a r e t a b u l a t e d below, along with t h e p e r c e n t a g e
d e v i a t i o n s of t h e p o s t f l i g h t a n a l y s e s from p r e d i c t e d .
c The
i
f a c t t h a t t h e two independent methods o f e v a l u a t i o n y e i l d e s s e n t i a l l y
i t h e same s o l u t i o n g i v e s c o n s i d e r a b l e confidence i n t h e p r o p u l s i o n
e v a l u a t i o n procedures.
The s t a n d a r d d e v i a t i o n s o f t h e average p r o p u l s i o n
system parameters and t h e i r p e r c e n t a g e d e v i a t i o n from the mean a r e given
be low :
Only one major engine m a l f u n c t i o n o c c u r r e d o u t of 48 e n g i n e s flown on
Block 11 v e h i c l e s f o r a 97.9 p e r c e n t s u c c e s s f u l r a t i n g .
c.
S-IV Stage ( C o r n e l l Short D u r a t i o n S-PV Base P r e s s u r e
Tests)
Base p r e s s u r e h o t flow t e s t s a t C o r n e l l A e r o n a u t i c a l
Laboratory (CAI,) designed t o o b t a i n a complete p i c t u r e o f t h e S-IV b a s e
flow f i e l d and g i v e some e x p l a n a t i o n f o r t h e engine performance d e v i a t i o n s
observed on p a s t f l i g h t s a r e e s s e n t i a l l y completed.
The r e s u l t s without
�secondary (helium h e a t e r ) flow a r e a s expected, based on p r e v i o u s 4- and
6-engine d a t a , There i s an i n c r e a s i n g p r e s s u r e g r a d i e n t from t h e engine
l i p t o t h e h e a t s h i e l d , r e s u l t i n g i n a p o s i t i v e p r e s s u r e t h r u s t . The
r e s u l t s of t h e secondary (helium h e a t e r ) flow must be c o n s o l i d a t e d and
finalized.
2.
S a t u r n I B and V Data Processor
As t h e S a t u r n v e h i c l e s become l a r g e r and more complex and
a s t h e m i s s i o n s become more v a r i e d , t h e amount o f d e t a i l e d i n p u t d a t a needed
i n a six-degree-of-freedom f l i g h t s i m u l a t i o n program i n c r e a s e s d r a s t i c a l l y .
The i n p u t problem i s f u r t h e r complicated by t h e v a r i e t y o f s o u r c e s from
which t h i s d a t a must be o b t a i n e d , An a t t e m p t was made on S a t u r n I,
Block I1 v e h i c l e s t o c o n s o l i d a t e a l l o f t h e time v a r y i n g d a t a f o r a given
s t a g e on one magnetic tape, However, c o n s t a n t changes i n s o u r c e d a t a
formats and u n i t s r e q u i r e d s e v e r a l r e d e f i n i t i o n s of t h e t a p e g e n e r a t i o n
A d i f f e r e n t procedure w i l l be used on f u t u r e S a t u r n v e h i c l e s .
programs.
Requirements f o r s p e c i f i c d a t a , d a t a formats and u n i t s w i l l be placed on
t h e v a r i o u s s o u r c e s , i . e . , s t a g e c o n t r a c t o r s , e t c . , such t h a t a l l d a t a
a r e c o n s i s t e n t w i t h t h e d a t a p r o c e s s o r program. Manual h a n d l i n g of t h e
d a t a w i l l be minimized, and manpower requirements, a s w e l l a s c o s t l y
The d a t a p r o c e s s o r o r g a n i z e s a l l d a t a
e r r o r s , w i l l be g r e a t l y reduced.
into three categories:
( 1 ) s t a g e c o n s t a n t s , ( 2 ) d a t a which a r e a f u n c t i o n
of Mach number, ( 3 ) d a t a which a r e a f u n c t i o n of time, The d a t a p r o c e s s o r
t h e n o u t p u t s a m u l t i p l e f i l e FORTRAN magnetic t a p e c o n t a i n i n g 3 n f i l e s
of d a t a , where n i s e q u a l t o t h e number of s t a g e s , A p r e f l i g h t and a
p o s t f l i g h t t a p e w i l l be permanently saved f o r each v e h i c l e i n t h e Comp
Lab t a p e l i b r a r y and w i l l be a v a i l a b l e f o r g e n e r a l use, This c o n s o l i d a t i o n
of d a t a w i l l a l s o e x p e d i t e v e h i c l e block s t u d i e s and summary r e p o r t s .
3.
Contracts
a.
r
General ~ y n a m i c s / ~ o n v a iNAS8-20249
This i s a six-month c o n t r a c t t o e v a l u a t e and t r u n c a t e
t r a c k i n g system e r r o r models f o r u s e on S a t u r n I B and S a t u r n V p o s t f l i g h t
trajectories.
During t h e p a s t month, a misunderstanding o f beginning
and t e r m i n a t i o n d a t e s was discovered, As a r e s u l t o f t h i s and t h e continued
absence o f t h e GD/C p r o j e c t l e a d e r due t o i l l n e s s , t h e work i s approximately
It was mutually agreed t h a t a 2-month no-cost
5 weeks behind schedule,
e x t e n s i o n was n e c e s s a r y t o complete t h e task.
The paper work f o r t h i s
e x t e n s i o n h a s been i n i t i a t e d .
The r e v i s e d c o n t r a c t t e r m i n a t i o n d a t e i s
February 28, 1966. The s t a t u s o f work being performed and t h e d e t a i l e d
t a s k d e s c r i p t i o n f o r t h e second h a l f of t h e c o n t r a c t p e r i o d were d i s c u s s e d
w i t h GD/C p e r s o n n e l on October 26, 1965. GD/c p l a c e d too much emphasis
on computer c o r e s t o r a g e and r e a l time computation r e s t r i c t i o n s . As a
r e s u l t , o n l y c o n s t a n t b i a s terms were included i n t h e t r a c k e r e r r o r models.
The t a s k f o r t h e second h a l f of t h e c o n t r a c t p e r i o d has been d e f i n e d w i t h
�complete emphasis on t o t a l t r a c k e r e r r o r models. These models w i l l be
t r u n c a t e d c o n s i d e r i n g o n l y c r o s s - c o r r e l a t i o n and numerical s i g n i f i c a n c e .
The i n t e r r e l a t i o n s h i p s between the t r a c k e r e r r o r s and t h e guidance e r r o r s
w i l l a l s o be e v a l u a t e d .
b.
Saturn
Stage C o n t r a c t o r (CCSD, New Orleans)
CCSD has a l l t h e computer programs needed t o c o n s t r u c t
a p o s t f l i g h t t r a j e c t o r y u s i n g a l l e x t e r n a l and onbsard t r a c k i n g d a t a .
They w i l l assume prime r e s p o n s i b i l i t y f o r t h e p o s t f l i g h t t r a j e c t o r y
from f i r s t motion through S-PVB c u t o f f p l u s 10 seconds beginning w i t h
A t r a j e c t o r y r e p o r t has been i s s u e d on SA-9 and SA-8
v e h i c l e AS-205.
t o demonstrate the c a p a b i l i t y t o e f f e c t i v e l y use t h e s e programs.
The
t r a j e c t o r i e s a g r e e extremely w e l l w i t h the t r a j e c t o r i e s e s t a b I i s h e d f o r
t h e s e v e h i c l e s by R-AERO-FF.
CCSD i s g a i n i n g f u r t h e r experience by
p r o c e s s i n g SA-10 t r a c k i n g d a t a on a r e l a x e d schedule, P a r a l l e l t r a j e c t o r y
e f f o r t s w i l l begin on v e h i c l e AS-201, and w i l l c o n t i n u e u n t i l CCSD assumes
prime t r a j e c t o r y r e s p o n s i b i l i t y .
c.
S a t u r n V C o n t r a c t o r (The Boeing Company)
The A e r o b a l l i s t i c s U n i t s o f TBC was a s s i g n e d t h e t a s k
o f developing a t r a c k i n g - d a t a e d i t i n g and f i l t e r i n g computer program i n
November 1964. This t a s k has been completed, approximately 5 months
behind schedule. This program i s now o p e r a t i o n a l . SA-8 a c t u a l t r a c k i n g
d a t a were used a s t h e f i n a l check case. A new t a s k assignment was i s s u e d
t o i n c o r p o r a t e a r e f r a c t i o n c o r r e c t i o n r o u t i n e and a measured parameter
t o e a r t h - f ixed plumbl i n e t r a n s f o r m a t i o n r o u t i n e i n t o t h e o p e r a t i o n a l
e d i t program. T h i s t a s k i s t o be completed by December 1.
The range i n s t r u m e n t a t i o n a n a l y s i s of S a t u r n I Block 11
t e s t f l i g h t s i s a l s o being done by TBC. The t r u n c a t e d t r a c k e r e r r o r
models f o r ground-based r a d a r and Mark 11 azusa have been used t o a n a l y z e
t h e d a t a from v e h i c l e s SA-5, SA-6, SA-7, and SA-9.
A report entitled
"Error Model S t u d i e s o f t h e E a s t e r n T e s t Range Tracking Systems" .has been
i s s u e d which d e s c r i b e s the r e s u l t s o f t h e s e a n a l y s e s . The SA-8 and SA-10
t r a c k i n g d a t a have been p r o c e s s e d , and t h e r e s u l t s a r e being c o n s o l i d a t e d
and documented.
O,
F l i g h t Mechanics Branch
1.
S a t u r n PB
( 1 ) The nominal S-IVB p r o p u l s i o n d a t a became a v a i l a b l e
on October 8 , 1965, w i t h a s s o c i a t e d complete v e h i c l e mass c h a r a c t e r i s t i c s
a v a i l a b l e t h e n e x t day.
S p a c e c r a f t mass c h a r a c t e r i s t i c s and S-IB s t a g e
p r o p u l s i o n and mass c h a r a c t e r i s t i c s had p r e v i o u s l y become a v a i l a b l e . The
�o p e r a t i o n a l t r a j e c t o r y , update 2, was generated during t h e p e r i o d
October 9 t o October 20, 1965, w i t h a n o f f i c i a l t r a n s m i t t a l o f t h e S-IVB
i n s e r t i o n c o n d i t i o n s t o MSC on F r i d a y , October 22, t h e d e a d l i n e date.
The extended overtime was r e q u i r e d f o r t h e g e n e r a t i o n of t h i s t r a j e c t o r y
d u r i n g t h i s period,
G r e a t e r confidence of o v e r a l l accuracy i s achieved
under a l e s s s t r i n g e n t time requirement,
A memrandum p r e s e n t i n g the r e v i s e d o p e r a t i o n a l
t r a j e c t o r y i s b e i n g expedited w i t h d e t a i l e d p r i n t o u t being made a v a i l a b l e
t o v a r i o u s p e r t i n e n t o r g a n i z a t i o n s . A more comprehensive review o f t h e
t r a j e c t o r y w i l l be subsequently published i n t h e '"S-201 Launch Vehicle
F l i g h t Mechanical Summary. "
A comparison of the s t a t e parameters a t S-I'VB
c u t o f f between t h e f i r s t and second o p e r a t i o n a l t r a j e c t o r i e s i s a s
follsws:
Parameter
P
.
Time
Altitude
Range
P a t h Angle
P r o p e l l a n t Reserve
P i t c h Command Rate
601.4 s e c
260.44 km
1632,4 km
82.070 deg
8000.00 l b s
-.56 d e g l s e c
592.6 s e c
260.54 km
1592.4 krn
82.073 deg
6245.00 l b s
-.I3 d e g l s e c
Work has begun on t h e d i s p e r s i o n a n a l y s i s .
should be completed w i t h i n two weeks,
This
( 2 ) The range s a f e t y t r a j e c t o r i e s w i l l be r e v i s e d and
t r a n s m i t t e d t o KSC and MSC on magnetic t a p e based upon t h e f i n a l o p e r a t i o n a l
t r a j e c t o r y . An a n a l y s i s was performed which determined t h e s t e e p e s t
t r a j e c t o r y the v e h i c l e could f l y during the e a r l y launch phase ( f i r s t
100 seconds), The u n r e s t r i c t e d aerodynamic d a t a have been t r a n s f e r r e d
t o o u r l a t e s t t u r n i n g r a t e deck, and w i l l be used t o compare the t u r n i n g
r a t e s o f t h e o p e r a t i o n a l t r a j e c t o r y w i t h t h o s e published i n Data Report
#5-65 f o r t h e r e f e r e n c e t r a j e c t o r y .
( 3 ) The c o n t r o l s t u d y f o r AS-201 i s near completion.
Wind l i m i t s f o r t h e maximum dynamic p r e s s u r e time o f f l i g h t should be
e s t a b l i s h e d n e x t week, M r . Showers, R-P&VE-S, has s t a t e d o r a l l y t h a t
t h e s t r u c t u r a l l i m i t s of t h e v e h i c l e a r e t h e l i m i t i n g f a c t o r f o r v e h i c l e s
AS-201 and 202. He s t a t e d t h a t f l e x i b l e body motions have been considered
i n e s t a b l i s h i n g t h e s e l i m i t s and has promised t o document t h i s i n a
memorandum.
�(4) C h r y s l e r has agreed t o d e l i v e r t h e l i f t - o f f and
s e p a r a t i o n s t u d i e s on AS-201 on o r about November 8. These r e p o r t s w i l l
be i n t e g r a t e d i n t o work b e i n g conducted on t h i s f l i g h t i n R-AERO-FMS.
F i r s t s t a g e p r o p u l s i o n d a t a became a v a i l a b l e October
18, 1965. The S-IVB p r o p u l s i o n d a t a t a p e became a v a i l a b l e October 26,
b u t d i f f i c u l t y by P&VE i n g e n e r a t i n g mass d a t a c a r d s has prevented
p r o g r e s s on AS-202 t r a j e c t o r y g e n e r a t i o n .
S p a c e c r a f t mass c h a r a c t e r i s t i c s
have been a v a i l a b l e s i n c e October 18, 1965, Deadline f o r f i r s t o p e r a t i o n a l
t r a j e c t o r y i s November I o r 30 days a f t e r r e c e i p t o f s p a c e c r a f t d a t a ,
whichever i s l a t e r .
The Aerospace Physics S e c t i o n , CCSD, i s p r e p a r i n g t h e
r a n g e s a f e t y package (Cape t a p e and d a t a r e p o r t ) f o r t h e r e f e r e n c e
The Cape t a p e , which w i l l c o n t a i n 8 range s a f e t y t r a j e c t o r i e s
trajectory.
a s r e q u i r e d by ETR, w i l l be ready f o r check by t h e f i r s t week i n November.
CCSD i s g e n e r a t i n g t h e range s a f e t y package f o r t h e
l a t e s t r e f e r e n c e t r a j e c t o r y . The Cape t a p e i s t o be r e a d y by t h e l a s t
of October, and t h e d a t a r e p o r t i n November.
e. T h r u s t O s c i l l a t i o n S t u d i e s : A l l t h r u s t o s c i l l a t i o n
c a s e s from P&VE of amplitude l e s s t h a n 5k peak-to-peak have been run
and r e s u l t s t a b u l a t e d , Analysis i s n o t y e t complete.
2.
Saturn V
The range s a f e t y d a t a r e p o r t which i s almost completed,
contains turning r a t e s , e f f e c t s o f d e s t r u c t , drag data, i n j u r y probabili t i e s , and o t h e r p e r t i n e n t range s a f e t y information. The r e p o r t w i l l be
d i s t r i b u t e d i n November.
Boeing i s making s t u d i e s t o e s t a b l i s h impact and i n j u r y
p r o b a b i l i t i e s f o r malfunctioning vehicles.
Performance parameters a r e
being i n v e s t i g a t e d , and the r e s u l t s w i l l be used i n e s t a b l i s h i n g t h e
composite t r a j e c t o r y t o use f o r range s a f e t y l i m i t s . Documentation i s
i n progress.
�D.
O p e r a t i o n s S t u d i e s Branch
1.
Saturn I B
a. A memorandum p r e s e n t i n g t h e expected dynamic p r e s s u r e
and atmospheric d e n s i t y f o r AS-201 and AS-202, assuming a f i r s t q u a r t e r
1966 launch f o r AS-201 and a second q u a r t e r 1966 launch f o r AS-202, has
been d i s t r i b u t e d , Both t h e nominal and +30 v a l u e s were given,
b. A d r a g c o e f f i c i e n t and an atmospheric d e n s i t y s h i f t
c u r v e , which transforms t h e a l t i t u d e dependent atmospheric d e n s i t y i n t o
a time and a l t i t u d e dependent atmospheric d e n s i t y , were s u p p l i e d t o
R-AERO-DA f o r use w i t h t h e SA-283 P r e l i m i n a r y O r b i t a l Reference T r a j e c t o r y ,
The s h i f t curve i s t h e r a t i o of a time and a l t i t u d e dependent atmosphere
( d e f i n e d f o r R-AERO-FO from p r e v i o u s o r b i t a l decay h i s t o r y ) t o t h e 1962
US Standard Atmosphere,
c. A memorandum p r e s e n t i n g t h e aerodynamic t o r q u e s a s a
f u n c t i o n o f a n g l e of a t t a c k f o r SA-203 and SA-204 has been d i s t r i b u t e d .
Both t h e nominal and +30 expected t o r q u e s were p r e s e n t e d . The d a t a f o r
SA-203 were based on a f i r s t q u a r t e r 1967 launch d a t e , and t h e d a t a f o r
SA-204 were based on a l a s t q u a r t e r 1967 launch d a t e . M r . B a l l a n c e ,
R-AERO-AT, s u p p l i e d t h e n e c e s s a r y aerodynamic d a t a .
d. A memorandum has been w r i t t e n concerning t h e communication
coverage f o r SA-203 o r b i t a l sequencing. This memorandum g i v e s t h e o r b i t a l
coverage f o r SA-203 f o r Radar O r b i t a l Coverage, Telemetry O r b i t a l Coverage,
and T e l e v i s i o n and Update O r b i t a l Ground Communications.
The i n f o r m a t i o n
assumes no v e n t i n g w h i l e i n o r b i t . As soon a s new o r b i t a l d a t a which
i n c l u d e v e n t i n g and performance d i s p e r s i o n s a r e g e n e r a t e d , a new memorandum
w i l l be w r i t t e n t o i n c l u d e t h e s e p e r t u r b a t i o n s ,
e. R-AERO-DA was supplied w i t h a d e t a i l e d o r b i t a l t r a j e c t o r y
p r i n t on SA-211 f o r t h e 1 3 t h t o 1 6 t h day i n o r b i t .
This p r i n t was f u r n i s h e d
a t t h e i r request,
2.
Saturn V
A memorandum d e f i n i n g t h e minimum o p e r a t i o n a l t r a c k i n g
c o n s t r a i n t s a s s o c i a t e d w i t h t h e S a t u r n V d i r e c t a s c e n t mode has been
distributed.
Since continuous coverage of t h e e n t i r e burn of t h e
S a t u r n V d i r e c t a s c e n t mode t r a j e c t o r y was not p r a c t i c a l , an a l t e r n a t e
mode o f communication coverage was p r e s e n t e d . More work i s being done
on t h e p o s t - f l i g h t e v a l u a t i o n requirements f o r t h e d i r e c t a s c e n t mode.
3.
General
A study i s being conducted t o compare t h e a c c u r a c i e s of
v a r i o u s t r a c k i n g systems a s a r e s u l t of a n a c t i o n item i n a memorandum,
R-ASTR-IP-433-65, from C o - S e c r e t a r i e s , Instrumentation/~ommunicationP a n e l ,
�Minutes o f t h e 1 6 t h Meeting o f t h e Instrumenta~ion/~ommunication
Panel.
This a c t i o n gave MSFC t h e r e s p o n s i b i l i t y t o i n i t i a t e a s t u d y on t h e
p o s s i b i l i t y s f r e p l a c i n g t h e Azusa system w i t h a n S-Band system compatible
w i t h t h e USB. Data a r e now being prepared u s i n g t h e G-DOP (Geometric
D i l a t i o n of P r e c i s i o n ) technique which w i l l p r e s e n t t h e 1, 2, and 3 0
e r r o r s i n determing t h e v e l o c i t y components from t r a c k i n g d a t a of t h e
v a r i o u s system t a k e n i n d i v i d u a l l y and j o i n t l y ,
1.
Heybey, W, H., "Ground Level A c o u s t i c a l Foci i n a Three-Layered
Atmosphere,'VASA Tt-3 X-53344, October 7 , 1965, U n c l a s s i f i e d .
2.
Weichel, R. J., "SA-10 F l i g h t T e s t Data Report," NASA TM X-53345,
October 7 , 1965, U n c l a s s i f i e d .
3.
Nunkey, B. W., " S t a t i c Aerodynamic C h a r a c t e r i s t i c s o f the Apollo
S a t u r n I B V e h i c l e , " HASA TM X-53348, October 13, $965, U n c l a s s i f i e d .
4.
G i l l i s , W. T o , and T. T e l f e r , "AS-204 Launch Vehicle Reference
T r a j e c t o r y , " NASA TI4 X-53349, October 1 9 , 1965, U n c l a s s i f i e d ,
5.
R o b e r t s , W. T., "An Environmental Model f o r Van A l l e n B e l t Protons ,"
NASA 7% X-53351, October 21, 1965, U n c l a s s i f i e d .
6.
P i t c o c k , Robert E., " E f f e c t s of Minuteman Cant Angles on t h e S t a t i c
L o n g i t u d i n a l S t a b i l i t y and Axial Force C h a r a c t e r i s t i c s of t h e S a t u r n
~~/Apol%o/~inutem
Conf
a n Fguration, '' Aero I n t e r n a l Note 24-65,
October 25, 1965, U n c l a s s i f i e d .
7.
Burns, R. E . , "Note on t h e Conditions o f W e i e r s t r a s s , Legendre,
J a c o b i and Clebsch i n V a r i a t i o n a l C a l c u l u s , ' ~ e r oI n t e r n a l Note 24-65,
October 25, 1965, U n c l a s s i f i e d .
8.
K i e f l i n g , L a r r y , " T h e o r e t i c a l P l i g h t Bending Response of a S a t u r n I
Vehicle t o a SinusofdaP," Aero I n t e r n a l Note 25-65, October 28, 1965,
Unclassified.
9.
Jones, J e s s H. , q ' I n v e s t i g a t i o n o f A c c i d e n t a l Explosion i n Connection
w i t h C o n t r a c t NAS8-20223," O f f i c e Mem R-AERO-AU-65-48, d a t e d
October 11, 1965, U n c l a s s i f i e d .
10,
Schutzenhofer, L., "Preliminary Estimate of the Unsteady Base P r e s s u r e
F l u c t u a t i n g Environment f o r t h e S a t u r n W V e h i c l e , " O f f i c e Memo
R-AERO-AU-65-44, U n c l a s s i f i e d .
�11.
Young, James C., "The A e r o e l a s t i c C h a r a c t e r i s t i c s of t h e S a t u r n I B
SA-202 Launch Vehicle; Des ign Environment, I' Off i c e Memo R-AERO-AU65-33, October 20, 1965, U n c l a s s i f i e d .
12.
Young, James C., "Design Environment A e r o e l a s t i c C h a r a c t e r i s t i c s
of t h e S a t u r n V e h i c l e , " Of £ i c e Memo R-AERO-AU-65-54, U n c l a s s i f i e d .
13.
P l a t z e r , Maximillian, "Panel F l u t t e r on S a t u r n I B and V Vehicles ,'I
O f f i c e Memo R-AERO-AU-65-61, October 29, 1965, U n c l a s s i f i e d .
APPROVAL
"
--
E. D. G e i s s l e r
D i r e c t o r , Aero-Astrodynamics Laboratory
Aero-Astrodynamics Laboratory
DISTRIBUTION
R-AERO-DIR
Dr. Geissler
Mr. Jean
R-AERO-P
(8)
R-AERO-S
(8)
R-AERO-R
M r . B u t l e r (4)
M r s High tower
.
R-AERO-D
(16)
R-AERO-A
(20)
R-AERO-G
(5)
R-AERO-F
(20)
R-AERO-T
M r . Murphree
M r . Cummings
D r . Heybey
Dr. Sperling
M r . Dickey
M r . Jandebeur
M r . Lavender
D r . Liu
R-DIR
D r . McCall
PA0
M r , Kurtz
MS-H
Mrs. J e r r e l l ( 3 )
�
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Saturn V Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000043
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: November 2, 1965."
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George C. Marshall Space Flight Center
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1965-11-02
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1960-1969
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Saturn Project (U.S.)
NASA space programs
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Progress reports
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Saturn V Collection
Box 15, Folder 31
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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Text
AERO-ASTRODYNANICS LABORATORY
MONTHLY PROGRESS REPORT
December 13. 1965
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I* TECHNICAL AND SCIENTIFIC STAFF'
11 PROJECTS OFFICE
III AEROSPACE ENVIROXMENT OFFICE
IV. ASTRODYNAMECS AND GUIDANCE THEORY DIVISION
A
Astrodynamics Branch
B
Guidance Theory Branch
C
Optimization Theory Branch
V
AERODHNA.NH@S DIVISION
A
Aerodynamic Design Branch
1. Saturn IB
2
Saturn ~ ~ J ~ e n t a u r
3 0 Saturn V
4 - General
B
Electromechanical Branch
C
F a c i l i t i e s Branch ..........o.O.De.....
D.
F l u i d Mechanics Research O f f i c e
E
Thermal Environment Branch
I n Saturn I
2
Saturn I B
3
Saturn P ~ I ~ e n t a u r
4
Saturn V
5 0 General
F
Unsteady Aerodynamics Branch
vl
DYNAMICS
PLIGHT MECHANICS DIVISION
A
Applied Guidance and P l i g h t Mechanics Branch
1- S a t u r n I B
2
Saturn V
3
General
4
Advanced Apollo Program ( U P )
5
Contractors
B
Control Theory Branch ...................,......9.
1
Saturn I B
2
Saturn ~ B l c e n t a u r
3 0 Saturn V
4* General
5. C o n t r a c t o r s
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Dynamics Analysis Branch .........................CI.O
1 Saturn I B
2
Saturn I ~ / ~ e n t a u r
Saturn V
3
4
General
5
Contractors
D
Advanced P r o j e c t s study Branch
VII
FLIGHT EVALUATION AND OPERATIONS STUDIES DIVISION
A
Special P r o j e c t s O f f i c e ...........................o.e
B
F l i g h t Evaluation Branch
1
Saturn H ..........eO~o.eD.e.
2
Saturn I B ...................................ee
3 - Saturn V
Contracts
4
C
F l i g h t Mechanics Branch
1
Saturn HB ................................e.~e.o...
2
General
D
Operations Studies Branch
l o Saturn I ..................................O.OO.
Saturn I B
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2
3
Saturn V
4
General
PUBLICATIONS
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�AERO-ASTRODYNAMLCS LABORATORY
MONTHLY PROGRESS REPORT
December 13, 1965
I. TECHNICAL AND SCIENTIFIC STAFF
1. A computer program to determine focal points in a three-layered
atmosphere has been written and checked out. Work is in progress on a
systematic survey of variations in focal points resulting from variations
in atmospheric parameters (Mabry)
.
2. A multistage optimization procedure, being programmed for the
CDC-3208, is being documented and a report 03 Linear guidance techniques
is being prepared (Dickey).
TI. PROJECTS OFFICE
1.
Incentive Contracts
Discussions of the Saturn EB, S-IVB Stage Flight Performance
Incentive Plan have resulted in modification of the plan to include
direct measurement of subsystem performance during flight. The effort
to include this direct measurement was hampered by a lack of defined
tolerances for each of the major subsystems. The incentive plan was
subsequently modified to include subsystem performance under an award
fee concept. The total Flight Performance Plan, which is being reviewed
before final typing, includes predicted payload capability, mission
performance capability, and telemetry performance under the incentive
fee concept and subsystem performance under the award fee concept.
2.
Fl ighL Mechanics Sub-Panel Activities
a. The Eighth Reference Trajectory Sub-Panel Meeting, held at
MSC on November 4, 1965, is documented in R-AERO-P-472-65.
b. The Fifteenth Guidance and Performance Sub-panel Meeting,
held at MSG on November 5 , 1965, is documented in R-AERO-P-473-65.
111.
AEROSPACE ENVIRONMENT OFFICE
1. The final report (Part IV), '"Mathematical Wind Profiles'' has
been received from the Lockheed California Company. This report presents
detailed procedures for predicting a future vector wind profile from
present and past wind profiles, for appl.icat.ionat Cape Kennedy, Florida.
It is being reviewed, along with the other three parts, for NASA publication.
�2. NASA TM X-53023, " T e r r e s t r i a l EnvFromen.t ( C l i m a t i c ) C r i t e r i a
g u i d e l i n e s f a r u s e i n Space Vehicle Deve10prnent,'~ i s being r e v i s e d .
This r e p o r t , along w i t h a s i m i l a r r e p o r t on space e n v i r o m e n t c r i t e r i a ,
i s used by MSPC i n o u r program d e s f g a studies.
3 . Two r e p o r t s a r e being pu5lished a s NASA Technical Memorandums.
The f i r s t i s an environmental model of Vsn Alley b e l t p r o t o n s and t h e
second i s an a n a l y s i s of l a t e s t d a t a o 2 upper atmospheric winds. During
November a paper e n t i t l e d , "Decrease in E l e c t r o n Density i n t h e Ionosphere
Following t h e Passage s f S a t u r n I," by N r - Fehker and M r . Roberts of t h e
Space E n v i r o m e n t Group, was p r e s e n t e d by M r . P e l k e r a t t h e Second U S
Symposium en I ? t e r a e t f o w s o f Space Vehicles with an Ionized Atmosphere.
M r . P e l k e r has beem i n v i t e d t o an ARPB/IDA m e e t i ~ gi n P e b r t a r y t o p r e s e n t
t h e s u b j e c t s f t h i s paper i n more d e t a i l .
1.
Cislunar T r a j e c t o r y S t u d i e s
a.
Contractor
2 2 a d d i t i o n t o t h e p u b l i c a t i o n named in t h e October
p r o g r e s s r e p s r t , a n o t h e r r e p o r t , "Launch Windows f o r C i s l u n a r T r a j e e t o r i e s , "
was p u b l i s h e d . This r e p o r t d i s c u s s e s t h e t r a j e c t o r y c o n s t r a i n t s and
r e l a t e d e f f e c t s on launch window by g e o m e t r i c a l c o n s i d e r a t i o n s and t h e
mathematical model which was used t o g e n e r a t e launch c o n d i t i o n s f o r t h e
t r a j e c t e r i e s r e p o r t e d on i n t h e e a r l i e r p u b l i c a t i o n .
The s t u d y of c i s l u n a r o r b i t s i n t h e e l l i p t i c a l three-body
model c o n t i n u e s a t a slow r a t e on t h e d i g i t a l o u t p u t program.
Since
c o r r e c t i o n s t o t h e program f o r t h e t r i c e a n a l o g o u t p u t computer a r e
n o t y e t p r o v i d i n g a c c u r a t e c a l c u l a t i o n s from t h a t program, use of a n o t h e r
a n a l c g o u t p u t computer capable of more a c c u r a t e computation i s being
considered.
2.
Conic I q t e r p h a n e t a r y Program
A s t u d y of Earth-to-Mercury t r a j e c t o r i e s being conducted t o
check o u t t h e new c o n i c i n t e r p l a n e t a r y program and f a m i l i a r i z e branch
p e r s o n n e l w i t h t h e deck i s n e a r l y complete f o r t h e y e a r 1969. The
minimtun C3 f o r t h a t p e r i o d i s about 43 km2/sec2. A C 3 of about 55 km2/sec2
i s needed t o p r o v i d e a Pauxch window of 30 days. The s t u d y w i l h ' b e
continued t o i n c l u d e t h e y e a r 9970. No new d i f f i c u l t i e s have been
experienced r e c e n t l y w i t h t h e program i n d i c a t i n g t h a t it i s now i n c o r r e c t
working o r d e r .
�B.
Guidance Theory Branch
1.
Saturn
I- centaur
Voyager (Northrop Schedule Order NQ. 7)
A f i r s t - d r a f t copy of t h e Northrop r e p o r t on a l a r g e s c a l e
u r
guidance system e r r o r a n a l y s i s has been
S a t u r n ~ ~ / ~ e n t aVoyager
reviewed.
The a n a l y s i s i s t o parking o r b i t under t h e assumption t h a t
IGM c o n t r o l s t h e Centaur s t a g e . The r e p o r t w i l l be c i r e u E a t e d . The
s c h e d u l e o r d e r has been modified so t h a t f u t u r e s t u d i e s w i l l c o n s i d e r
t h e S a t u r n V v e h i c l e t o be t h e Voyager launch v e h i c l e .
2.
LOW Thrust Guidance and Performance (Northrop Schedule
Order No. 6 )
Computer progra.ming has been i ~ i t f a t e dt o determine t h e
f e a s i b i l i t y s f a guidance technique for t h e s p i r a l escape t r a j e c t o r y
suggested ill Aero I n t e r n a l Note .?'!
14-65, Gsnsi.derabhe in-house e f f o r t
has been p u t i n t o t h e p r o o f r e a d i n g sf guidance e q u a t i o n s of an HG,M type
f o r p o s s i b l e use around t h e sun; a f e w c l e r i c a l m i s t a k e s have been
found.
Since t h i s work i s t e d i o u s , X o r t h r o p i s making an independent
check of t h e guidance e q u a t i o n development b e f o r e a t t e m p t i n g t o program
t h e s e e q u a t i o n s f o r a f e a s i b i l i t y s t u d y which w i l l probably be done
i n house,
Attempts t o compute an optimum low t h r u s t s p i r a l escape
t r a j e c t o r y a r e c o n t i n u i n g ; a s y e t , i t has been impossible t o o b t a i n
convergence. It i s p o s s i b l e t h a t end c o n d i t i o n s i n a d d i t i o n t o zero
energy have t o be s p e c i f i e d t o produce a r e a s o n a b l e t r a j e c t o r y and t h a t
t h e s p e c i f i c a t i o n s f escape end c o n d i t i o n s a l o n e i s n o t enough.
3.
Implementation
a . The t r a n s v e r s a l i t y c o n d i t i o n s t o be used f o r t h e
d e t e r m i n a t i o n o f an o p t i m a l t r a j e c t o r y from a c i r c u l a r o r b i t around
t h e e a r t h t o escape v e l o c i t y have been added t o t h e ~ e w t o n ' smethod
i s o l a t i o n computer program. When t h e p r o g r a m i n g is completely
checked o u t , t h e deck can be used t o determine escape t r a j e c t o r i e s
f o r g r a d u a l l y d e c r e a s i n g t h r u s t l e v e l s . As t h e t h r u s t l e v e l f o r a
p a r t i c u l a r v e h i c l e d e c r e a s e s , t h e t r a j e c t o r y begins t o r e q u i r e more
and more s p i r a l s about t h e e a r t h t o r e a c h escape v e l o c i t y . This
c h a r a c t e r i s t i c of t h e problem has r e q u i r e d t h e i n v e s t i g a t i o n of more
e f f i c i e n t numerical i n t e g r a t i o n p r o c e s s e s , but a t t h e p r e s e n t t i m e ,
none of t h e methods y i e l d s u f f i c i e n t l y a c c u r a t e r e s u l t s .
The i n v e s t i g a t ion i s continuing.
b.
The m o d i f i c a t i o n s t o t h e ~ e w t o n ' smethod i s o l a t i o n
r o u t i n e t o allow t h e i n c l u s i o n of s w i t c h i n g f u n c t i o n s have been programmed
and a r e being checked o u t . These m o d i f i c a t i o n s w i l l allow t h e determinat i o n of o p t i m a l s t a g i n g p o i n t s f o r m u l t i s t a g e v e h i c l e s o r t h e d e t e r m i n a t i o n
of o p t i m a l o r b i t a l t r a n s f e r t r a j e c t o r i e s w i t h c o a s t i n g phases.
�c . Recursion r e l a t i o n s h i p s have been developed f o r t h e
computation of optimum low t h r u s t i n t e r p l a n e t a r y t r a j e c t o r i e s .
The
v a r i a b l e s i n t h e e q u a t i o n s of motion were expanded a s power s e r i e s i n
t i m e , and r e c u r s i o n formulas were developed f o r t h e Euler-Lagrange
e q u a t i o n . P e r t u r b i n g f o r c e s i n c o r p o r a t e d i n t o t h e e q u a t i o n s of motion
were t h e e a r t h , t h e e a r t h ' s o b l a t e n e s s , t h e moon, t h e sun, and t a r g e t
P l a n s a r e t o i n c o r p o r a t e t h e e a r t h ' s t h i r d and f o u r t h harmonic
planet.
terms i n t o t h e e a r t h ' s g r a v i t a t i o n a l f i e l d and extend t h e use of t h e
program t o a more g e n e r a l i n t e r p l a n e t a r y deck by addfng more terms f o r
t h e r e m a h l n g p l a n e t s . Programming of t h e r e h t i f o n s h i p was i n i t i a t e d .
d. A s t u d y has been. i n i t i a t e d t o determine t h e f e a s i b i l i t y
of n u m e r i c a l l y i n t e g r a t i n g t h e e q u a t i o n s s f motion and Euler-Lagra3ge
equations (using a l a r g e i n t e g r a t i o n s t e p s i z e ) f o r possible use as a
low t h r u s t guidance scheme. Newton's method i s beEng used t o determine
t h e i n i t i a l m u l t i p l i e r s . A computer program i s being i n c o r p o r a t e d .
The f e a s i b i l i t y of t h i s approach w i l l f i r s t be determined f o r more
c o ~ v e n t i c l n a lh i g h o r medium t h r u s t v e h i c l e s .
a.
Aeronutronics Contract No. NAS8-20150
Work i s c o n t i n u i n g t o e v a l u a t e t h e range of v a l i d i t y
o f f i r s t and second o r d e r p e r t u r b a t i o n s o l u t i o n s f o r t h e c o n s t a n t low
a c c e l e r a t i o n t r a j e c t o r y w i t h t h e t h r u s t i n e i t h e r t h e r a d i a l o r circumf e r e n t i a l d i r e c t i o n . The e v a l u a t i o n i s being made f o r v a r i o u s t h r u s t
a c c e l e r a t i o n l e v e l s . Future work w i l l c o n s i d e r t h r u s t a t an a r b i t r a r y
constant angle t o t h e radius vector.
b.
Hayes I n t e r n a t i o n a l
- NAS8-20176
A p e r t u r b a t i o n technique r e c e n t l y r e p o r t e d seems
u n s a t i s f a c t o r y f o r t h e low t h r u s t t r a j e c t o r y computation problem because
of t h e d i f f i c u P t i e s i n o b t a i n i n g i n t e g r a l s of h i g h e r o r d e r terms. Also,
i t seems t h a t i n i t i a l v a l u e s of Lagrange m u l t i p l i e r s must c o n t i n u e t o be
determined by i t e r a t i o n . During t h i s r e p o r t p e r i o d , a major e f f o r t has
been d i r e c t e d t o a p o s s i b l e means of s o l u t i o n f o r t h e low t h r u s t guidance
problem.
The r e c t a n g u l a r c o o r d i n a t e e q u a t i o n s of motion a r e expanded t o
second o r d e r t o r e p r e s e n t t h e g f o r c e w i t h h i g h e r o r d e r terms d e l e t e d ;
cakcuPus of v a r i a t i o n s i s a p p l i e d t o t h i s simple s e t . F u r t h e r s t u d i e s
w i l l e x p l o r e t h e p o s s i b i l i t y of d e v i s i n g a guidance technique based o n
these equations, i f possible.
c.
I l l i n o i s I n s t i t u t e o f Technology
- NAS8-20129
S e v e r a l d i f f e r e n t s t e e r i n g laws a r e being programmed and
e v a l u a t e d f o r t h e s p i r a l a s c e n t and c a p t u r e phase.
The keynote of t h i s
c o n t r a c t i s s i m p l i c i t y and e a s e of implementation. Techniques, such a s
�f i t t i n g an approximate t a n g e n t i a l t h r u s t t r a j e c t o r y through p r e s e n t
p o s i t i o n and t h e d e s i r e d t e r m i n a l ccmdition t o d e f i n e v e l o c i t y r e q u i r e d
followed by Vg s t e e r i n g t o remove t h e v e l o c i t y e r r o r , a r e used. Another
approach a t t e m p t s t o c o n t r o l t h e e c c e n t r i c i t y v e c t o r in d i r e c t i o n and
magnitude.
S i m i l a r approaches a r e being i n v e s t i g a t e d f o r t h e c a p t u r e
s p i r a l w i t h s t e e r i n g and t h r u s t c o n t r o l based cn approximate c h a r a c t e r i s t i c s s f t h e nominal t r a j e c t o r y . For t h e s e simple approaches t o work,
i t i s n e c e s s a r y t o command t h e a c c e l e r a t i e n v e c t o r .
d.
U n i v e r s i t y of North C a r o l i n a
- NAS8-20106
This c o n t r a c t has t e r m i n a t e d , and t h e f i n a l r e p e r k i s
being prepared.
e.
United A i r c r a f t
- ;;AS8-20k19
D f f f i c u l t i e s have been experienced i n t h e implementation
o f t h e Newton-Raphson f ~ w i t e2%fferen-cce a l g o r i t h m a s t h e v e h i c l e approaches
a p l a n e t . The major diEficuBty i s i n prcvidewg c l o s e r t i m e s t e p s o r mesh
p o i n t s a s r e q u i r e d , A procedure t o provide program control o f mesh p o i n t
s p a c i n g has been d e v i s e d , and programnigg has begun. A s u b r o u t i n e which
computes t h e p o s i t i o c and t h r e e time d e r f v a t i v e s of each p l a n e t has been
It i s planned t o hold a meeting a t MSPC w i t h United A i r c r a f t
checked o u t .
t o d i s c u s s t h e c o n t r a c t and p o s s i b l e s i m p l i f i c a t i o n s which may be made.
C.
O p t i m i z a t i o n Theory Branch
I. A n a l y t i c s t u d i e s on t h e a p p l i c a t i o n of opti.mal c o n t r o l t o
load r e l i e f system d e s i g n have been concerned w i t h d e t e r m i n a t i o n of t h e
o p t i m a l c o n t r o l f o r d e t e r m i n i s t i c dl.sturbances.
Two d i f f e r e n t formulat i o n s of t h e optimum contrsE have r e s u l t e d f o r l i n e a r p l a n t s w i t h
q u a d r a t i c performance indexes:
a. Control a s a f u n c t i o n s f time, i n v o l v i n g a simple
two-point boundary v a l u e problem w5ich i s s o l v a b l e w i t h o u t i t e r a t i o n .
b. Control having two components, feedback g a i n s which a r e
s o l u t i o n s t o t h e corresponding r e g u l s t o r problem, and an irn~tegralf u n c t i o n
of t h e d i s t u r b a n c e and t h e c l o s e d loop p l a n t response.
An i n v e s t i g a t i o n i s being made t o determine i f t h e same
c o n t r o l can be achieved p u r e l y by feedback of the s t a t e w i t h t h e g a i n s
now dependent on t h e d i s t u r b a n c e . A s e a r c h w i l l be made u s i n g t e c h n i q u e s
suggested by Whitbeck of Corner1 and t h o s e suggested by Shridhar a s
'"pecific Optimal Control" t e c h n i q u e s .
Apparent e r r o r s p r e v i o u s l y undetected i n t h e computer progra-m
a s s o c i a t e d w i t h t h i s s t u d y a r e being c o r r e c t e d .
�2.
An a t t e m p t has been made t o apply t h e Kopp-Moyer n e c e s s a r y
c o 2 d i t i o n f o r o p t i m a l i t y t o a s i n g u l a r s o l u t i o n of a g e n e r a l i z e d one-stage
t r a j e c t o r y o p t i m i z a t i o n problem. D i f f i c u l t y has been encountered i n
g e n e r a t i n g t h e r e q u i r e d h i g h e r o r d e r d e r i v a t i v e s , so t h a t r e s u l t s a r e
i n c o n c l u s i v e t o d a t e . The t e s t would i n d i c a t e whether o r n o t t h e s i n g u l a r
s o l u t i o n , f o r which a n a n a l y t i c a l e x p r e s s i o n has been developed, i s a
candidate f o r the optimal t r a j e c t o r y .
3.
b h r t h r o p Schedule Order No. 2
Objective:
f o r l i n e a r systems.
To i n v e s t i g a t e
analytFcaE d e s i g n
techniques
M o d i f i c a t i o n s suggested by MSPC t o ~ o r t h r o p ' sa n a l y t i c a l
d e s i g n method t o reduce t h e s e n s i t i v i t y of t h e systems designed t o
It a p p e a r s ,
parameter v a r i a t f s n s were i n c o r p o r a t e d i n t o t k e program.
a t Beast i n i t i a l l y , t h a t no improvement has beer. made s i n c e t h e program
i s now f r e e t o s p e c i f y urrdesirable ope^^ 130p f F l f e r p o l e s , and i t does so.
4.
Systems Technology I n c o r p o r a t e d
- NAS8-11419
O b j e c t i v e : A ~ a l y t i c a ls t u d i e s of t h e c o n t r o l of h i g h l y coupled launch v e h i c l e s , i n c l u d i n g t h e development o f s i m p l i f i e d dynamics
r e p r e s e n t a t i o n f o r d e s i g n purposes, d e t e r m t n a t i o n of c o n v e n t i o n a l system
performance l i m i t a t i o n s , e v a l u a t i o n of advanced c o n t r o l t e c h n i q u e s , and
s e n s i t i v i t y analysis.
The f i r s t l i s t e d o b j e c t i v e bas been met and t h e r e p o r t on
t h i s p o r t i o n of t h e s t u d y i s t o be published s h o r t l y . C o n t r a c t funds
have been expended w i t h o u t t h e b a s t t h r e e o b j e c t i v e s being met in f u l l ;
t h e c o n t r a c t o r i s s u b m i t t i n g a p r o p o s a l f o r about a f o u r o r f i v e manmonth e x t e n s i o n t o complete t h e c o n t r a c t .
O b j e c t i v e : To i n v e s t i g a t e t h e f e a s i b i l i t y and o p e r a t i o n
of t h e d i g i t s l a d a p t i v e f i l t e r , a c u r v e - f i t t i n g procedure f o r e l i m i n a t i n g
f l e x u r e components from t h e c o n t r o l s i g n a l .
The d r a f t of t h e f i n a l r e p o r t was reviewed d u r i n g t h i s
period.
Four pages of e r r a t a , and s e v e r a l s u g g e s t i o n s on rearrangement
o f t h e r e p o r t t o improve i t s r e a d a b i l i t y , were t r a n s m i t t e d t o McDonnell.
The c o n t r a c t o r i s c o r r e c t i n g t h e o r i g i n a l r e p o r t , and has agreed t h a t an
accompanying summary r e p o r t would h e l p c l a r i f y t h e achievements of t h e
contract.
�cn
u
ha, 6,
4
s 5
e
U
rn
4
a, o
3 $ Z
2a us 2m da,
h
.,-I
�b. A f l i g h t c o n t r o l system has been d ~ s i g n e dt o meet
performance s p e c i f i c a t i o n s a t f o u r nominal f l i g h t c o n d i t i o n s , and t h e
accepted range of i d e a l bending mode s l o p e s a t r a t e gyro l o c a t i o n s has
been d e f i n e d . Work d u r i n g t h i s p e r i o d has r e s u l t e d i n a r e d u c t i o n i n
complexity o f t h e system.
c . E v a l u a t i o n of t h e m u l t i p l e b l e n d e r c o n f i g u r a t i o n has
shown t h a t performance s p e c i f i c a t i o n s can be met f o r t h e zmesmfnal system,
b u t complexity and peed f o r a c c u r a t e knowledge of mode s l o p e s make t h i s
a n i m p r a c t i c a l c o n f i g u r a t i o n . Recent e f f o r t has been d i r e c t e d toward
development o f a new b l e n d e r l o g i c f o r a two-gyro system.
V.
AERODYXAMSCS DIVISION
A.
Aerodynamic Design Oranch
1.
S a t u r n IB
a. Aerodynamic c h a r a c t e r i s t i c s o f t h e Apollo-Saturn I B
v e h i c l e s f o r range s a f e t y d e f i n i t i o n a r e b e i ~ gr e f i n e d . Data w i l l be
p r e s e n t e d f o r t h e f i r s t and second s t a g e f l i g h t and a b o r t c o n f i g u r a t i o n s
f o r t h e power-on and power-off c o n d i t i o n s . These d a t a i n c l u d e t h e
8.0.
a n g l e of a t t a c k range of Co t o 180' and Mach number range 0
Also included a r e d r a g d a t a f o r v a r i o u s s t a g e s and components a s a
f u n c t i o n of Mach number. b a d d i s t r i b u t i o n s f o r high a n g l e s of a t t a c k
a r e g i v e n t o d e f i n e break-up i n c a s e of l o s s of c o n t r o l . These d a t a
w i l l be p u b l i s h e d i n a RASA 'B"blX i n t h e near f u t u r e .
-
b. Small s c a l e model f o r c e t e s t s were conducted i n t h e
MSFC 14-inch t u n n e l t o determine some e f f e c t s of t h e S a t u r n I B t a i l
b a r r e l ramp on f i n l i f t c h a r a c t e r i s t i c s . T e s t s were conducted w i t h
and w i t h o u t t h e t a i l b a r r e l ramp. P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t
t h e t r a n s o n i c recompression shock generated by t h e t a i l b a r r e l ramp
has an i n s i g n i f i c a n t e f f e c t on f i n l i f t c h a r a c t e r i s t i c s . Vehicle
forebody a x i a l f o r c e was reduced.
Some i n t e r e s t i n g t r a n s o n i c d a t a t r e n d s were observed
d u r i n g t h i s i n v e s t i g a t i o n which have been a t t r i b u t e d t o model shock
reflections.
These r e s u l t s , which can be a p p l i e d t o t r a n s o n i c t e s t i n g
o f f i n n e d S a t u r n shapes i n a l a r g e number of f a c i l i t i e s , w i l l be
published.
c . Interna.8 p r e s s u r e h i s t o r i e s f o r t h e S a t u r n HB s p a c e c r a f t
compartment have been computed f o r v a r i o u s v e n t a r e a s and PU leakages.
The d a t a , documented i n R-AERO-AD-65-65, w i l l be used t o r e s i z e t h e v e n t
a r e a a n t h e AS-201 and AS-202 v e h i c l e s and t o provide r e v i s e d compartment
p r e s s u r e s f o r t h e AS-204 and subsequent v e h i c l e s w i t h t h e HW leakage
reduced t o 5.0 in2.
�d. Data f o r t h e ApoPlo-Saturn IB have been p u b l i s h e d i n
XASA TM X-53348.
This r e p o r t i n c l u d e s t o t a l v e h i c l e s t a t i c s t a b i l i t y ,
axial f o r c e c h a r a c t e r i s t i c s , load and p r e s s u r e d i s t r i b u t i o n s , s e p a r a t i o n
aerodynamics, and l i f t - o f f aerodynamics. These d a t a a r e being recommended
a s f i n a l d e s i g n c r i t e r i a a d w i l l supersede p r e v i o u s l y used memorandums.
S i n c e t h e s e d a t a w i l l r e p r e s e n t p r i m a r i l y a c o m p i l a t i o n and r e f i n e m e n t
o f p r e v i o u s c r i t e r i a , t h e y should have no e f f e c t on v e h i c l e hardware
design o r f l i g h t schedules.
2,
Saturn ~ ~ / ~ e n t a u r
The aerodyximic c h a r a c t e r i s t i c s of two proposed S a t u r n IB/
Centaur v e h i c l e s have been documented in R-AERO-AD-65-66,
These v e h i c l e s
a r e two s t u d y c o n f i g u r a t i o n s used i.9 an a 2 a l y s i s to determine t h e e f f e c t
o f i n c r e a s i n g t h e payload volume by v a r i o u s meam.
3.
Saturn V
a . Hir~ge>!cment Program: Yesti?& EY &he LeRG BO x 10-Soot
f a c i l i t y i s scheduled t o begfF on November 2 9 , 1965. ? k d e l h s t a k l a t b o n
l . s complete.
Static tnozzle p r e s s u r e d a t a w i l l be o b t a i n e d t o d e f i n e
hinge moments. TBC i s r e s p o n s i b l e f o r t e s t i n g and a n a l y s i s .
b.
S a t u r n V/Voyager:
The p r e l i m i n a r y aerodynamics f o r four
p r e l i m i n a r y c o n f i g u r a t i o n s s f t h e S a t u r n V Voyager a r e being determined.
The f o u r c o n f i g u r a t i o n s have c y l i n d e r l e n g t h s of 22.7 f e e t , 4 % f e e t ,
5 4 f e e t , and 7 5 f e e t between t h e BU and t h e g e n e r a l i z e d nose shape.
A c y l i n d e r l e n g t h o f 54 f e e t i s considered t o be t h e optimum a t t h i s
t i m e , and t h e aerodynamics f o r t h i s c o n f i g u r a t i o n have been g i v e n top
priority.
c . LOR S t a t i c S t a b i l i t y a r d Axial Force C h a r a c t e r i s t i c s :
All r e q u e s t e d d a t a have been r e c e i v e d from Geseral ~ y n a m i c s / ~ o n v a i r
e x c e p t t h e c u r v e - f i t t e d p l o t s and t h e f i n a l d a t a r e p o r t . The Ecefng
Company i s a n a l y z i n g t h a t p a r t of t h e d a t a which i s b e l f e ~ n x lt o be s f
s u f f i c i e n t accuracy t o m e r i t an a n a l y s i s . These d a t a ilaeabude t h e rclPEsg
moment d a t a , t h e p r e s s u r e r a k e d a t a o n t h e t a i l b a r r e l , t h e upper s t a g e
d a t a , and p o s s i b l y t h e a sop,tributiom to s t a t i c s t a b i l i t y end a x i a l f o r c e
c h a r a c t e r i s t i c s bekween POo and 2 0 Q .
d.
I n t e r f e r e n c e - F r e e Fin Program:
Plans a r e being f i ~ a l f z e d
f o r conducting S a t u r n V fin-shroud i n t e r f e r e v c e - f r e e load programs in
e a r l y 1966. The c o n t r a c t i s being n e g o t i a t e d w i t h Cornell f o r model
d e s i g n , f a b r i c a t i o n , and t e s t i n g i n t h e C o r n e l l t r a n s o n i c wind t u n n e l .
Supersonic d a t a w i l l be o b t a i n e d i n t h e Axes 9 x 7-foot t u n n e l FT
A p r i l 1966. Ames has t e n t a t i v e l y accepted t h i s program.
�4.
General
a . O r i f i c e Flow C o e f f i c i e n t Study: A conference concerning
t h e f e a s i b i l i t y of conducting t h e o r i f i c e c o e f f i c i e n t experimental program
i n t h e Ames 6-foot wind t u n n e l was h e l d a t Ames Research Center on November
3 , 1965. Marshall p r e s e n t e d t h e h i s t o r y and j u s t i f i c a t i o n f o r t h e s t u d y ,
w h i l e Northrop (who was conducting t h e i n v e s t i g a t i o n f o r MSFC) p r e s e n t e d
t h e proposed approach and t e s t program. Ames was q u i t e i n t e r e s t e d i n
t h i s s t u d y and has recommended acceptance to t h e i r management. We a r e
g u a r a ~ t e e dt e s t time i n J u l y 1966, w i t h t h e p o s s i b i l i t y of t e s t i n g i n
A p r i l 1966, provided Ames can n e g o t i a t e t h e f a c i l i t y o p e r a t i n g c o n t r a c t
by t h e f i r s t o f t h e y e a r .
b . J e t Simulation Study: The Thfokol j e t s i m u l a t i o n
c o n t r a c t was completed on November 1 2 , 1965. A r n i ~ i m a lfo8Pow-on
p r o p o s a l has b e e ~ ir e c e i s e d . This e f f o r t would b e ccncesmed p r i m a r i l y
w i t h s i m u l a t i e c of the F-l e w g i ~ . eturbine e x h s ~ s tand i t s e f f e c t on
eagfne plume c h a r a c t e r i s t i c s t o a dfscanee of two e x i t d i a m e t e r s
downstream. Some e f f o r t would be a v a i l a b l e t o determine engine s i m u l a n t
base c h a r a c t e r i s t i c s f a r i n p i t t o a n a l y t i c a l prolgrams b e i r g developed by
t h e Thermal Environme:2f S r a ~ c h . The c o s t of t h i s seven-month p r o j e c t
would be approximately $18,080.00.
The proposed work would be a l o g i c a l follow-on t o t h e
c o n t r a c t j u s t completed. However, b e f o r e a c c e p t i n g t h e p r o p o s a l , a
t e c h n i c a l r e p r e s e n t a t i v e from Thiokol w i l l p r e s e n t t o MSPC t h e f i n a l
r e s u l t s of t h e complete c o n t r a c t and d i s c u s s w i t h i n t e r e s t e d MSPC
p e r s o n n e l t h e d e t a i l s of t h e follow-on e f f o r t .
c. Viscous Cross-Plow Study: Models and b a l a n c e s n e c e s s a r y
f o r i n i t i a l t e s t s i n t h e MSFC 14-inch t u n n e l a r e a v a i l a b l e . T e s t s a r e
t e n t a t i v e l y scheduled t o begin i n January 1966.
This phase of t h e v i s c o u s cross-flow i n v e s t i g a t i o n w i l l
b e concerned w i t h t h e normal f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n V shapes
The
of v a r y i n g s c a l e and one o g i v e c y l i n d e r a t a n g l e s of a t t a c k t o 36".
e f f e c t s of Reynolds number on h i g h a l p h a v i s c o u s cross-flow L i f t w i l l be
s t u d i e d . The ogive c y l i n d e r d a t a w i l l be compared w i t h e x i s t i n g t h e o r i e s
a3d experimental d a t a .
R e s u l t s of t h e i n i t i a l MSFC i n v e s t i g a t i o n w i l l p r o v i d e
g u i d e l i n e s f o r t h e follow-on l a r g e s c a l e LTV t e s t t o be conducted i n t h e
second q u a r t e r o f 1966.
d. Compartment Venting Methods Documentation: A p r e s e n t a t i o n
of t h e method used by t h e Aerodynamic Design Branch t o compute compartment
i n - f l i g h t p r e s s u r e h i s t o r i e s has been completed. This p r e s e n t a t i o n i s t o
be r e l e a s e d i n an Aers-Astrsdynamics I n t e r n a l Note. Documentation of t h e
g e n e r a l procedure w i l l p r e s e n t e l a b o r a t e d e s c r i p t i o n s of procedure now
necessary in a l l design reports.
�e. T r i s s n i c Gone-Cylinder-Frustum-Cylinder Study: T e s t i n g
has been completed on a s e r i e s of cone-cylinder-frustum-cylinder bodies
f o r a p a r a m e t r i c s t u d y t o d e f i n e l o c a l normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s over frustum and c y l i n d e r s . The c o n t r a c t o r , MSG, bas completed
about 90 p e r c e n t o f t h e d a t a r e d u c t i o n , which i n v o l v e s i n p u t t i n g p r e s s u r e
d a t a i n t o a computer program and i n t e g r a t i n g t o determine t h e l o c a l
normal d i s t r i b u t i o n s
.
B.
ElectromechanicaE Branch
1.
Force Measurement Development
Dynamic damping f o r c e measurements w i t h t h e p r o t o t y p e f o r c e d
o s c i l l a t i o n model have been r u n i n t h e 14-inch kna2eL. Performance has
been q u i t e s a t i s f a c t o r y w i t h approximately 260 d a t a p s i g t s taken.
Improvements needed are b e t t e r t o r q u e spreng clanping far t h e h i g h e r
f r e q l ~ e n c i e sand more a l p h a o f f s e t capabfL%t:s for t h e Iswer frequency
spring.
Future models w i l l improve t k s e arid a l l o w f ~ vra r i a b l e c e n t e r
of rotation.
The second p r o t o t y p e o f t h e i.mpuhse f o r c e b a l a n c e f o r t h e
hypersonic shock t u n n e l , which has been through p r e l i m i n a r y c a l i b r a t i o n ,
appears t o meet a l l r e q u i r e m e n t s , This b a l a n c e , i.199, w i l l be used w i t h
t h e f i r s t S a t u r n c o n f i g u r a t i o n i n t h e t u n n e l i n mid-January.
A second
b a l a n c e , i.203 (1.00 inch d i a m e t e r ) , now being f a b r i c a t e d i s scheduled
f o r t h e same model of reduced s i z e i n mid-February,
A micro-force balance d e s i g n f o r t h e low d e n s i t y chamber
flow n o z z l e i s proceeding f o r measuring t h e s e l o a d s i n micro-pounds,
2.
P r e s s u r e Measurement Development
A r e s o n a n t tube c a l i b r a t o r f o r a c o u s t i c p r e s s u r e s i s b e i n g
developed. D r i v e r s have been chosen and coupling horns f o r t h e t u b e
have been made.
Frequencies a t a nominal 170db have been g e n e r a t e d t o
approximately 40K Hertz.
Acoustic p r e s s u r e t r a n s d u c e r s s u i t a b l e For t h e v a r i e t y o f
a p p l i c a t i . o n s in modeling a r e being developed. Adequake t r a n s d u c i n g
t e c h n i q u e s a r e a v a i l a b l e f o r t h e sound p r e s s u r e Levels of . 0 0 l t o 2.00
p s i (110 t o 175db) nominally and f r e q u e n c i e s t o l O O K Hertz. Problems
being r e s o l v e d a r e t h o s e of s i z e ; i . e . , s p a c i n g i s l i m i t e d i n small
models and allows wave-length c a n c e l l a t i o n s a t h i g h e r v e l o c i t i e s .
T a i l o r e d o r i f i c i n g o f .030 inches t o .200-inch diameter diaphragm
t r a n s d u c e r s i s allowing up t o 23K Hertz f l a t response. With helium
f i l l , 45K H e r t z f l a t response i s expected. Manufacturing t e c h n i q u e s
and u n r e l i a b i l i t y i n use have a s y e t made d i r e c t m i n i a t u r e (.015 t o
.030 i n c h d i a m e t e r ) p i e z o e l e c t r i c c r y s t a l a p p l i c a t i o n s i m p r a c t i c a l ,
A s m a l l s c a l e t e s t i s underway a t Lewis Research Center u s i n g t h e
t a i l o r e d o r i f i c e technique.
�3.
Thermal Measurement Development
The t h i n - f i l m b e a t gages used i n t h e v a r i o u s f a c i l i t i e s
a r e being improved i n q u a l i t y , i n t h e number o f t y p e s b e i a g made, and
i n developing s o u r c e s of supply. High temperature u n i t s o p e r a t i n g t o
1 0 0 0 ° ~a r e i n t h e p r o t o t y p e s t a g e .
4.
Dynamic Data A c q u i s i t i s x ~acd Air-aBysis
The 50K Hertz d a t a r e c o r d e r w i t h c r o s s - c o r r e l a t i o n
c a p a b i l i t i e s has been shipped t o HITRH f o r t e s t s u p p o r t . The system
w i l l be r e t u r n e d w i t h t h e cross-beam c o r r e l a t i o n t o t h e Thermal and
Acoustic Simulation F a c i l i t y (TASF) h e r e e a r l y n e x t y e a r .
Two analog c o r r e l a t o r s , which a r e t o be d e l i v e r e d soon,
w i l l be used f a r d a t a in all frequency ranges; t h e lower f r e q u e n c i e s
(below 50K H e r t z ) w i l l be analyzed a t I g c r e a s e d t a p e speeds.
5.
Flow V i s u a l i z a t i o n Development
The s i x - i n c h s c h l i e r e n and c l o s e d c i r c u i t TV systems f o r
t h e Thermal and Acoustic Simulation F a c i l i t y a r e t o be d e l i v e r e d about
December 15. The h i g h a c o u s t i c n o i s e w i l l i n most c a s e s p r o h i b i t d i r e c t
viewing o f t h e s c h l i e r e n , A l i g h t - w e i g h t overhead c a r r i a g e i s being
provided f o r t h e systems f o r l o n g i t u d i n a l and v e r t i c a l adjustment and
t r a n s f e r between v a r i o u s flow d u c t s .
Work i s c o n t i n u i n g on v a r i o u s flow v i s u a l i z a t i o n schemes i n
t h e low d e n s i t y chamber. R a d i a t i o n s t i m u l a t i o n and gas r a d i a t i o n
The d e n s i t i e s normally e l c o u n t e r e d a r e w e l l
t e c h n i q u e s a r e being used.
below t h e r a n g e o f t h e more conventional system.
6.
Gas Analysis Developments
A r e s i d u a l gas a n a l y z e r , which has been designed f o r t h e
low d e n s i t y chamber, w i l l analyze the gas composition i n t h e chamber
a t v a r i o u s in-flow c o n d i t i o n s and be a d a p t a b l e t o a wide range of
chamber p r e s s u r e s ,
A t e c h n i q u e has been developed f o r t h e helium a n a l y z e r t o
be used t o measure t h e helium-air r a t i o i n t h e j e t mixing zone i n t h e
Thermal and Acoustic Simulation F a c i l i t y .
7.
Remo t e Sensing Developments
Remote s e n s i n g of d e n s i t y and v e l o c i t y has been pursued
w i t h electron-beam s c a t t e r i n - g and s t i m u l a t e d u l t r a v i o l e t r a d i a t i o n .
Laser equipment has been purchased f o r s i m i l a r experiments under
various division contracts.
�8.
Model and Component Development
An a u t o m a t i c boundary l a y e r t r a v e r s e probe f o r t h e 14-inch
t u n n e l has been completed and checked o u t . This probe, which i s s t i n g mounted, has a t r a v e l of 1.500 i n c h e s a c c u r a t e t o .OOP inch. Automatic
programmed p o s i t i o n i s provided.
The m i n i a t u r e probe can c a r r y t o t a l
t e m p e r a t u r e , p r e s s u r e o r o t h e r types of s e n s o r s .
The d e s i g n of a n image model f o r c e system f o r t h e 14-inch
t u n n e l i s about 50 p e r c e n t complete. This w i l l be a s i d e - w a l l supported
model s i m i l a r t o a s p l i t t e r p l a t e concept except t h a t a f i x e d image of
t h e h a l f model w i l l r e p l a c e t h e s p l i t t e r p l a t e , A s p l i t t e r p l a t e w i l l
be provided a l s o f o r comparative t e s t i n g .
The f o r c e d o s c i l l a t i o n model system used w i t h t h e p r o t o t y p e
dynamic damping model w i l l be improved f o r more f l e x i b l e appl%eati.on
t o t h i s type of work and t o d r i v e a p r e s s u r e - i n s t r u m e n t e d model, This
work, which i s w e l l underway, w i l l i n c l u d e i m p r o ~ e r n e ~ tisn d i c a t e d by t h e
p r e s e n t t e s t o f t h e damping model.
A s i d e - w a l l f o r c e system f o r t h e 14-inch t u n n e l has been
It i s equipped w i t h au.tomatic programmed
completed and checked o u t .
a l p h a c o n t r o l . F i r s t use i s t o be f o r a s e r i e s of f i n load s t u d i e s .
Two b a l a n c e ranges a r e provided w i t h 5 f o r c e o r moment components
measured.
A VKF base flow t e s t c e l l , which w i l l i n c l u d e i n a d d i t i o n
t o t h e c e l l a v e h i c l e base model and 3 - d i r e c t i o n instrument probe
m a n i p u l a t o r , i s being designed and w i l l be adapted t o t h e AEDC f a c i l i t y
f o r v a r i o u s flow s t u d i e s .
Design i s e s s e n t i a l l y complete on a l l TASP mechanical
components i n c l u d i n g t h e c o l d d u c t and c o n t r o l s , models, i n s t r u m e n t a t i o n
c a r t s and survey probes.
The f a b r i c a t i o n and checkout w i l l c o n t i n u e
through December and January.
Other major model systems underway a r e a s follows:
SBPP Nozzle P a r a m e t r i c Models ( E a r l y Design)
P i l o t Hi-Re Force Model and M o d i f i c a t i o n s ( E a r l y Design)
Sat. V Open I n t e r s t a g e Force Model ( F i n a l Design)
S a t . V I n t e r s t a g e Ring Force Model ( F i n a l Design)
Sat. IB 14-Inch Tank Loads Model ( F i n a l F a b r i c a t i o n )
Low Density Chamber Flow Nozzle ( F i n a l F a b r i c a t i o n )
Wavy-Wall Models ( F i n a l F a b r i c a t i o n )
Lunar Erosion Model ( D e l i v e r e d )
Sat. V Forebody Force Model f o r HST (Design)
Q-Ball P r e s s u r e Models f o r 14-Inch Tunnel ( D e l i v e r e d )
�9.
F a b r i c a t i o n Resources
The work of t h e AEC shops a t Oak Ridge was r e c e n t l y i n s p e c t e d .
The low d e n s i t y flow n o z z l e s f d i f f i c u l t - t o - m a c h i n e s o f t copper was i n
e x c e l l e n t c o n d i t i o n . Thin-film gage f a b r i c a t i o n was beginning t o flow
v e r y r e l i a b l y and looked good. P o s s i b i l i t i e s of e l e c t r i c a l f a b r i c a t i o n
from c o a r s e l a y o u t s appeared t o be v e r y promising.
Astro Space i s f a b r i c a t i n g f o r c e b a l a n c e s , t h i n f i l m gages,
and o t h e r s p e c i a l items v e r y s a t i s f a c t o r i l y . Hayes I n t e r n a t i o n a l w i l l
f a b r i c a t e most of t h e TASP Cold Flow Duct and o t h e r components.
Micro G r a f t w i l l f a b r i c a t e t h e Lqage Model Force System f o r
t h e 14-inch t u n n e l as s c o n a s t h e d e s i g c i s complete. The wavy-wall
f a b r i c a t i o n s on 5 w a l l s , d o l e by Republic A v i a t i o n , were unacceptable.
These a r e beiqg r e - d o x in-house.
These f a b r i e a t i c n s e r v i c e s a r e provided
through ME Lab and a r e q u i t e s a t i s f a c t o r y w i t h t h e e x c e p t i o n of t h e
Republic work,
A t e c h n i c i a n has been provided a t JPL f o r 4 weeks t o check
Two t e c h n i c i a n s a r e a t Lewis Research
o u t a n LN-cooled f o r c e model.
Center on base a c o u s t i c and n o z z l e hinge moment t e s t .
C.
F a c i l i t i e s Branch
1.
Hmpulse Base Plow F a c i l i t y
The High Reynolds Number F a c i l i t y model s t u d i e s were
continued. A l l planned t e s t s have been conducted u s i n g t h e upstream
diaphragm p o s i t i o n . However, problems w i t h t h e downstream diaphragm
p o s i t i o n have been encountered w i t h both t h e t r a n s o n i c and s u p e r s o n i c
t e s t s e c t i o n s . C s n p l e t i o n of t h e downstream diaphragm t e s t s i s pending
a d d i t i o n a l hardware f a b r ic a t ion.
During f a b r i c a t i o n of t h i s hardware, t h e HBFF i s scheduled
f o r about one month w i t h a n R-AERO-AT p r o j e c t , "Heat T r a n s f e r and P r e s s u r e
Measurements i n a Cavity Formed by a Rocket Engine Exhaust." This s t u d y
i s t o compare experimental d a t a t o t h e o r e t i c a l p r e d i c t i o n a s a p p l i e d t o
an eroded c a v i t y of t h e l u n a r s u r f a c e . Hardware f o r t h i s t e s t was
r e c e i v e d November 24, and i n s t a l l a t i o n began November 29, 1965.
2.
Hypersonic Shock Tunnel
S e v e r a l r u g s were made i n t h e hypersonic shock t u n n e l t o
check r e p e a t a b i l i t y u s i n g b e t t e r q u a l i t y h e a t t r a n s f e r i n s t r u m e n t a t i o n .
Although r e s u l t s a r e much improved over previous d a t a , some problems
i n th.is a r e a remain unsolved.
�After several visits by the manufacturer's representatives,
the helium purification system seems to be mechanically satisfactory;
however, from all available means of analyzing the gas, it does not seem
to be removing air from the helium-air mixture. The manufacturer and
Purchasing Office have been informed of all our testing results; however,
their course of action to remedy the problem has not yet been determined.
Several modifications are underway to automate the operation
of the 20mm shock tube facility to be ready to start testing as requirements of R-AERO-AE are made available.
Hardware requirements for a static stability test on the
Saturn IB-V upper stages have been given t o R-MRB-LIE.
It la expected
that initial testing will begin about January 15, 1966.
3.
14 X 14-Inch T r f s o n i c Wind Tw~neB
The following tests were conducted during November:
a. An investigation to determine static stability a2d
axial force data sf several S a t u r n IB configurations using scalloped
and cylindrical tanks in the S-IB stage. Total runs: 7 2 .
b. An investigation of the pressure distribution on a
cone-frustum-cylinder general payload configuratiin at high angles of
attack. Total runs: 49.
c. An investigation to obtain rigid body upper stage
aerodynamic damping characteristics of the Apolls-Saturn HB and V
vehicles. This test is in progress.
4. 7 X 7-Inch Bisonic Wind Tunnel
An investigation to evaluate a technique for measuring
gas velocities through the use of a small gas laser was resumed. This
test is being performed by Brown Engineering for R-AERB-AT.
The i,nvestigationof separated flow and oscillating shocks
associated with a series of semi-circular section cylinder-flare-cylinder
models was completed. This work is being done by Wyle Laboratories
for R-AERO-AU.
5.
Thermal and Acoustic Simulation Pacili.ty
The contractor has delayed delivery sf the helium heater
until mid-February. Although this slippage will delay the system
checkout test program, it appears that the heater will be available
when the support equipment and model hardware becomes available.
�6.
Hot Plow T e s t F a c i l i t y
The a i r c o n t r o l v a l v e i s being modified t o i n c r e a s e t h e
r e s p o n s e time.
A l i m i t e d weight flow c a l i b r a t i o n was conducted on t h e
h e a t e r s o t h a t maximum weight flow through t h e h e a t e r could be
e s t a b l i s h e d f o r c e r t a i n d e s i g n c r i t e r i a f o r R-AERO-AT.
D.
F l u i d Mechanics Research O f f i c e
1. AL~aPysisof Density M e a s u r h g Systems: Analytical. s t u d i e s
s f impact p r e s s u r e p r s b e s by Monte Carlo techniques a g r e e completely
w i t h t h e p u b l i s h e d r e s u l t s o f t h e U n i v e r s i t y of Toronto I n s t i t u t e of
Aerospace S t u d i e s . To v e r i f y t h e s e s t u d i e s f o r complex probe d e s i g n s
which cannot be analyzed by t h e U n i v e r s i t y s f Toronto t e c h n i q u e s , f l i g h t
c o n f i g u r a t i o n s and fXigbt d a t a f o r d e 2 s i t y probes used on Explorer 17
and from GSFC thermosphere F l i g h t s a r e being examined.
2. O r b i t a l Aerodynamic C o e f f i c i e n t s , AAP: P r e l i m i n a r y d a t a
f o r o r b i t a l d r a g c o e f f i c i e n t s , c e n t e r o f p r e s s u r e l o c a t i o n , and o t h e r
o r b i t a l aerodynamic c h a r a c t e r i s t i c s f o r s e v e r a l concepts of a 1/10
g r a v i t y space s t a t i o n conf i g u r a t i o n have been d e r i v e d . V a r i a b l e
parameters included v a r i o u s r o t a t i o n a l modes w i t h r e s p e c t t o t h e v e l o c i t y
v e c t o r . These c a l c u l a t i o n s , which were made by Eockheed under NASA
C o n t r a c t NAS8-21230, p o i n t e d o u t s e v e r a l problems i n t h e Lockheed
programs.
P r i n c i p a l l y , t h e s e problems a r e concerned w i t h t h e c o u p l i n g
of many m u l t i s i z e d elements. Since f u r t h e r s t u d i e s w i l l most l i k e l y
r e q u i r e more d a t a of thi.s t y p e , t h e computer programs a r e being expanded
t o handle t h e more complicated b o d i e s .
3 . D i g i t a l a n a l y s i s of random processes:
R-AERO-AM and
R-COMP-RRV a r e developing j o i n t l y a computer program f o r a d i g i t a l
a o a l y s i s of random v a r i a b l e s which ( a ) can use an u n l i m i t e d amount
o f d a t a , ( b ) g i v e s s t a t i s t i c a l and numerical e r r o r s of a l l d e s i r e d
p r o p e r t i e s and ( c ) reduces computation and p r i n t - o u t times. The
u s u a l s t o r a g e l i m i t a t i o n s a r e avoided by a c c e p t i n g t h e d a t a i n small
p i e c e s . Comparing t h e e s t i m a t e s from i n d i v i d u a l p i e c e s a l l o w s a
c a l c u l a t i o n of s t a t i s t i c a l and numerical e r r o r s . Cost s a v i n g , r e d u c t i o n
of sample l e n g t h , number of l a g s , number of f r e q u e n c i e s , e t c . , a r e t h e n
i n t r o d u c e d by checking t h e accumulated e r r o r s a g a i n s t p r e s c r i b e d e r r o r
The program i s w r i t t e n i n two p a r t s . The f i r s t covers c r o s s margins.
c o r r e l a t i o n e s t i m a t e s , and t h e f i r s t t e s t examples have been r u n
s u c c e s s f u l l y . The second covers cross-power s p e c t r a and w i l l be
submitted f o r coding. A p p l i c a t i o n s t o o p t i c a l measurement o f
t u r b u l e n t f P u c t u a t i o n s and a c o u s t i c model t e s t s a r e being prepared.
�4. Cold Flow Duct: A f a c i l i t y which p r o v i d e s high p r e s s u r e
a i r (up t o 3500 p s i ) e x h a u s t i n g through n o z z l e s i n t o t h e atmosphere i s
r e q u i r e d by R-AERO-AM t o s t u d y t u r b u l e n c e and n o i s e g e n e r a t i o n i n
s u p e r s o n i c e x h a u s t s . The r e c e n t l y developed o p t i c a l crossed-beam
S i n g l e and
c o r r e l a t o r w i l l be used f o r t h e t u r b u l e n c e measurements.
c l u s t e r e d n o z z l e s w i l l be a t t a c h e d t o a s e t t l i n g chamber i n which s c r e e n s
can be i n s t a l l e d a t d i f f e r e n t l o c a t i o n s t o v a r y t u r b u l e n c e i n t h e exhaust.
Aerodynamic d e s i g n i s complete, a d . mechanical d e s i g n and f a b r i c a t i o n
( t h r o u g h R-AERB-AE) a r e underway. The a p p a r a t u s wb%B be c a l l e d t h e
Cold Flow Duct and w i l l be housed in t h e TASP (Thermal and Acoustic
Simulation F a c i l i t y ) .
F i r s t t e s t s using the o p t i c a l c o r r e l a t o r a r e
scheduled f o r March 1966.
5.
Contracts
a. NAS8-11208:
The IIT Researc? I ~ s t l t u t ef s r m d l a t e d t h e
t h e o r y behind t h e "correlatieln gunsswhich c r a s s c o r r e l a t e s t h e s i g n a l s
from two microphones t h a t a r e adgusted t o t h e same l i n e of s i g h t ,
producing a "narrow f i e l d of viewrYd e t e c t o r . T h i s d e t e c t o r f i n d s t h e
s t r e n g t h , s c a l e s , and f r e q u e n c i e s o f dorninazt soead s o u r c e s i.2 engine
exhausts
.
b. NAS8-l'h.299 and In-House:
The paper "Hkeat T r a n s f e r
Below R e a t t a c h i n g Turbulent Flows1-as
been accepted f o r p r e s e n t a t i o n
a t t h e AIAA Aerothermochemistry o f Turbulent Flows Conference, Temperature,
h e a t t r a n s f e r and h o t w i r e measurements i n t h e r e c i r c u l a t i o n a r e a behind
a b l u n t t r a i l i n g edge show ( a ) a dominant h e a t flow r e s i s t a n c e i n t h e
newly d i s c o v e r e d base boundary l a y e r , (b) t u r b u l e n c e l e v e l s i n e x c e s s
of 100 p e r c e n t , and ( c ) l a r g e t u r b u l e n c e e f f e c t s on base h e a t i n g r a t e s .
E.
Thermal E n v i r o m e n t Branch
1.
Saturn I
The S a t u r n I thermal d a t a e v a l u a t i o n summary r e p o r t has
been completed and i s being published a s CCSD TM-AE-65-115.
A s t u d y was i n i t i a t e d t o determine t h e e f f e c t s of r a d i a t i o n
on t h e gas temperature d a t a r e c e i v e d from thermocouples flown on t h e
S a t u r n v e h i c l e s . R e s u l t s s f t h i s s t u d y should be o b t a i n e d i n December.
P r e p a r a t i o n s a r e being made t o e v a l u a t e t h e AS-201 f l i g h t
data.
2.
S a t u r n EB
The maximum aerodynamic h e a t i n g environment f o r t h e AS-207
v e h i c l e w i t h 205K t h r u s t engines has been determined. The magnitude of
t h e thermal environment w i l l be approximately 3 p e r c e n t g r e a t e r t h a n
�t h a t p r e v i o u s l y determined f o r t h e S a t u r n HB v e h i c l e (200K e n g i n e s ) .
Because of t h e s i m i l a r i t y between t h e 205K d e s i g n c r i t e r i a e n v i r o m e n t
w i t h t h e 200R d e s i g n c r i t e r i a environment, s e p a r a t e environmental d e s i g n
c r i t e r i a f o r t h e 205K s e r i e s of v e h i c l e s w i l l n o t be e s t a b l i s h e d . A
r e p o r t p r e s e n t i n g t h e above r e s u l t s w i l l be published in December.
A S a t u r n HB thermal environment handbook i s being developed.
Design c r i t e r i a f o r t h e b a s i c s t a g e s , f i n s and protuberances have been
compiled and e d i t e d . F r c v i s i o n has been made f o r i n c o r p o r a t i n g f u t u r e
o r replacement d a t a a s s o c i a t e d w i t h performance and/or t r a j e c t o r y changes.
This manual w i l l be published i n mid-December.
The i n c r e a s e d aerodynamic h e a t i n g e n v i r o m e n t induced by t h e
S a t u r n PB p r o t u b e r a n c e s f o r v a r i o u s d e s i g n t r a j e e t o r i e s i s being determined.
These d a t a w i l l be included f z ~t h e S a t u r n 13 t h e r m a l e w f r s m e n t a l handbook.
The a e r o d y ~ a m i ch e a t i n g r e l a t l o - s h i p s a r e being formulated
i n t o a g e n e r a l aerodynamic h e a t i n g s u b r o u t i n e , which w i l l be used i n an
advanced thermal a r a l y z e r computer prcgram.
The s e p a r a t e d f l o w s t u d y i s being csntimued. Empirical
r e l a t i o n s h i p s which a c c u r a t e l y p r e d i c t t h e s e p a r a t i o n geometry have
been o b t a i n e d .
An empirhea1 r e l a t i o n s h i p which can d e f i n e t h e l i m i t s
of t h e geometry of s e p a r a t i o n i s being formulated.
S e v e r a l methods
have been determined and a r e being examined. P u b l i c a t i o n of t h e s e
r e s u l t s w i l l be delayed t o allow a more i n t e n s i v e i n v e s t i g a t i o n of t h e s e
methods.
Thermal e n v i r o ~ m e n t sf o r t h e S-LIE s t a g e B-P engine components
d u r i n g f l i g h t have been p u b l i s h e d a s CCSD 7%-AE-65-288.
These environments
were based on SA-9 and SA-10 f l i g h t d a t a r e c e i v e d from c a l o r i m e t e r s
mounted on t h e engine b e l l and a s p i r a t o r s u r f a c e s .
The R-B engine
s u p p o r t band temperatures d u r i n g f l i g h t have been determined u s i n g t h e s e
environments.
In a d d i t i o n , a p p r o p r i a t e m o d i f i c a t i o n s were made t o p r e d i c t
t h e S-IB-3 s t a t i c t e s t engine s u p p o r t band temperatures.
Good c o r r e l a t i o n
w i t h t h e t e s t d a t a was o b t a i n e d .
The c a l o r i m e t e r c a l i b r a t i o n d a t a from Wyle Laboratory a r e
being analyzed. However, i t i s b e l i e v e d t h a t t h e d i g i t a l t a p e t h a t was
s e n t t o GCSD from t h e Wyle t e s t c o n t a i n s i n a c c u r a t e l y t r a n s c r i b e d d a t a .
Wyle L a b o r a t o r i e s i s checking t h i s p o s s i b i l i t y .
A f i n a l report of the
w
i
l
l
n
o
t
be
pubhished
u
n
t
i
l
a
l
l
d
a
t
a
have
been p r o p e r l y processed.
results
The s t e a d y s t a t e temperature d i s t r i b u t i o n a c r o s s t h e c y l i n d r i c a l
d i s c of a membrane c a l o r i m e t e r i s being determined. Varied temperature
d i s t r i b u t i o n s have been o b t a i n e d by imposing s e v e r a l c o n v e c t i v e and
r a d i a t i v e environments.
It i s e s s e n t i a l t o f u t u r e S a t u r n EB f l i g h t
e v a l u a t i o n t h a t t h e membrane c a l o r i m e t e r t e m p e r a t w e d i s t r i b u t i o n be
a c c u r a t e l y determii-ed, s i n c e a l l scheduled S a t u r n I& c a l o r i m e t e r
i n s t a l l a t i o n s a r e o f t h e membrane t y p e .
�T e s t i n g o f t h e S a t u r n S-IB and S - I , Block 11, c o n f i g u r a t i o n s
w a s t e r m i n a t e d a t AEDC o n November 4 , 1965. The e f f e c t s o f o n e i n o p e r a t i v e
e n g i n e and t h e removal o f t h e e n g i n e s h r o u d s were i n v e s t i g a t e d . A complete
examination o f t h e d a t a obtained during t h e t r a n s o n i c t e s t i n g phase has
i n d i c a t e d t h a t t h e e x p e c t e d Mach number and a l t i t u d e were n o t o b t a i n e d .
T r a n s i e n t e x t e r n a l f l o w d u r i n g combustion f n v a l l d a t e d t h e d a t a . The
Mach 1.6 d a t a a r e b e i n g a n a l y z e d and w i l l be documented.
A r e p o r t descri.b%ng t h e t h i n - f i l m r e s i s t a n c e thermometer
c a l i b r a t i o n t e s t s r u n a t My-CaP E n g i n e e r i n g w i l l be p u b l i s h e d a s CCSD
TN-AE-65-113.
Model b u i l d u p and model rnodificati.on s f the S-I, Block I1
i n t e r m e d i a t e d u r a t i o n t e s t model a t AEDC have heen completed. T e s t i n g
i s now underway a t Mach 1.63 2nd 3 8 , 0 8 0 f e e t a l t i t u d e .
T e s t s of t h e Satelrn S-9B short duratis_7i model En t h e
Cornell. A e r o n a u t i c a l L a b o r a t o r y (GAL) 8 x 8 t r a n s o n i c wi3d t e n n e l a r e
being prepared.
A rough e s t i m a t e of c e l l occupancy f a r t h i s t e s t i s
A p r i l 1, 1965.
An e m p i r i c a l c a n v e c t i v e b a s e h e a t i n g model and a g e n e r a l i z e d
computer program t o c a l c u l a t e approximate S a t u r n S-IB s t a g e c o n v e c t i v e
b a s e h e a t i n g v a l u e s a r e b e i n g developed.
The computer, b e i n g c o n s t r u c t e d
i n segments, i s o n s c h e d u l e . The p o r t i o n o f t h i s program which w i l l
c a l c u l a t e r e v e r s e d mass f l o w i s complete w i t h p r e l i m i n a r y r e s u l t s b e i n g
c a l c u l a t e d . A t e c h n i c a l b u l l e t i n w i l l be p u b l i s h e d .
A t e c h n i c a l n o t e concerned w i t h t h e M-1 e n g i n e r a d i a t i o n
f o r n o n e q u i l f b r i u m c o n d i t i o n s h a s been d r a f t e d , The computer program
p r e v i o u s l y b u i l t t o c a l c u l a t e a b s o r p t i o n and s c a t t e r i n g c r o s s s e c t i o n s
o f carbon p a r t i c l e s i s being a l t e r e d t o allow p a r t i c l e d i s t r i b u t i o n
i n p u t and t h e c a l c u l a t i o n s f plume r a d i a n c e , T h i s program w i l l t h e n
be used t o p r o v i d e i n p u t t o t h e s i n g l e plume r a d i a t i o n program b e i n g
d e v e l o p e d f o r t h e S-IB s t a g e .
T u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g i s b e i n g s t u d i e d .
R e s u l t s have been o b t a i n e d f o r t h e main j e t under chemical e q u i l i b r i u m
c h e m i s t r y c o n d i t i o n s u s i n g t h e c o n s t a n t p r e s s u r e a n a l y s i s . Also b e i n g
i n v e s t i g a t e d i s t u r b i n e e x h a u s t g a s mixing w i t h a i r under chemical
equilibrium conditions.
I n i t i a l r e s u l t s i n d i c a t e t h e presence s f a
l a r g e amount o f s o l i d c a r b o n . A r e p o r t d e s c r i b i n g t h e method and
r e s u l t s w i l l be i s s u e d .
3.
Saturn ~ ~ / ~ e n . t a u r
An a n a l y s i s t o d e t e r m i n e t h e maximum a e r o d y r a n i e h e a t i n g
environment a s s o c i a t e d w i t h t h e S a t u r n 1 ~ / 6 e n t a u s C i s l u n a r Pegasus
t r a j e c t o r y was t e r m i n a t e d , P r e l i m i c a r y r e s u l t s p r e v i o u s l y o b t a i n e d show
�t h a t t h e t o t a l aerodynamic h e a t i n g would be l e s s t h a n h a l f t h a t f o r t h e
AS-201 and AS-202 v e h i c l e s .
These r e s u k t s w i l l be p u b l i s h e d .
4.
Saturn V
Rocketdyne p l a n s t o f i r e twa S - I 1 u l l a g e motors a t t h e i r
McGregor, Texas, f a c i l i t y about t h e end of December o r e a r l y January.
The Thermal Envirorment Eranch p l a n s ts f z s t a l l a T e f l o 2 probe and a
copper probe i n t h e exhaust f a r t h e f i r s t and second f i r i n g s , r e s p e c t i v e l y .
These p r o b e s , which a r e being f a b r i c a t e d by Beat Technology Laboratory,
w i l l be composed o f a 3-inch diameter c y l i n d e r w i t h a h e m i s p h e r i c a l nose
cap and w i l l be m o ~ n t e dabout 2% f e e t from t h e e x i t p l a n e ( j u s t i n f r o n t
of t h e f i r s t Mach d i s c ) . $be Teflon probe w i l l have about 4 o r 5 a b l a t i o n
s e n s o r s t o be used in a? a t t e m p t t o measure a b l a t i o n arid p a r t i c l e e r o s i o n
caused by t h e exhaust %rnpiv.gemenk. The coFper probe w i l l have thermocouples
i n s t a l l e d a t v s ~ i o u sd e p t h s %2 a copper slug i n e-- a t t e m p t t o measure t h e
h e a t t r a ~ s f e rr a t e a t the s u r f a c e ~ P Zt h e temperature d i s t r i b u t i o n through
t h e s l u g . These experimental dara will be cempared w i t h t h e c r e t i c a f
h e a t i n g and n b l a t f o i , calc.~llakfel?s.
a.
A b l a t i o n Program
TFe e q u s t i o n s a r e being formulated and a d i g i t a l computer
program w r i t t e n f o r a n a l y z i n g a b l a t i n g thermal p r o t e c t i o n systems. The
program i s being developed i n two phases:
Phase H w i l l produce a
"working t o o l " program t o handle m a t e r i a l s f o r which experimental d a t a
a r e a v a i l a b l e ; Phase Il w i l l produce a program having d i v e r s i f i e d
theoretical capabilfties
.
The "-\n70rking tooB'"roogram
bas now reached p r o d u c t i o n
s t a t u s , and t h e u s e r ' s Manual has been p ~ b l i s h e da s LYSC/BREC document
A712574. An o r a l p r e s e n t a t i o n on t h e program's c a p a b i l i t i e s a ~ n d i t s
u s e w i l l b e g i v e n t~ t h e customer ir t h e near f u t u r e .
Work has resumed on Phase 11 o f t h e p r c g r a m , which w i l l
i n v o l v e a n a l y s e s of decomposi.tfon-in-depth and s o l i d p a r t i c l e impingement
from r o c k e t e x h a u s t s .
The "worki.ng t o o l ? program i s being used t o a n a l y z e
s e v e r a l a b l a t i v e models t o be t e s t e d i n t h e S-I'\% u l l a g e motor e x h a u s t s
f o r R-AERB-AT
.
be
Thermo Methods Ar?..alysis
- Plat-Plate
Modification
Two b a s i c v e r s i o n s of t h e f l a t - p l a t e t r a n s f o r m a t i o n s
have been d e r i v e d and t e s t e d . The mast r e c e n t has been found t o g i v e
erroneous r e s u l t s i n a r e g i o n o f n e g a t i v e v e l o c i t y d i s t r i b u t i o n . The
�former v e r s i o n , now being t e s t e d msr'e e x t e n s i v e l y , has been found t o be
q u i t e s i m i l a r t o an approximate s o l u t i o n f o r t h e momentum t h i c k n e s s
o b t a i n e d by E. Truckewbrodt from a l e n g t h y d e r i v a t i o n based on t h e
energy i n t e g r a l e q u a t i o n .
Such c l o s e s i m i l a r i t y w i t h t h e more l e n g t h y s o l u t i o n
l e n d s s u p p o r t t o t h e t r a n s f o r m s o k u t i o n based on a simple f l a t - p l a t e
momentum t h i c k n e s s s o l u t i o n .
c.
Equilibrium Weal ~ a s J ~ o r r n aShock
1
Program f o r S t a g n a t i o n
P o i n t Heating
The g o a l of t h i s s t u d y i s to develop t h e c a p a b i l i t y t o
c a l c u l a t e s t a g n a t i o n p o i n t h e a t i n g r a t e s for a b l u n t body in an e q u i l i b rium r e a l gas flow f i e l d . Tvo numerical techniques were used t o s o l v e
t h e laminar bot~ndary l a y e r e q u a t i o ~ s8 3 t h e s t s g - ? a t i o n r e g t o n s s f t h e
b l u n t body.
D i g i t a l colnputer programs were w r i t t e r for b o t h t e c h n i q u e s ,
and t h e r e s u l t i n g programs were cheeked c u t . Tbe behavior o f t h e numerical
s o k u t i o n s was e x p l o r e d , and t h e r e s d l t s for h e a t i n g r a t e s i n air compared
f a v o r a b l y w i t h r e s u l t s publistsed by o t h p r s .
A computer program, generated by Lewis Research C e n t e r ,
f o r p r e d i c t i o n o f t r a n s p o r t p r o p e r t i e s of multicompsnent r e a c t i n g g a s e s
was checked o u t , and a number of t e s t c a s e s were examined.
do
Thermal Analysis of t h e LPV P a r t i a l l y Enclosed Engine
Cluster
The c l u s t e r e d LFV engines a r e being s t u d i e d . The r a d i a n t
h e a t i n t e r c h a n g e c o n f i g u r a t i o n f a c t o r s have been c a l c u l a t e d f o r b o t h t h e
c l u s t e r e d and i n - l i n e engine c o n f i g u r a t i o n s . Meat t r a n s f e r c o e f f i c i e n t s
a t t h e n o z z l e w a l l s a r e being c a l c u l a t e d based on engine t e s t d a t a .
Using t h e above d a t a , t h e s t e a d y s t a t e temperature d i s t r i b u t i o n s f t h e
c l u s t e r e d engine c o o f i g u r a t i o n w i l l be determined.
e,
Base P r e s s u r e and Envfromewt
The p o r t i o n s f t h i s s t u d y now u?der i ~ v e s t i g a t i o n
i n v o l v e s t h e t u r b u l e n t boundary l a y e r growth on aszzke w a l l s w i t h
mass i n j e c t i o n c o o l i n g .
The accumulation of d a t a on t h e P-1 engine has reached
a p o i n t where r e a s o n a b l y a c c u r a t e i n p u t s t o t h e boundary l a y e r program
can be made. These d a t a have been documented i n a Technical Data Release.
A m u l t i p l e - s l o t mass i n j e c t i o n scheme has been i n c o r p o r a t e d
i n t o t h e boundary l a y e r program; one r u n has been made f o r boundary l a y e r
growth over t h e e n t i r e P-B nozzle.
In a d d i t i o n , s u f f i c i e n t approximate
�d a t a were c o l l e c t e d t o allow one r u n f o r t h e boundary l a y e r growth on
t h e H-l n o z z l e . As y e t , almost no experimental i n f o m a t i o n a n t h i s
engine has been l o c a t e d .
Additional runs with the multiple-slot i n j e c t i o n
boundary l a y e r program w i l l be made t o v e r i f y i t s o p e r a t i o n . A s u b r o u t i n e
t o i n c o r p o r a t e a d i s t r i b u t e d mass i n j e c t i o n technique i n s t e a d of t h e
m u l t i p l e - s l o t scheme i s being w r i t t e n . Technical Data Releases s i m i l a r
t o t h e one r e f e r e n c e d abave w i l l be prepared f o r t h e H - l and 5 - 2 engines.
f
.
Stage S e p a r a t i o n Thermodyn,amics
A method of p r e d i c t e d r o c k e t nozzle exhaust impingement
p r e s s u r e s on a f l a t p l a t e has been developed by making use of a methodo f - c h a r a c t e r i s t i c s computer program which i n v a l v e s ~ c k e z t ' st u r b u l e n t
f l a t p l a t e t h e o r y and a computer program wbEch s o l v e s t h e turbulenmt
momentum i n t e g r a l e q u a t i o n by av. i t e r a t i v e method a ~ dt h e n p r e d i c t s
h e a t r a t e s u s i n g ~ e ~ n o l d a' s~ a l o g y .
Other s m a l l t a s k s i n p r o g r e s s or r e c e n t l y completed
a r e as fallows:
(1) P r e d i c t i o n s f plume p r o p e r t i e s and shape a t 350,000
f e e t a l t i t u d e f o r shock impingement l o c a t i o n a s s o c i a t e d w i t h experimental
t e s t s a t Cornell.
( 2 ) Obtaining s e v e r a l s e t s of thermo-chemical d a t a
a s s o c i a t e d w i t h v a r i o u s p r o p e l l a n t s used i.n c u r r e n t probl.ems.
( 3 ) P r e d i c t i o n s f r e a l gas flow f i e l d and b e a t t r a n s f e r
a s s o c i a t e d w i t h h o t flow r o c k e t exhaust impingeme~t t e s t s scheduled a t
NASA-MSPC (Centeur r e t r o - m o t o r s ) .
g.
h?cnzzke a,nd J o t Wake Study
The program has once a g a i n been debugged and i s o p e r a t i n g
properly.
The SC-4028 p l o t program i s now o p e r a t i o n a l . The e f f e c t i v e n e s s
of t h i s t y p e s f o u t p u t i s r e s t r i c t e d by t h e graph s i z e which i s i n h e r e n t
t o t h e SC-4020 p l o t t e r . Ameans of photo-enlarging t h e pl.ots has been
attempted and was s u c c e s s f u l . A new photographic enlargement p l a t e i s
on o r d e r and should a r r i v e in a few weeks.
It w i l l t h e n be p o s s i b l e t o
e n l a r g e t o ll" x l8".
h.
M u l t i p l o Shock
A new t e c h r i q u e , being proposed t o i n v e s t i g a t e t h e r e g u l a r
shock r e f l e c t i o n from t h e a x i s of symmetry, i s used t o determine t h e
r e f l e c t e d shock wave near t h e a x i s of symmetry by making use of t h e
e x i s t i n g s i n g l e shock flow f i e l d program t o g e t h e r w i t h an o v e r a l l
�c o n s e r v a t i o n balance technique.
P r e l i m i n a r y r e s u l t s from t h e f i r s t few
t r i a l s seem t o i n d i c a t e t h a t such a technique might l e a d us t o completely
s o l v e t h e axisymmetric flow f i e l d under r e g u l a r r e f l e c t i o n c o n d i t i o n s .
i.
Thermodynamics and Chemistry of Reacting Gases
E r r o r s were found i n t h e f i n i t e r a t e chemistry program
o b t a i n e d from ~ A % ~ / ~ e w iAs replacement
.
espy o f t h e chemistry program
was shipped from N A S A I L ~ Wt o~ ~#RE@ ow Xovember 1 2 , 1965. This program
w i l l be made o p e r a t i o n a l on HSPC" computers when i t i s r e c e i v e d .
The N A S A / L ~thermodynamic
~ ~ ~
d a t a (i.nclsadFng i o n i c
s p e c i e s ) have been r e c e i v e d .
A f t e r t h e s e d a t a have been v e r i f i e d , t h e y
thermochemieal
equilibri.um program.
w i l l be used by t h e ~ A s ~ / ~ e w
is
9.
Cold Plow-Sase Flow Test
Planning for t h e c o l d flow t e s t i s c o n t i n u i n g . The
t e s t i s t e n t a t i v e l y scheduled t o begin a t AEDC i n March 1966 in t h e
Tunnel E a r e a of t h e vsn Karman Gas Dyiiamies F a c i l i t y (WP). Design
and f a b r i c a t i o n of t h e model d i f f u s e r and t h e enc8asiEg s t r u c t u r e a r e
being c o o r d i n a t e d by R-AERO-AEM.
k.
Perform Research i n t o t h e Problem of I n t e r a c t i o n of
Axisymmetric J e t s
The purpose of t h i s p r o j e c t i s t o develop a computer
program t~ p r e d i c t t u r b u l e n t mixing and combusticn c h a r a c t e r i s t i c s of
a r o c k e t exhaust plume w i t h t u r b i n e g a s e s e x h a u s t i n g p e r i p h e r a l l y about
t h e n o z z l e e x i t and w i t h an e x t e r n a l gas stream surrounding t h e plume.
This p r o j e c t was i n i t i a t e d d u r i n g t h e preceding c o n t r a c t y e a r . The
mathematical procedure has e s s e n t i a l l y been developed and i s being
o u t l i n e d i n a t e c h n i c a l r e p o r t . The computer program which w i l l use
t h i s mathematical procedure, however, i s n o t y e t complete.
1.
T h e o r e t i c a l Techniques f o r P r e d i c t i n g Sase Plow Environment
i n t h e V i c i n i t y of t h e Bluff Base of ar- AxFsynmetric Body
The purpose of t h i s p r o j e c t i s t o develop a computer
program t o c a l c u l a t e base flow p r o p e r t i e s f o r an axisymmetric body w i t h
a b l u f f base. Thus f a r , t h e work has c o n s i s t e d p r i m a r i l y of a s t u d y o f
l i t e r a t u r e d e s c r i b i n g c u r r e n t techniques f o r d e a l i n g w i t h problems of
t h i s n a t u r e . The method of Zumwalt (Zumwabt, 6 . W., "AnahyticaH and
Experimental Study of t h e Axially-Symmetric Supersonic Base P r e s s u r e
Problem," U n i v e r s i t y o f I l l i . n o i s , PI3.D. T h e s i s , 1959. ) lases an a x i s p e t r i c
model w i t h a "sting.'-his
mathematical model begins to break down a s
t h e sting-to-base-diameter r a t i o approaches zero. T h e r e f o r e , a l i m i t i n g
I1
s t i n g " diameter i s found below which t h e model i s no longer a p p l i c a b l e
and t h e c a l c u l a t e d p r e s s u r e reaches a maximum v a l u e . An i n v e s t t g a t i o n
i s being made of t h e p o s s i b i l i t y of r e p l a c i n g t h e s t i n g by a v i s c o u s
c o r e o r neck,
�m.
Gray-Body C a l i b r a t i o n F a c i l i t y
This i s a c a n t i ~ u a t i s nof e f f o r t i n i t i a t e d d u r i n g t h e
p r e c e d i n g c o n t r a c t y e a r . The d e s i g n and f a b r i c a t i o n o f t h e Gray-Body
C a l i b r a t i o n F a c i l i t y a r e s t i l l u ~ d e r w a y . The d e t a i l e d d e s i g n f o r t h e
h e a t s o u r c e module i s 96 p e r c e n t completed. The c o o l i n g and vacuum
r e q u i r e m e n t s have been determined, and a l l components have been s e l e c t e d .
n.
Plow F i e l d VisuaPEzatFon
kangley Research Center was v i s i t e d t o c o n f e r w i t h
Langley personnel c s n c e r n i l g t h e i r work i n t h e a r e a of flow f i e l d
v i s u a l i z a t i o n . Primary i n t e r e s t was i n flow f i e l d measurement t e c h n i q u e s
a p p l i c a b l e t o t h e base flow model t e s t s t o be conducted e a r l y n e x t y e a r
by R-AERB-AT,
A c o n f e r e ~ c ewas h e l d with p e r s o n n e l i n t h e Gas
T h e i r main
Measurements S e c t i o ? of t h e Instrument Research Division.
e f f o r t s a r e c u r r e n t l y d i r e c t e d toward developing e l e c t r o n beam and
s p a r k d i s c h a r g e d e v i c e s f o r measurfrig d e n s i t y , ~ 7 e l o e % t y and
,
temperature
They a r e l i m i t e d ts I c w defisity flows.
i n a hypersonic E l - w .
Meetings were a l s o h e l d w i t h people engaged i n measuring
s k i n t e m p e r a t u r e , and a b l a t i o n and aerodynamic h e a t i n g on l i f t i n g r e e n t r y
bodies.
Also d i s c u s s e d was systems a n a l y s i s s f hypersonic c r u i s e v e h i c l e s
t o determine t h e s t a t u s of work and t o e s t a b l i s h c o n t a c t s f o r f u t u r e use.
This i s i n s u p p o r t of o u r e f f o r t t o develop t h e c a p a b i l i t y t o a n a l y z e
problems expected i n f u t u r e b o o s t e r development.
F.
Unsteady Aerodynamics Branch
1.
J n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Erkviroment
P r e l i m i n a r y e s t i m a t e s of t h e S a t u r n V i n f l i g h t a c o u s t i c
environments, which cover a Mach range of .8 t o 2,2 f o r t h e v e h i c l e a t
zero a n g l e of a t t a c k a r e being p u b l i s h e d .
S t u d i e s of s e p a r a t e d flow on cone c y l i n d e r f l a r e bodies have
been completed i n t h e MSPC 7-inch t u n n e l . These t e s t s w i l l d e l i n e a t e t h e
e f f e c t s of Reynolds number, Mach number, and model geometry on s e p a r a t e d
flow.
Ease f h u c t u a t i n g p r e s s u r e s a r e being o b t a i n e d on t h e t e s t
There
" s a t u r n V GoEd FPOW Xozzle Aerodynamic Hinge Moment T e s t m3-64."
w i l l be e i g h t f l u c t u a t i n g p r e s s u r e measurements l o c a t e d i n one quadrant
of the base.
Reports by M r . K e l l y and M r . T h r a l l s f Measurement Analysis
It i s planned t o c o n t i n u e t h i s c o n t r a c t .
C o r p o r a t i o n a r e being reviewed.
�I n t h e meeting " ~ e v i e wof Panel F l u t t e r and Aerodynamic
Noise Problems on S a t u r n I B and V , l D on November 15, 1965, R-AERO-AU
made a p r o p o s a l t o o b t a i n f l u c t u a t i n g p r e s s u r e d a t a from a f u l l - s c a l e
f l i g h t experiment and a 6 p e r c e n t wind t u n n e l model t e s t .
2.
Launch S i t e Acoustic Environment
The p r e d i c t i o n program f o r t h e s p a t i a l c o r r e l a t i o n f u n c t i o n s
on t h e v e h i c l e s u r f a c e f o r b o t h t h e s t a t i c f i r i n g and launch engineg e n e r a t e d a c o u s t i . ~e n v i r o m e n . t has been completed. Attempts t o reduce
t h e computing time have n o t been s u c c e s s f u l . An a t t e m p t i s being made
t o s i m p l i f y t h e fundamental e q u a t i o n .
A technique f o r p r e d i c t i n g t h e sound p r e s s u r e l e v e l
r e c e i v e d a t a f a r - f i e l d I s c a t i o n from an a c o u s t i c , broadband, d i r e c t i o n a l ,
p o i n t s o u r c e r a d i a t i n g i n t o an inhomogeneous media bas been developed.
I n i t i a l r e s u l t s from t h i s program r e c e i v e d r e c e n t l y a r e being compared
t o measured v a l u e s . P r e d i c t e d and measured r e s u l t s a r e being compared
under a wide v a r i e t y o f c o n d i t i o n s t o e v a l u a t e t h e accuracy o f t h i s
technique.
3.
Acoustic Model Test F a c i l i t y
P l a n s a r e being made t o i n i t i a t e a n a c o u s t i c model t e s t a t
t h e Acoustic Model T e s t F a c i l i t y a t t h e T e s t Laboratory. P r e l i m i n a r y
"checkout" t e s t s a r e planned f o r January 1966.
A s s i s t a n c e i s being o b t a i n e d from R-AERO-Y t o d e f i n e t h e
m e t e o r o l o g i c a l c o n d i t i o n s which e x i s t a t t h e Acoustic Model T e s t F a c i l i t y .
This i n f o r m a t i o n w i l l be used t o determine t h e e f f e c t s o f m e t e o r o l o g i c a l
c o n d i t i o n s on t h e a c q u i r e d a c o u s t i c d a t a .
4.
Panel F l u t t e r Aerodynamics
A meeting was h e l d November 3 , 1965, w i t h M r . C l i n e ,
PGcVE-DIR, t o d i s c u s s t h e p o t e n t i a l paneb f l u t t e r hazard on t h e S-EVHP
s t a g e and t~ d i s c u s s t h e p o s s i b i l i t y of modifying f l i g h t v e h i c l e AS-201.
M r . C l i n e s t a t e d t h a t P&VE was prepared t o apply t h e v i s c o - e l a s t i c
m a t e r i a l t e s t e d i n t h e Langley f l u t t e r t e s t s , but s i n c e t h e t e s t r e s u l t s
showed few b e n e f i c i a l e f f e c t s , they decided n o t t o apply t h e m a t e r i a l .
Aero-Astrodynamics Laboratory concurs w i t h t h i s d e c i s i o n . A t t h i s time,
P&VE b e l i e v e s t h a t t h e f l u t t e r hazard i s n o t s e r i o u s enough t o m e r i t
s t r u c t u r a l m o d i f i c a t i o n on t h e unmanned v e h i c l e s . However, P&VE would
l i k e t o perform f l u t t e r t e s t s on a f u l l - s c a l e segment of t h e S-IWIW
s t a g e b e f o r e making any d e c i s i o n p e r t a i n i n g t o t h e manned v e h i c l e s .
On November 15, 1965, a p r e s e n t a t i o n was g i v e n t o M r . Weidner,
R-DIR, by R-AERO and R-PSsVE reviewing t h e panel f l u t t e r problem on t h e
S a t u r n I B and V v e h i c l e s .
P r e l i m i n a r y c o p i e s of t h e minutes of t h e meeting
have been forwarded t o D r . Rees, M r . Weidner, M r . G e l l e r , M r . C l i n e and
D r . Rudolph.
,
�A m e e t i n g was h e l d November 24, 1965 a t Ames Research
Center among r e p r e s e n t a t i v e s of ARC and MSPC t o d i s c u s s t h e f e a s i b i l i t y
of conducting f u l l - s c a l e p a n e l f l u t t e r t e s t s on t h e forward s k i r t of
t h e S - I I B s t a g e . The proposed f a c i l i t i e s a r e t h e Ames 9 x 7-foot
These t e s t s w i l l
s u p e r s o n i c and 11 x EB-foot t r a n s c n i c wind t w n e l s .
i n v e s t i g a t e t h e e f f e c t s o f d i f f e r e n t i a l p r e s s u r e and i n f l i g h t l o a d i n g
c o n d i t i o n s on t h e f l u t t e r c h a r a c t e r i s t i c s s f t h e s e p a n e l s and w i l l
d e f i n e t h e f l u t t e r boundaries under t h e s e c o n d i t i o n s . S t r u c t u r a l
f i x e s would a l s o be i n v e s t i g a t e d shswBd t h e t e s t r e s u l t s d i c t a t e t h e i r
need. Ames p e r s o a n e l s t a t e d that they could n o t support Marshall i n
t h e ' k x p l o r a t o r y " t e s t of t h i s r a t u r e because of t u ~ l 3 e ls c h e d u l i n g
problems and manpower s h o r t a g e . However, they would a l l o t M a r s h a l l
two weeks tuntrlel time t o conduct a "proof'Qest,
which would c o n s i s t
of s u b j e c t i n g t h e p a r e l s t o t h e most s e v e r e i n f l i g h t aerodynamic and
Sf f l u t t e r o c c u r s under t h e s e c o n d i t i o n s ,
s t r u c t u r a l l a a d i n g condTtfsn.s.
immediate emphasis would be placed on s t r u c t u r a l f i x e s . With t h i s t y p e
of t e s t , no f l u t t e r bouldary would be d e f i n e d .
W-AERB-AD f e e l s t h a t
more t h a n a ' " r o s f g g test program i n d i c a t e d by kmes w i l l be r e q u i r e d .
The most s e v e r e e o ~ d i t i c n scannot be e s t a b l i s h e d w i t h c e r t a i n t y w i t h o u t
some e x p l o r a t o r y e f f c r t . Furthermore, a c e r t a i ~p o r t i o n of t h e f l u t t e r
boundary n e a r t h e c r i t i c a l b u c k l i n g s t r e s s should be d e f f ~ e dt o determine
t h e minimum dynamic p r e s s u r e f o r f l u t t e r w i t h v a r i o u s d i f f e r e n t i a l
p r e s s u r e s , Mach numbers a d combinations of compressive and s h e a r l o a d i n g s .
It i s b e l i e v e d t h a t a minimum of f o u r weeks t u n n e l time w i l l be r e q u i r e d
t o o b t a i n t h e i n f o r m a t i o n n e c e s s a r y t o d e f i n e t h e f l u t t e r boundaries i n
more d e t a i l and allow an assessment of t h e f l u t t e r problem.
5.
Satur2 V Ground Winds (AU-5)
a . As a r e s u l t of a c t i o n item b in memorandum from I - D I R ,
" P r e s e n t a t i o n of S t r u c t u r a l . Load Design C r i t e r i a , " d a t e d October 20, 1965,
a meeting was h e l d o v October 29, 1965, among Messrs. A. G. Rainey,
W. H. Reed 111, C. W. J o n e s , and M. C. Farmer of kangley and M r . R. W.
W d k e r of MSFC t o d i s c u s s a d d i t i o ~ a lSaturD V ground winds t e s t s i n t h e
Langley 16-foot transonic dynamic t u n n e l . The primary o b j e c t i v e s of
such t e s t s were t o i 2 v e s t i g a t e , i n more d e t a i l , aerodynamic f i x e s , w i t h
primary emphasis on o p t i m i z i n g t h e "haLosfPp r e v i o u s l y t e s t e d and, a£ t e r
completing t h e aerodynamic f i x t e s t s , t o conduct t e s t s w i t h o u t r e d - l i n i n g
model t o F r v e s t i g a t e peak response loads. Eangley p e r s o n n e l f e l t t h e
proposed t e s t s were u q j u s t i f i e d because:
(I), The f e a s i b i l i t y of u s i n g t h e p r e s e n t "halo'"
c o ~ . f i g u r a t i s nhas n o t been thoroughly i n v e s t i g a t e d by MSFC.
(2)
Reduction of "haloq9s i z e would p o s s i b l y reduce
t h e e f f e e t i v e r e s s of t h e h a l o s below an a c c e p t a b l e l e v e l .
(3)
So a d d i t i o n a l r e a s o n a b l e aerodynamic f i x e s have
been proposed by MSPC.
�( 4 ) I n v e s t i g a t i o n of peak response beyond t h e v a l u e s
t e s t e d p r e v i o u s l y would be u s e l e s s because u n d e f i n a b l e changes i n t h e
s t r u c t u r a l c h a r a c t e r i s t i c s of t h e model a t h i g h e r l o a d i n g s would
invalidate the data.
b.
I f Langley personnel can be convinced t h a t such t e s t s
a r e j u s t i f i e d , they will. r e q u i r e t h e following up-to-date information:
( 1 ) F i r s t n a t u r a l frequency of v e h i c l e on t h e launch
pad and c r a w l e r f o r a l l weight c o n f i g u r a t i o n s t o be t e s t e d and c o r r e sponding mode shape and g e n e r a l i z e d mass f o r each c o n d i t i o n .
( 2 ) Allowable base bending moment and bending moment
d i s t r i b u t i o n along vehicle.
c.
The f o l l o w i n g c o u r s e of a c t i o n i s being i n i t i a t e d by
R-AERO-AU:
(1) A formal memo and l e t t e r w i l l be w r i t t e n t o P & E
and Kennedy Space C e n t e r , r e s p e c t i v e l y , r e l a t i n g ~ a n g l e y ' so p i n i o n on
conducting such t e s t s and r e q u e s t i n g t h e i r r e a s o 2 s , i f any, why t h e
s i z e and l o c a t i o n of t h e '%halos1' p r e v i o u s l y t e s t e d would be u n s a t i s f a c t o r y
on t h e v e h i c l e . Also, i f t h e l a r g e l l h a l o s ' h c a n o t be used, R-AERO-AU
should be informed of t h e maximum a l l o w a b l e " h a l o l b i z e and t h e l o c a t i o n
where t h e y could be a p p l i e d .
( 2 ) Formally r e q u e s t up-to-date
c h a r a c t e r i s t i c s and c a p a b i l i t i e s from P&VE.
vehicle structural
( 3 ) I f such t e s t s o u t l i n e d above can be j u s t i f i e d ,
r e q u e s t Langley t o conduct them.
d. Action item b w i l l r e q u i r e a d d i t i o n a l a i d from t h e
c o n t r a c t o r (Boeing) s i n c e no t e s t i n g o r i g i n a l l y was p r o j e c t e d i n c o n t r a c t
p l a n n i n g . M r . McNair i s reviewing p r e s e n t Boeing t a s k assignments t o
determine i f t h i s a d d i t i o n a l workload may be absorbed w i t h o u t i n c r e a s i n g
t h e o v e r a l l l a b o r a t o r y l e v e l of e f f o r t . This survey should be completed
by November 1 7 , 1965.
M r . E. D. Deese of KSC, who c o n t a c t e d t h i s o f f i c e on
November 1 0 , 1965, r e p o r t e d t h a t KSC was working on o f f i c i a l exposure
and r e a c t i o n times f o r t h e S a t u r n V v e h i c l e and t h a t a survey i n d i c a t e s
t h a t v e h i c l e d e f l e c t i o n w i l l have t o be h e l d below 36 inches when t h e
mobile s e r v i c e s t r u c t u r e (MSS) i s around t h e v e h i c l e .
In addition, Mr.
Deese suggested t h a t t h e i n f l u e n c e of t h e MSS on v e h i c l e dynamic r e s p o n s e
be i n v e s t i g a t e d and t h a t aerodynamic l o a d s on t h e MSS i t s e l f be e s t a b l i s h e d ,
KSC would d e s i g n and f a b r i c a t e t h e model, and a d e c i s i o n would be needed
i n t h e near f u t u r e t o meet a February o r March t e s t d a t e . R-AERO-AU
�informed KSC o f ~ a n g l e y ' sp o s i t i o n and of t h e upcoming MSPC r e q u e s t .
The KSC s u g g e s t i o n w i l l be i n c o r p o r a t e d i n t o t h e t e s t p l a n , i f f e a s i b l e .
6.
S a t u r n 1 3 / ~ e n t a u rGround Winds
Although R-AERO-AU has r e l e a s e d a l l scheduled wind t u n n e l
r
wind s t u d i e s , t h e c o n t r a c t w i t h Atkins
time f o r S a t u r n Z ~ / ~ e n t a uground
and M e r r i l h , H D ~ . , t o r e d e s i g 3 and c o n s t r u c t a more e x a c t a e r o e l a s t i c
ground winds model of t h e S a t u r n ~ / @ e n t a uwas
r
n o t canceled. R-AERO-AU
f e l t i t d e s i r a b l e t o c o n t i x u e w i t h t h e c o n s t r u c t i o n of t h i s model because
Atkins and M e r r i l l had almost completed t h e r e d e s i g n o f t h e S-IS and S - I D
s t a g e s when R-AERO-AU r e c e i v e d i n s t r ~ c t i o n st o r e l e a s e scheduled wind
t u n n e l time. Also, because t h i s model has a more e x a c t mass and s t i f f n e s s
d i s t r i b u t i o n , and because of t h e p o s s i b i l i t y o f u s i n g t h i s model w i t h
o t h e r f u t u r e payload shapes and w e i g h t s , t h e model would be v e r y h e l p f u l
i n u n d e r s t a n d i n g and f i n d i n g f i x e s for t h e g u s u ~ dwinds problem.
The M a r t i n Company has prepared a p r e l i m i n a r y r e p o r t o f
on.-line d a t a obtain.ed. du.ring the wind t u n n e l t e s t program ( P u b l i c a t i o n ,
Section 10); these reports a r e not f o r d i s t r i b u t i o n . N r t h e r data
r e d u c t i o n by M a r t i n has h a l t e d a w a i t i n g c o n t r a c t n e g o t i a t i o n f o r c o s t
overruns.
8.
A e r o e l a s t i c C h a r a c t e r i s t i c s of Vehicle 203
Am experiment t o b e t t e r d e f i n e t h e p r e s s u r e d i s t r i b u t i o n
i n t h e Mach range of .80 t o .95 has been completed. This i n f o r m a t i o n
has been forwarded to Lockheed a s an aid i n determining t h e aerodynamic
damping o f v e h i c l e 203.
9.
Dynamics o f Separated Plow
M r . E r i c i s s o n p r e s e n t e d t h e f i n a l r e s u l t s of c a n t r a c t
NAS8-5338 02 November 9 , 1965. This c o n t r a c t w i l l be t e r m i n a t e d upon
completion of a f i n a l r e p o r t t o be r e l e a s e d about December 31, 1965.
�VI.
DPXAMICS AND FLIGHT MECHANICS DIVISION
A.
Applied Guidance and P l i g h t Mechanics Branch
1.
Saturn IB
a. A memorandum e n t i t l e d " V e l o c i t y E r r o r Due t o T h r u s t
Decay o f t h e S-IVB S t a g e f o r AS-201 and AS-20%80h a s b e e n d i s t r i b u t e d .
A v e n t i n g a n a l y s i s f o r t h e AS-203 ( l i q u i d hydrogen e x p e r i m e n t ) h a s b e e n
conducted,
Preliminary r e s u l t s indicate t h a t variations i n vent force
and i n s e r t i o n c o n d i t i o n s c a u s e no s i g n i f i c a n t change i n t h e o r b i t a l
conditions.
Thus, l i t t l e e f f e c t i s e x p e c t e d on t h e t r a c k i n g a c q u i s i t i ~ n
and l o s s t i m e ; t h i s i s b e i n g s t u d i e d by R-AERO-F.
b.
Performance changes due t o i n d i v i d u a l p e r t u r b a t i o n s o f
t h e s t a g e and v e h i c l e c h a r a c t e r i s t i c s sf t h e S a t u r n I ~ / @ e n k a u vr e h i c l e
have b e e n d e t e r m i n e d ,
The NASA T e c h n i c a l Memorandum c o v e r i n g t h e g e n e r a l
performance s u r v e y i s b e i n g p r e p a r e d .
c. The s t u d y on l a u n c h p r o b a b i l i t y f o r d u a l l a u n c h t y p e
m i s s i o n s h a s b e e n f i n i s h e d , and a r e p o r t i s b e i n g p r e p a r e d .
2,
Saturn V
a. The e f f e c t s o f c o n t i n u o u s o p e r a t i o n o f t h e AS-503 S-IVB
oxygen-hydrogen b u r n e r (modified S-IV helium h e a t e r ) upon t h e LOR m i s s i o n
parking o r b i t a r e being investigated.
The b u r n e r w i l l be i n s t a l l e d o n
AS-503 and s u b s e q u e n t p r i m a r i l y f o r r e p r e s s u r i z a t i o n of t h e S-Em s t a g e .
However, i f t h e r e s u l t s o f t h e AS-20% e x p e r i m e n t i n d i c a t e t h e r e q u i r e m e n t ,
t h e b u r n e r w i l l be o p e r a t e d c o n t i n u o u s l y t h r o u g h o u t t h e p a r k i n g o r b i t t o
p r o v i d e a d d i t i o n a l t h r u s t f o r s e t t l i n g t h e p r o p e l l a n t s i n t h e S-PVB.
The
The r e q u i r e d computer r u n s ,
b u r n e r h a s a t h r u s t l e v e l o f 15 t o 22 pounds.
u s i n g p r e l i m i n a r y d a t a , have been s u b m i t t e d .
b, The two-volume DM-2 d e s i g n r e f e r e n c e m i s s i o n document
i s b e i n g i n s p e c t e d and c o r r e c t e d , and should go t o reproductizhn on
December 11, 1965. T h i s document i s t h e p r o d u c t o f a j o i n t working
organizations, operating
g r o u p , composed o f p e r s o n s from t h e MSFC/TBC/NSC
under t h e d i r e c t i o n o f t h e R e f e r e n c e T r a j e c t o r y Subpanel,
c. A s t u d y o f t h e f e a s i b i l i t y o f i n i t i a t i n g g u i d a n c e d u r i n g
t h e S-IC s t a g e o f t h e S a t u r n V AS-506 v e h i c l e shows t h a t t h e p a y l o a d c a n
be i n c r e a s e d c o n s i d e r a b l y by u s i n g l i f t i n g t r a j e c t o r i e s l e a d i n g i n t o t h e
r e l e a s e o f t h e HGM e q u a t i o n s between 80 t o 90 s e c o n d s , b u t t h e r e i s a l s o
a n a s s o c i a t e d i n c r e a s e i n loads.
An o p t i m i z e d z e r o - l i f t t r a j e c t o r y w i t h
IGM b e i n g r e l e a s e d a f t e r tower j e t t i s o n was u s e d a s a r e f e r e n c e t r a j e c t o r y .
The l o a d s were n o t i n c r e a s e d d u r i n g t h e b o o s t e r s t a g e s i n c e t h e a n g l e o f
a t t a c k b u i l d u p came a f t e r t h e max q r e g i o n was p a s s e d .
This approach
�gave an i n c r e a s e of 1100 pounds i n parking o r b i t ,
This 1100 pounds
could be t r a d e d back i n t o a s t e e p e r t r a j e c t o r y f o r a 3 p e r c e n t r e d u c t i o n
i n l o a d s w i t h no payload p e n a l t y over t h e r e f e r e n c e t r a j e c t o r y .
d. Openc and c l o s e d loop guidance i n t h e S-IC s t a g e o f
t h e S a t u r n V AS-506 v e h i c l e i s being analyzed.
The i t e r a t i v e guidance
was r e l e a s e d on t h e r e f e r e n c e t r a j e c t o r y a f t e r t h e max q r e g i o n was
The
passed t o shape t h e t r a j e c t o r y f o r t h e open loop t i l t program.
c l o s e d loop guidance approach i n t h e b o o s t e r could n o t be j u s t i f i e d
over t h e open loop guidance system from a 3-sigma v e h i c l e and atmospheric
p e r t u r b a t i o n study. However, an S-IC engine-out a n a l y s i s shows t h a t t h i s
may n o t be the case.
The engine-out a n a l y s i s i s completed, and a s i m i l a r
a n a l y s i s of engine-out i n t h e S-IC s t a g e f o r l i f t i n g t r a j e c t o r i e s l e a d i n g
i n t o IGM r e l e a s e a f t e r max q i s being made.
e. The payload c a p a b i l i t y of S a t u r n V v e h i c l e s , based upon
November c u r r e n t w e i g h t s , was r e c e i v e d from TBC and t r a n s m i t t e d t o
I n d u s t r i a l Operations.
3.
General
a. A j o i n t working group c o n s i s t i n g of personnel: from t h e
MSFC/GE/TBC/MSC/TRW o r g a n i z a t i o n s i s developing a computer program f o r
The program employs
g e n e r a t i n g " J o i n t Apollo Reference T r a j e c t o r i e s . "
( a s much a s p o s s i b l e ) t h e r e s u l t s of t h e ' V e h i c l e Systems and T r a j e c t o r y
Analysis M o d u l a r i z a t i o n t > r o j e c t , and t h e " P r o j e c t Apollo Coordinate
System Standards."
For c u r r e n t needs, a m a k e s h i f t program i s i n o p e r a t i o n
t o g e n e r a t e documents such a s t h e DRM-2, b u t , a t t h e same time, t h e
e f f i c i e n t modularized program i s being developed.
The modularized
program should be e a s i l y modified t o g e n e r a t e o p e r a t i o n a l t r a j e c t o r i e s
when t h a t phase o f t h e program i s reached.
b.
S t u d i e s a r e b e i n g conducted by Boeing, C h r y s l e r , Northrop
and in-house personnel i n c o o r d i n a t i o n w i t h AERO-F, P&VE, and ASTR on t h e
e f f e c t s of t h r u s t o s c i l l a t i o n r e s u l t i n g from t h e closed-loop a c t i o n of t h e
p r o p e l l a n t u t i l i z a t i o n system d u r i n g t h e S-I1 and S-IVB f l i g h t on t h e
guidance accuracy and payload.
These s t u d i e s c o n s i d e r both p r e d i c t e d
t h r u s t h i s t o r i e s (provided by P&VE) and p a r a m e t r i c v a r i a t i o n s i n t h e
amplitude and p e r i o d of a s i n e wave r e p r e s e n t a t i o n of t h r u s t .
These
s t u d i e s , which i n c l u d e b o t h t h e S a t u r n I B and t h e S a t u r n V v e h i c l e s ,
a r e being g i v e n t o p p r i o r i t y i n t h e guidance work of a l l of t h e i n d i c a t e d
groups, w i t h a heavy commitment of manpower and computer time involved.
c.
The s t e e p e s t d e s c e n t o p t i m a l t r a j e c t o r y program has been
completed.
The program u s i n g t h e complete a d j o i n t method which f i n d s
e x a c t o p t i m a l s i n t h e sense t h a t t h e t r a j e c t o r i e s s a t i s f y t h e n e c e s s a r y
c o n d i t i o n i s a l s o completed.
It i s planned t o i n c o r p o r a t e i n e q u a l i t y
c o n s t r a i n t s i n t o t h e l a t t e r program i n t h e near f u t u r e . Reports on t h e
�two t e c h n i q u e s a r e b e i n g prepared a s w e l l a s a summary o f t h e r e l a t i v e
advantages and d i s a d v a n t a g e s . This work has been performed t o develop
an in-house c a p a b i l i t y i n o p t i m i z a t i o n techniques o t h e r t h a n c l a s s i c a l
COV i n a d d i t i o n t o t h e obvious advantage of o b t a i n i n g a good program.
d. A study i s being i n i t i a t e d t o s i m p l i f y and reduce t h e
g e n e r a l s t a g e i t e r a t i v e guidance e q u a t i o n s by e l i m i n a t i n g t h e c r o s s
coupling yaw s t e e r i n g r a t e Q K 4 ) . A memorandum o n the r e s u l t s w i l l be
issued.
e. The study on the p r o b a b i l i t y o f t h e S-IVB/IU
the moon i s complete and a r e p o r t has been prepared.
impacttng
f.
The purpose of t h e l u n a r launch window s t u d y i s t o show
the e f f e c t of t h e o p e r a t i o n a l c o n s t r a i n t s o f launch azimuth, Bawnch
l i g h t i n g , Lunar l i g h t i n g , launch window w i d t h , and Paunch p e r i o d on t h e
l u n a r launch windows f o r t h e 1967-72 time perksd. An I n t e r n a l Note i s
being prepared.
?%he
c r l n s t r a f n t o f launch l i g h t i n g Fs being removed from
t h e c u r v e s , and t h e r e s u l t i ~ gk a ~ n c bwindow d i s p l a y s will be published
i n another report.
4.
Advanced Apollo Program ( U P )
a.
Program).
The name MAP seems uncommonly a p p r o p r i a t e i n t h i s c a s e because
t h e program d e s i r e d i s t o examine launch o -p-p o r t u n i t i e s and miss i o n
c o n s t r a i n t s and 'hap" o u t f o r t h e u s e r t h o s e Launch s p p o r t u n i t i e s and
launch c o n d i t i o n s t h a t a l l o w one t o s a t i s f y a l l t h e d e f i n e d c o n s t r a i n t s .
Although approximations a r e used i n t h i s p r e l i m i n a r y a n a l y s i s , t h e MAP
results are quite reliable.
The program i n use a t MSC f o r MAP purposes
was picked up l a s t week; no documentation i s a v a i l a b l e .
The MSC program
i s limited t o lunar applications.
Our i n t e n t i s t o p i c k up a program
from Goddard t h a t has some g e n e r a l f e a t u r e s d e s i r e d f o r t h e MAP program,
p u l l any u s e f u l modules from t h e MSC program, and d e v e l c p o t h e r modules
r e q u i r e d t o produce t h e d e s i r e d MAP program.
The r e s u l t a n t program should
be e s p e c i a l l y u s e f u l f a r AAP s t u d i e s .
b.
The payload c a p a b i l i t y of
Saturn I B v e h i c l e s , based upon November c u r r e n t wei,ghts, was r e c e i v e d
from CCSD and t r a n s m i t t e d t o I n d u s t r i a l Operations.
c.
S a t u r n HB P o l a r O r b i t s .
Optimized t r a j e c t o r i e s f o r
S a t u r n I B P o l a r O r b i t s have been generated f o r b o t h a t h r e e - s t a g e d i r e c t
a s c e n t i n t o a 200 nm c i r c u l a r p o l a r o r b i t and f o r a f l i g h t p r o f i l e w i t h
a s u b o r b i t a l s t a r t of t h e S e r v i c e M ~ d u l ei n t o an 80 nm e l l i p s e c i r c u l a r i z e d
a t apogee u s i n g a second burn of t h e SM. Work c o n t i n u e s t o i n c l u d e a
14-day o r b i t and d e - o r b i t t o the r e e n t r y p o i n t , b u t p r o g r e s s i s slow because
of problems i n t h e computer r o u t i n e .
�T r a j e c t o r i e s have been completed f o r a S a t u r n I B v e h i c l e
d.
two-stage d i r e c t a s c e n t i n t o a 200 m c i r c u l a r o r b i t f o r Apol%a a p p l i c a t i o n s
o r b i t a l experiments,
One v e h i c l e would be used f o r a f u e l t r a n s f e r
experiment, w h i l e the o t h e r would house an o r b i t a l workshop i n t h e
D o c m e n t a t i o n has been delayed because
empty S-IVB p r o p e l l a n t tanks.
of o t h e r work w i t h higher p r i o r i t i e s .
e. A study has been i n i t i a t e d t o d e f i n e t h e amount s f
f l i g h t performance r e s e r v e s r e q u i r e d t o guarantee S a t u r n I W payloads
when t h e S e r v i c e Module i s used a s a t h i r d s t a g e . A nominal t r a j e c t o r y
The s t u d y ,
has been determined based upon an 81 nm by 107 run e l l i p s e .
being j o i n t l y conducted w i t h h c k h e e d , i s 50 per c e n t complete.
f,
An e x i s t i n g caZcuPus o f
v a r i a t i o n s computer r o u t i n e l w i t h m o d i f i c a t i o n s t o c u t o f f on C3 and
i s o l a t e a n i n j e c t i o n plane has been checked o u t . Wurk w i l l resume when
problems of higher p r i o r i t y have been s t u d i e d .
The r e q i ~ % r e m e nft o r
t h i s program has been r e c s g ~ i z e d fram surveying t h e prap-jsed U P m i s s i o n s .
g.
A s t u d y i s b e i n g conducted t o d e f i n e t h e c a p a b i l i t y of
t h e S a t u r n V v e h i c l e c f p l a c i n g a paylcad i n t o a synchronous e q u a k o r i a l
orbit.
The s t u d y i n c l u d e s both a s u b o r b i t a l s t a r t of t h e S-It% i n t o a
100 nm p a r k i n g o r b i t and an o r b i t a l s t a r t of t h e S-PVB o u t of 100 run
parking o r b i t .
The r e q u i r e d plane change i s made a f t e r t h e parktng o r b i t .
h.
Saturn V Polar Orbit.
The pay1,oad c a p a b i l i t y of t h e
Saturn V v e h i c l e f o r 200 nm a l t i t u d e p o l a r o r b i t has been d e f i n e d and
documented i n R-AEIPO-DAP-104-65.
.
i.
A 1 1 S a t u r n HB and
S a t u r n ~ ~ / ~ e n t performance
a u r
c a p a b i l i t y d a t a have been completed.
J. The comparison of machine time v e r s u s accuracy of
v a r i o u s e x i s t i n g perfcrrnanee r o u t i n e s and t h e Lockheed-developed PRESTO
I f t h e Leckheed claims f o r t h i s program a r e
r o u t i n e i s completed.
v e r i f i e d , i t should prove t o be an e x c e l l e n t tcoL f o r U P f l i g h t p r o f i l e s .
k. A memorandum has been d i s t r i b u t e d which documents t h e
m i s s i o n p r o f i l e f o r AAP l u n a r mapping mission.
T h i s p r o f i l e was p r e s e n t e d
a t t h e AAP M i s s i o n Planning Task Force meeting a t MSC on November 9 ,
1. Development s f t h e e a r t h o r b i t a l rendezvous deck u s i n g
IGM continued.
Two t y p e s o f rendezvous a r e now being attempted.
In t h e
f i r s t c a s e b o t h t h e p u r s u i t and t a r g e t v e h i c l e s a r e i n c i r c u l a r p a r k i n g
o r b i t s w i t h t h e p u r s u i t v e h i c l e i n the inner o r b i t .
These two v e h i c l e s
have been brought t o w i t h i n 10 k i l o m e t e r s of each o t h e r w i t h small e r r o r s
I n the second c a s e t h e t a r g e t v e h i c l e i s i n an e l l i p t i c a l
i n velocity,
orbit.
F a i r l y l a r g e e r r o r s i n p o s i t i o n a r e a l s o being o b t a i n e d i n t h i s
case.
Continued development and refinement of t h i s deck should e l i m i n a t e
t h e s e inaccrlracies i n p o s i t ion.
�5.
Contractors
(1) AS-501 R e f e r e n c e T r a j e c t o r y Document: The Boeing
document "AS-581 Launch V e h i c l e R e f e r e n c e ' T r a j e c t c r y s vi s b e i n g reviewed
before r e l e a s e .
(29 AS-502 R e i e r e n c e T r a j e c t o r y Dosl.m?nf:
The AS-582
launch v e h i c l e r e f e r e n c e t r a j e c t o r y i s being prepared,
31e b a s i c t r a j e c E2wevez-, a n a d d i t i o n a l
t o r y w i l l be f o r l a u n c h a l o n g an azimuth of 72'.
s t u d y w i l l . be made t o d e t e r m i n e t h e e f f e c t of a v a r i a b l e haunch azimuth
and a v a r i a b l e c o a s t p e r i o d i n p a r k i n g o r b i t on the ground t r a c k , s p l a s h
s i t e , l a u n c h windaw, and t r a c k i n g a v a i l a b k l i t y .
(13) AS-363 P x e l i v a n a r q Elnss i ~ Prc
n file: Ike AS-563
p r e l i m i n a r y rnissaon p r ~ f i l ewas p r e s e n t e d ks t h e L 2,B sl-&bpa.neIm e e t i n g
? t h a t %ha p r o f i l e
a t MSC o n November 5 , 1965, MSt personnel ~ ~ i n k e dt
did not completely s a t i s f y a s e t c f r e i e n r l y r e l e a s e d S / C m i s s f ~ n
requirements.
MSC r e q u e s t e d MSBC serpprlrt i n p r e p a r i n g a s e t ?F l a u n c h
v e h i c l e i n j e c t i o n characteristics f o r s e v e r a l p c s s i b l e S / C missLon
profiles.
Boeing i s p r e p a r i n g t h e d a t a .
( 4 ) AS-504 Spectrum:
I n r e s p o n s e t o a r e q u e s t of t h e
r e f e r e n c e t r a j e c t o r y s u b p a n e l , a s e t of k r a j e c t a r i e s i s b e i n g g e n e r a t e d
f o r t h e AS-504 m i s s i c n ,
This s e t bncludes f i v e launch a z i m u t h s w i t h a
f i r s t and second o r b i t i n j e c t i o n from e a c h , f o r a t c t s l 0 2 P O t r a j e c t o r i e s .
The d a t a t o be g e n e r a t e d f o r d a y s o t h e r t h a n t h e primary l a u n c h day have
n o t been d e c i d e d upon.
T h i s work i s scheduled t o be completed by
December 13.
(5) T r a j e c t o r y O p t i m i z a t i o n Program: %be document
d e s c r i b i n g t h e r e s u l t s of t h e s t e e p e s t a s c e n t t r a j e c t o r y s t u d y f o r
maximizing p a y l c a d i n o r b i t s u b j e c t t o Lnequal-ity c ~ n s t r a i n t sd u r i n g
a t m o s p h e r i c f l i g h t i s b e i n g c ~ m p l e t e d . A d ~ s c u s s i c n<>f t h e c o m p a t i b i l i t y
of t h e r e s u l t s with s t a g i n g requirements i s being ~ n c l u d e d , Application
of ISONAX t o t h e a n a l y s i s i s b e t n g s t u d i e d .
6
F l i g h t P l a n Computer Program Develcprnent : T h i s
program, which i s a p o r t i o n of t h e J o i n t ApolEc R e f e r e n c e T r a j e c t o r y
Program, i s t o be used f o r a d e t a i l e d s s m u l a t i s n ~f the launch v e h i c l e
flight.
E n g i n e e r i n g a n a l y s i s i s c o n t i n u i n g on t h e p a r k i a g o r b i t and
b o o s t - t o - i n j e c t i o n s i m u B a t ~ o n s , Models f 3 r v e n t % n g and u l l a g e t h r u s t
have b e e n d e v e l o p e d and coded. The s t u d y o f p a r k i n g o r b i t p e r t u r b a t i o n s
caused by t h e moon and s u n , a s w e l l as checkout cf p a r k i n g o r b i t subr o u t i n e s , h a s b e e n d e l a y e d because o f program checkout.
�( 7 ) T a r g e t i n g D e f i n i t i o n and S i m p l i f i c a t i o n : The
purpose o f t h i s assignment i s t o f i n d t h e b e s t way t o d e f i n e and make
a v a i l a b l e t h e t a r g e t i n g parameters a s r e q u i r e d by t h e i t e r a t i v e guidance
mode, The t a r g e t parameters r e p r e s e n t o r b i t and l u n a r i n j e c t i o n t e r m i n a l
c o n d i t i o n s . An e x p r e s s i o n has been o b t a i n e d f o r launch azimuth v a r i a t i o n
a s a f u n c t i o n of time o f launch f o r t h e simple s p h e r i c a l case.
Difficulties
have been encountered i n g e n e r a t i n g a f u n c t i o n which w i l l make up t h e
d i f f e r e n c e i n going from t h e s p h e r i c a l t o the complete case.
b.
Chrysler
(1) AS-203 and AS-204 Engine-Out Analysis: The r e s u l t s
of t h e s i n g l e and d u a l S-IB engine-out s t u d i e s f o r t h e AS-203 and AS-204
v e h i c l e s a r e being published.
( 2 ) AS-203 Launch Vehicle Reference T r a j e c t o r y : An
AS-203 r e v i s e d launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been g e n e r a t e d ,
and p r e l i m i n a r y documentation h a s been r e c e i v e d . A f l i g h t c o r r i d o r ,
d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements being
prepared should be completed e a r l y i n December.
(3) AS-203 I n t e r s t a g e Venting T r a j e c t o r y : P r e l i m i n a r y
documentation of a maximum and minimum p r e s s u r e time h i s t o r y has been
received.
Review o f t h e s e t r a j e c t o r i e s w i l l be a j o i n t e f f o r t w i t h
R-AERO-ADD.
(4)
AS-204 Launch Vehicle Reference T r a j e c t o r y : The
f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e
requirements document i s being published.
(5) AS-205 and 206 P r e l i m i n a r y Launch V e h i c l e Reference
T r a j e c t o r i e s : The AS-205 and 206 launch v e h i c l e p r e l i m i n a r y r e f e r e n c e
t r a j e c t o r i e s have been documented. A f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s ,
and f l i g h t performance r e s e r v e requirements f o r AS-206 a r e being generated.
The AS-205 d e s i g n t r a j e c t o r i e s , f l i g h t c o r r i d o r , e t c . , a r e being published.
(6) AS-205 and AS-206 Abort and A l t e r n a t e Missions:
P r e l i m i n a r y documentation of AS-205 and AS-206 a b o r t and a l t e r n a t e
m i s s i o n p l a n s i s b e i n g reviewed.
AS-207 P r e l i m i n a r y Launch Vehicle Reference
(7)
T r a j e c t o r y : A f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance
r e s e r v e requirements a r e b e i n g determined and should be completed i n
December.
(8) AS-207 Abort and A l t e r n a t e Missions: A s t u d y i s
underway t o d e f i n e the performance c a p a b i l i t y of the AS-207 v e h i c l e w i t h
s i n g l e and d u a l e n g i n e s o u t t o perform t h e primary m i s s i o n o r t o d e f i n e
an a c c e p t a b l e a l t e r n a t e mission.
�( 9 ) T h r e e - D e g r e e s - o f - F r d m Computer Routine: A v e r y
a c c u r a t e check o f t h e AS-207 launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been
obtained.
Work c o n t i n u e s on expanding t h e c a p a b i l i t y of t h i s r o u t i n e ,
which i s t o r e p l a c e t h e r o u t i n e now being used.
c.
Lockheed
The use o f s w i t c h i n g f u n c t i o n t h e o r y t o d e t e r m i n e
optimum s t a g i n g p o i n t s i s being i n v e s t i g a t e d . The s w i t c h i n g f u n c t i o n
e q u a t i o n s have been w r i t t e n and have been i n c o r p o r a t e d i n t o a n e x i s t i n g
two-dimensional vacuum computer r o u t i n e .
Checkout a n a l y s i s i s complete,
If t h e
and t h e three-dimensional e q u a t i o n s a r e being formulated.
s w i t c h i n g f u n c t i o n approach proves t o be p r a c t i c a l f o r g e n e r a l performance
c a l c u l a t i . o n s , i t i s planned t o e v e n t u a l l y r e p l a c e o r modify e x i s t i n g
performance computer programs u n t i l a l l programs u s e t h i s much more
e f f i c i e n t technique.
d,
Ling-Temco -Vought
The l u n a r launch window study,wilP be completed i n
December w i t h f i n a l documentation i n January.
No major problems have
been encountered.
e.
Northrop
(1) The E r r o r P r o p a g a t i o n Computer Program w i l l u s e
a Monte C a r l o t e c h n i q u e t o g e n e r a t e a s e t of t r a n s l u n a r i n j e c t i o n e r r o r s ;
t h e n , u s i n g a s e t o f two body p a r t i a l d e r i v a t i v e s , t h e s e e r r o r s w i l l be
propagated t o p o s i t i o n and v e l o c i t y e r r o r s a t some f u t u r e time a l o n g t h e
trajectory.
Using t h e s e new p o s i t i o n and v e l o c i t y p o i n t s , a d i s t r i b u t i o n
This program w i l l be used t o s u p p o r t
of midcourse AV w i l l be g e n e r a t e d .
both Apollo and AAP s t u d i e s .
The advantage of t h i s program over p r e v i o u s
r o u t i n e s i s t h e i n c o r p o r a t i o n of t h e two-body p a r t i a l d e r i v a t i v e s which
w i l l a l l o w much f a s t e r and more e f f i c i e n t g e n e r a t i o n of t h e d e s i r e d d a t a
a t l i t t l e l o s s i n accuracy.
( 2 ) The second p a r t o f t h e S a t u r n V hardware e r r o r
The d a t a a r e being a n a l y z e d ,
analysis i s i n the d a t a processing stage.
using Monte C a r l o t e c h n i q u e s , and a r e b e i n g compared t o t h e r e s u l t s
o b t a i n e d from t h e r o o t sum s q u a r e (RSS) s t u d y p r e v i o u s l y completed, A
Monte C a r l o a n a l y s i s of t h e p o s i t i o n and v e l o c i t y v e c t o r s a t i n j e c t i o n
onto t h e l u n a r t r a n s f e r c o n i c has g i v e n an e r r o r p r e d i c t i o n a l m o s t
i d e n t i c a l t o t h a t o b t a i n e d w i t h t h e RSS method.
( 3 ) A guidance p l a t f o r m switchover c a p a b i l i t y has been
s u c c e s s f u l l y added t o t h e System A n a l y s i s deck.
This deck can now be
used t o conduct a study i n which b o t h open l o o p and c l o s e d l o o p t r a j e c It i s hoped t h a t t h i s s t u d y w i l l
t o r i e s a r e s i m u l t a n e o u s l y simulated.
r e v e a l t h a t open loop guidance can be used f o r checkout of t r a j e c t o r i e s
guided by e i t h e r open o r c l o s e d loop methods.
�(4) The r e s u l t s of a p e r t u r b a t i o n s t u d y on t h e r e c e n t l y
developed l u n a r b r a k i n g deck u s i n g IGM have been g i v e n t o i n t e r e s t e d NASA
personnel.
Another p e r t u r b a t i o n s t u d y i s underway i n which t h e i n c l i n a t i o n
and nodal l o n g i t u d e a r e p r e s p e c i f i e d and f i x e d .
B.
Control Theory Branch
1.
Saturn I B
The l o s s of h y d r a u l i c power t o one c o n t r o l engine o f t h e
AS-204 v e h i c l e has been i n v e s t i g a t e d from l i f t - o f f t o a f l i g h t time o f
50 seconds.
I n c a s e s where t h e r o l l r a t e of t h e v e h i c l e was e x c e s s i v e l y
h i g h , t h e t r a j e c t o r y was terminated.
This i s i n answer t o an a c t i o n item
from t h e F l i g h t Mechanics P a n e l , which r e q u e s t e d t h i s f a i l u r e mode be
extended and t h e t r a j e c t o r y p r i n t o u t f u r n i s h e d t o t h e p r o p e r people a t
MSC, Houston.
Three c a s e s have been chosen. A l l t h r e e c a s e s b u i l d t o a
p i t c h and yaw a t t i t u d e r a t e of 1 t o 2 degrees per second. However, t h e
r o l l r a t e goes t o 5 degrees p e r second f o r a l l t h r e e c a s e s i n l e s s than
two seconds a f t e r t h e f a i l u r e .
From t h i s p o i n t t h e behavior of t h e
three cases d i f f e r .
CASE 1. The r o l l r a t e c o n t i n u e s to b u i l d and t h e p i t c h
and yaw r a t e s remain c o n s t a n t o r d e c r e a s e . A t t h e end of 5 seconds, t h e
r o l l r a t e i s 11 degrees p e r second and t h e p i t c h and yaw r a t e s a r e o n l y
1%d e g r e e s p e r second. A t 3% seconds a f t e r f a i l u r e , t h e pitch-yaw
a t t i t u d e i s 5 d e g r e e s w i t h a r a t e o f 1 314 degrees p e r second. However,
t h e r o l l a n g l e i s 19 d e g r e e s w i t h a r o l l r a t e of 7% d e g r e e s per second.
CASE 2.
The r o l l r a t e remains f a i r l y c o n s t a n t a t 4% t o
5 degrees per second, and t h e p i t c h and yaw r a t e s drop t o 1 d e g r e e per
second o r l e s s . A t t h e end of 8 seconds, t h e r o l l r a t e i s 5 degrees
per second and t h e pitch-yaw r a t e s a r e % d e g r e e p e r second. A t t h e end
of 4 seconds a f t e r f a i l u r e , t h e pitch-yaw a t t i t u d e a n g l e i s 5 degrees w i t h
a r a t e o f 1 d e g r e e p e r second; however, t h e r o l l a n g l e i s 17% degrees w i t h
a r a t e of 4% d e g r e e s p e r second.
CASE 3. The r o l l r a t e goes t o 5 degrees p e r second
w i t h i n 1%seconds a f t e r f a i l u r e and t h e n r e t u r n s t o z e r o a f t e r 5% seconds
from f a i l u r e .
The pitch-yaw r a t e s go t o 1%d e g r e e s p e r second w i t h 2
seconds a f t e r f a i l u r e and t h e n r e t u r n t o z e r o w i t h i n 6 seconds from
failure.
A t t h e end o f 6 seconds, t h e pitch-yaw r a t e s and t h e r o l l r a t e s
a r e z e r o ; however, t h e pitch-yaw a n g l e i s 5 degrees and t h e r o l l a n g l e
i s 16 degrees.
These t h r e e c a s e s g i v e a good spread o f t h e v e h i c l e
behavior under t h e i n £ luence of h y d r a u l i c f a i l u r e t o one c o n t r o l engine.
These r e s u l t s s u g g e s t t h a t t h e r o l l r a t e s and a n g l e s a r e b e t t e r i n d i c a t o r s
�o f impending t r o u b l e from t h i s f a i l u r e t h a n t h e pitch-yaw s i g n a l s .
N o t i c e i n a l l t h r e e c a s e s t h e r o l l r a t e was 5 d e g r e e s p e r second i n
l e s s t h a n 2 seconds a f t e r f a i l u r e . At t h e t h e , t h e r o l l r a t e was
5 d e g r e e s p e r s e c o n d , t h e pitch-yaw r a t e s were l e s s t h a n 2 d e g r e e s
p e r s e c o n d , and t h e pitch-yaw a n g l e s were e q u a l t o o r l e s s t h a n 2
degrees.
(1) C o n t r o l r e s p o n s e s c o v e r i n g f i r s t s t a g e f l i g h t time
t o d e t e r m i n e bending moments and c o n t r o l v a r i a b l e e n v e l o p e s e r e b e i n g
Wind g u s t s w i l l be a p p l i e d
g e n e r a t e d u s i n g c o n t r o l . w e i g h t s mass d a t a .
a t a l l a l t i t u d e s t o comply w i t h t h e new d e s i g n c r i t e r i a .
( 2 ) A s t u d y t o d e t e r m i n e t h e e f f e c t o f wind d i r e c t i o n
and wind speed o n r i g i d body c v n t r o l r e s p o n s e s and pertinent t r a j e c t o r y
November 3 , 1 9 6 5 ,
i n f o r m a t i o n h a s been documented i n Memo R-AERO-DCC-36-65,
( 3 ) %he r e s u l t s o f a s t u d y t o d e t e r m i n e t h e RSS bending
moments and c n r r e s p o n d i n g v e h i c l e c o n t r o l r e s p n n s e s have b e e n documented
a s Memo R-AERQ-DCC-37-65.
The s t u d y , based e n new c o n t r o l w e i g h t s , w i l l
s u p e r s e d e d a t a p u b l i s h e d i n R-AERO-DCC-26-65,
August 1 2 , 1 9 6 5 .
The d a t a
cover time p o i n t s c o r r e s p o n d i n g t o Mach L.0, max q , and j u s t b e f o r e
inboard e n g i n e c u t o f f .
A b r i e f s t u d y o f t h e c o n t r o l s f t h e AS-207 v e h i e l e
w i t h o u t f i n s h a s been made t o o b t a i n d a t a f o r comparison w i t h t h e
proposed s t a n d a r d l a u n c h v e h i c l e .
The e f f e c t o n s t a g i n g o f s h o r t e n i n g t h e t i m e between
d.
IECO and OECO f o r t h e S a t u r n PB h a s been examined. The p r e s e n t sequence
a l l o w s 6 s e c o n d s between t h e two e v e n t s , c o s t i n g a p p r o x i m a t e l y 200 pounds
It was d e t e r m i n e d t h a t one second between t h e two e v e n t s
i n payload.
would be s u f f i c i e n t f o r s t a g i n g r e q u i r e m e n t s from a c o n t r o l s t a n d p o i n t .
e. Using AS-202 d a t a , r i g i d body r e s p o n s e s and bending moment
c o e f f i c i e n t s were d e t e r m i n e d f o r time p o i n t s i n t h e h i g h "qs' r e g i o n o f
flight.
The c o n t r o l system used was DMP w i t h a c c e l e r o m e t e r f e e d b a c k ,
f o r a n a t u r a l f r e q u e n c y r a n g e o f .O5 t o . 3 and damping r a t i o s f - 5 and .7.
The bending moments were d e t e r m i n e d f o r e a c h c a s e t o i n v e s t i g a t e t h e e f f e c t
o f t h e c o n t r o l f r e q u e n c y . T h i s s t u d y i s 9 5 p e r c e n t complete.
2.
Saturn BB/~entaur
a. A s t u d y t o d e t e r m i n e c o n t r o l r e s p o n s e s and b e n d i n g moments
t o c o v e r time p o i n t s o v e r t h e f i r s t s t a g e f l i g h t h a s been documented.
These d a t a , i n c o n j u n c t i o n w i t h t h e d a t a p r e v i o u s l y p u b l i s h e d f o r t h e
c r i t i c a l t i m e p o i n t s , w i l l be used t o d e t e r m i n e e n v e l o p e s o f t h e r e s p o n s e s ,
T h i s w i l l t e r m i n a t e t h e Centaur e f f o r t .
�b. The r e s u l t s of t h e S a t u r n ~ ~ / ~ e n t ai nus u
r l a t i o n panels
s e p a r a t i o n s t u d y a r e b e i n g documented.
3.
Saturn V
The c o u p l i n g of h i g h e r modes w i t h t h e r i g i d body p i t c h and
d r i f t mode i s being i n v e s t i g a t e d t o determine t h e g a i n s r e q u i r e d t o
m a i n t a i n a g i v e n frequency, damping and d r i f t r o o t l o c a t i o n a s h i g h e r
modes a r e included i n t h e system.
The modes t o be added f i r s t a r e t h e
engine, low frequency s l o s h , and t h e f i r s t bending modes.
P r e s e n t l y , e i g h t d i f f e r e n t combinations of t h e s e modes have
been c a t e g o r i z e d , r a n g i n g from a t h i r d - o r d e r system ( r i g i d body p i t c h
and d r i f t modes) t o a n i n t h o r d e r system ( p i t c h , d r i f t , s l o s h , and one
The numerator and
bending mode w i t h second-order engine dynamicsj,:'
denominator pslynomiaks f o r t h e s e e i g h t systems have been o b t a i n e d .
Data a r e being p r e p a r e d t o o b t a i n t h e t r a n s f e r f u n c t i o n s from s e n s o r
o u t p u t t o engine command.
4.
General
a.
The t r a j e c t o r y , mass bending, s l o s h and aerodynamic d a t a
were t r a n s m i t t e d t o Lockheed on November 1 0 t h f o r t h e i r s t u d y , "A Nonlinear
slender-body-theory aerodynamic
F i l t e r f o r High Frequency Cutoff. "'he
c o e f f i c i e n t s a r e being o b t a i n e d .
b e The s t u d y of r e a c t i o n j e t c o n t r o l f o r t h e r e c o v e r a b l e
S-IC b o o s t e r d u r i n g r e e n t r y i s being r e v i s e d and extended. Newer, more
r e l i a b l e aerodynamic d a t a a r e being used t o c a l c u l a t e t h e v e h i c l e parame t e r s f o r t h e forthcoming analog s i m u l a t i o n . Analog computation procedures
have been i n i t i a t e d , and t h e programming i s being checked f o r c o r r e c t n e s s .
c.
F l i g h t s i m u l a t i o n s have been made t o p l o t time t r a c e s
of t h e S - I 1 s t a g e gimbal a n g l e over a ten-second p e r i o d f o l l o w i n g f i r s t
stage separation ( f i r s t plane).
The t r a c e s were r e q u e s t e d by R-P&VE-PTE
f o r use i n engine h e a t i n g c a l c u l a t i o n s .
The s i m u l a t i o n s a r e being
documented.
d. The S-IC s t a g e t r a n s i e n t s r e s u l t i n g from an engine
f a i l u r e near c u t o f f a r e b e i n g reexamined w i t h r e v i s e d c o n t r o l system
data.
P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t t h e t r a n s i e n t s w i l l be s i g n i f i Another memo w i l l
c a n t l y lower t h a n t h o s e pub1 ished i n R-AERO-DCC-34-65.
be i s s u e d t o r e f l e c t t h e change.
e. The program t o a p p l y q u a d r a t i c c o s t c o n t r o l , Kalman
f i l t e r i n g , and parameter e s t i m a t i o n techniques t o a f l e x i b l e v e h i c l e i s
w e l l underway,
S u c c e s s f u l o p e r a t i o n o f t h e Automatic S y n t h e s i s Program
was achieved. T h i s program was chosen f o r mechanization and s e v e r a l
Several o t h e r computer
problems a s s o c i a t e d " w i t h ' i t s use were r e s o l v e d ,
�program a n a l y s i s t o o l s were a l s o p r e p a r e d .
This work a s p r e s e n t e d i n
t h e f o u r t h (October 1965) p r o g r e s s r e p o r t h a s b e e n c e n t e r e d a b o u t low
o r d e r s y s t e m s u s e d a s b u i l d i n g b l o c k s toward more r e a l i s t i c c a s e s .
f.
The o b j e c t i v e o f t h i s c o n t r a c t f o r d e s i g n c r i t e r i a f o r
space v e h i c l e d u r i n g t h e haunch p h a s e o f f l i g h t i s t o p r e p a r e a s e r i e s
of monographs o n c o n t r o l and s t a b i l i t y f o r s p a c e l a u n c h v e h i c l e s .
The
f i r s t r e v i s e d monograph, VoZ. 11, P a r t 2 , "NonEinear S y s t e m s , " R e p o r t
Noo GDC-DDE65-056, September I., 1965, h a s been r e c e i v e d .
Personnel
who a r e i n t e r e s t e d i n t h i s monograph sh?uld c o n t a c t W-AERO-DCA, 876-6917.
The rough d r a f t mo~.ograph, V a l . I, P a r t 1, "Short
P e r i o d D y n a m i c s , ' 2 a s b e e n reviewed b u t h a s n e t been. r e t u r n e d t o GI)/@.
g.
Optimum u t i l f z a t i e n , i n t h e RTAS program, 0% t h e t a p e
r e a d - a n d - w r i t e pro.jced,~resd i d n o t z e d u c e t b e c 3mputer time s u f f l c i e n t l y
Do a l l o w the product lo^ of t h e l a r g e mmber o f r u n s n e c e s s a r y ,
The
system w i l l t h e r e f o r e be s i m p l i f i e d . by removing khe e n g i n e compliance
Parallel
e q u a t i o n s ; hopefuEly, k h g e w i l l r e d u c e t h e r u n n i n g t i m e .
e f f o r t s a r e b e i n g made t e a d a p t a n c t h e r p r o g r a n EOP use i n t h i s s t u d y .
5,
Contractors
(1) The a n a l y s i s o f t h e AS-203 v e h i c l e s i s r e v e a l i n g
few e n g i n e - o u t c a p a b i l i t i e s s f t h i s v e h i c l e because o f t h e l a r g e gimbal
a n g l e s r e q u i r e d even f o r t h e nonma1functioning v e h i c l e i n r e s p o n s e t o
t h e 95 p e r c e n t d e s i g n winds and t h e l a r g e u n c e r t a i n t i e s i n t h e
aerodynamics.
begun.
(2)
Engine-out a n a l y s e s on t h e AS-284 v e h i c l e have
Many of t h e r e q u i r e d e n g i n e - o u t t r a j e c t o r i e s have been g e n e r a t e d .
( 3 ) Check-out r u n s on t h e 6D computer program
m o d i f i c a t i o n s t o employ c o n t r o l f i l t e r s and n o n l i n e a r aerodynamics
are i n progress.
Use s f t h e m o d i f i c a t i o n s w i l l b e g i n s h o r t l y ,
( 4 ) A s t u d y i s b e i n g made t o d e t e r m i n e t h e d i f f e r e n c e s
i n t h e r i g i d body c o n t r o l v a r i a b l e s i n r e s p o n s e t o d e s i g n winds w i t h
c o n t r o l f i l t e r s and a c t u a t o r l i m i t s and dynamics i n c l u d e d i n t h e simul a t i o n , a s compared t o s i m i l a r r e s p o n s e s when t h e f i l t e r s and a c t u a t o r
dynamics a r e o m i t t e d .
A l l d a t a n e c e s s a r y f o r t h e s t u d y have been
f u r n i s h e d by MSFC.
(5) F l e x i b l e body l o a d s were i n v e s t i g a t e d f o r t h e
S a t u r n I B , 201 v e h i c l e u s i n g d e t a i l e d wind p r o f i l e s .
Four winds measured
w i t h t h e FPS-16 r a d a r / J i m s p h e r e were used f o r t h e a n a l y s i s .
me winds
o f J a n u a r y 12 ( T e s t No. 0866) and February 1 2 ( T e s t No. 0982) had h i g h
�s h e a r s and r e l a t i v e l y Low wfnd speeds; t h e winds of March 9 , 1965 and
These s t u d i e s were
January 27 had high wind speeds and 1i.w wfnd s h e a r s .
done i n c o n j u n c t i o n w i t h f l u t t e r s t u d i e s by D r . P l a t z e r .
The s t u d y on ''A Nonlinear F i l t e r f o r High Frequency
Gutoffto i s t o e x p l c f t t h e Lockheed GgeveBaped n o n l i n e a r f i l t e r f o r
s u p p r e s s i o n n f unwanted f l e x i b l e feedback s i g n a l s i n t h e c o n t r o l loop
During t h e f i r s t r e p o r t i n g p e r i o d , p r o g r e s s
of the S a t u r n type v e h i c l e .
was made i n determining l i n e a r network c h a r a c t e r i s t f c s r e q u i r e d f o r
To r e a l i z e smooth passage
e f f i c i e n t o p e r a t i e n of t h e n o n l i n e a r f i l t e r .
s f a s i g n a l w i t h frequency below the f i l t e r c u t o f f , i t was a s c e r t a i n e d
from a n a l y s i s and analog computer r u n s t h a t m u l t i p l e high frequency
No
s i g n a l s must undergo a s p e c i f i c p a t t e r n o f k i n e a r a t t e n u a t i o n .
d i f f i c u l t y i s expected i n determining the law frequency phase and g a i n
e f f e c t s of sampling and h y s t e r e s i s .
c.
Missi,3n S u p p o r t
98)
Seqding and Sl3sbing A n a l y s i s , S a t u r n HB Vehicle,
AS-233 B ~ o s t e rF l i g h t
This study i s to determine t h e s t a b i l i t y requirements
f o r t h e AS-203 f a r t h e f i r s t s t a g e o f f l i g h t .
The f o l l o w i n g t a s k s have
been completed.
(2)
(a)
C:ai,n s e l e c t i o n and f i l t e r d e s i g n f a r gyro
c o n t r o l a t t h e 140-second time p o i n t and f o r
aft-mounted accelerometer c o n t r o l a t t h e
68-second and 80-second time p o i n t s .
(b)
S t a b i l i t y of the upper bending modes v e r i f i e d
f o r t h e s e c a s e s , and a frequency r e s p o n s e
a n a l y s i s completed f o r a l l c a s e s of gyro
c a n t r o l and f o r t h e 60- and 80 second time
p o i n t s wi.th t h e aft-mounted a c c e l e r o m e t e r .
(c)
Design of t h e accelerometer f i l t e r and loop
f i l t e r i n i t i a t e d f o r t h e forward-mounted
accelerometer cases.
(d)
Wark conti.nued on s e t t i n g up t h e f l e x i b l e
body t r a n s i e n t response program.
" K t i l i z a t i s n of V e l o c i t y Feedback From P l a t f o n n Mounted Accelerometer for Control of S a t u r n V LOR"
An e f f o r t i s being made t o determine t h e l i m i t a t i o n s
and problems encountered i n u s i n g v e l o c i t y feedback from a platform-mounted
�accelerometer f o r c o n t r o l and load r e d u c t i o n .
The v e l o c i t y feedback
appears o n l y moderately e f f e c t i v e i n reducing bending moments w i t h o u t
a d d i t i o n a l compensation.
An a n a l y s i s of q u a n t i z a t i o n e r r o r s from
sampling has begun.
(3)
Study t o Reduce Bending Moments v i a Control
System Design
The o b j e c t i v e f o r t h i s t a s k i s t o d e s i g n a
c o n t r o l l e r t h a t w i l l minimize t h e i n t e g r a l of l a t e r a l v e l o c i t y r a i s e d
t o an even power p l u s a q u a d r a t i c i n c o n t r o l e f f o r t . The c o n t r o l l e r
has been o b t a i n e d a s a f u n c t i o n of time.
Synthesizing t h e c c n t r o l l e r
a s a f u n c t i o n of s t a t e v a r i a b l e s has c o n t i n u e d , w i t h c r o s s p r o d u c t s
of t h e s t a t e v a r i a b l e s i n c l u d e d , by u s i n g a c u r v e - f i t t i n g procedure.
A memorandum d e s c r i b i n g t h e r e s u l t s t o d a t e i s being w r i t t e n .
(49
S t u d y t o Reduce Wending Moments v i a Control
System Design, Variable C o e f f i c i e n t Case
The o b j e c t i v e o f t h i s strmdy i s t o determine t h e
degree of s u c c e s s which can be s b t a i n e d by using modern c o n t r o l t e c h n i q u e s
t o d e s i g n a c o n t r o l system which w i l l reduce bending moments.
Kalman
f i l t e r t e c h n i q u e s a r e being used t o design a l i n e a r c o n t r o l system w i t h
feedforward and feedback loops.
(5)
Nonlinear Accelerometer f o r Load R e l i e f
The o b j e c t i v e of t h i s t a s k i s t o determine t h e
bending moment r e d u c t i o n o b t a i n a b l e through t h e use of a n o n l i n e a r
element i n t h e accelerometer feedback.
Rigid body t r a j e c t o r y runs
over t h e time of b o o s t e r f l i g h t were made w i t h t h e n o n l i n e a r a c c e l e r o m e t e r
feedback added t o t h e b a s i c a t t i t u d e c o n t r s P L e ~ . The bending moments
o b t a i n e d by a t t i t u d e c o n t r o l o n l y were compared w i t h t h o s e o b t a i n e d by
adding a l i m i t e d accelerometer feedback--the Load r e d u c t i o n was approximately 43 p e r c e n t . A f i n a l r e p o r t i n d r a f t form bas been r e c e i v e d , but
has n o t y e t been reviewed.
(6)
Generati.on o f a Graphical. o r Analytfcal. Formulation
s f Peak Vehicle Responses
The o b j e c t i v e o f t h i s s t u d y i s t o determine a
g e n e r a l method f o r p r e d i c t i n g maximum v e h i c l e r e s p o n s e v a l u e s .
After
reviewing t h e summary o f work t o d a t e , i t was concluded t h a t t h e formulas
f o r computing maximum v a l u e s , a l t h o u g h c o r r e c t , were n o t i n t h e d e s i r e d
form a s a f u n c t i o n s f p h y s i c a l v e h i c l e parameters.
A d d i t i o n a l work w i l l
be n e c e s s a r y t o complete t h i s p r o j e c t .
E v a l u a t i o n of t h e s e n s i t i v i t y s f t h e c o n t r o l law
(7)
t o changes i n t h e wind p r o f i l e and o f t h e weighting terms i n t h e
q u a d r a t i c c r i t e r i o n w i l l be continued.
�(8) The m o d i f i c a t i a n s to t h e B-2 Gape Deck t o i n c l u d e
f i l t e r e q u a t i o n s and s t h e r v a r i a t i o n s needed f o r c c n t r o l s t u d i e s h a s
been p u b l i s h e d i n L2ekbeed d~czament$) TM-5G-30-71,
C.
Dynamics AnaPys%s S r a n c h
1.
Saturn HB
a.
The s l o s h model p a r a m e t e r s for AS-205 have been d e t e r m i n e d
and a p r e l i m i n a r y copy cf t h e r e s u l t s g i v e n t o R-ASTR-P, f u l . f i l P i n g a
s c h e d u l e a g r e e d upon by R-AERO-D an1 R-ASTR-F.
b.
A memsras-ndum has been d i s t r i b u t e d g i v i n g t h e r e s u l t s o f
a bending a n a l y s i s o f AS-205 f i r s t - s t a g e f l i g h t .
A mema p r e s e 9 t f " ~ gt h e r e s u l t s sf a bendixg a n a l y s i s s f t h e
S a t u r n ~ ~ / ~ e a k af dur w
r t % B i g h t s t a g e has E e e ~f s s u e d ,
3.
S a t u r n t'
(1) Tasks t n a s s e s s t h e f i n a l c o n t r n l system d e s i g n f o r
t h e S-EG, S - P I , and S-JV3 s t a g e s of t h e AS-SO1 v e h i c l e have been g i v e n
Eng%ne o u t , d e t a i l wind p r o f i l e s and g u s t p e n e t r a t i o n a r e t o
t o Bseing.
be i n c l u d e d .
( 2 ) A c ~ n p a r i s 2 ncf t h e s t a b i l i t y c h a r a c t e r i s t i c s o f
t h e v a r i o u s proposed c o n t r o l systems f o r t h e AS-501 s p a c e v e h i c l e h a s
been c c n c l u d e d , w i t h a r o u g h d r a f t s f t h e r e p 2 r t a b o u t t w c - t h i r d s
esmp l e t e d
.
(31 A r i g i d bedy t h r e e - d i m c n s i o n a l sirnuPation of t h e
AS-501 s p a c e v e h i c l e u s i r l g t b nonlinear,
~
r 7 t a r y s l c s h mcdel d e v e l o p e d
by D r . Bauer i s be-irlg s e t up on t h e a a n l s g computer.
The e f f e c t o f t h e
n o n l i n e a r s l o s h model
the S a t u r n 19 r e s p c n s e w E l l be s t u d i e d .
~ j n
('1) A bend%.ng arialbysfs S~zmr AS-50.4 was completed and
s e n t t o Bqeing f o r use in c ' n t r ~ Petud%es.
( 2 ) Four e a s e s of t h e r i g i d r e s p o n s e d a t a g e n e r a t e d
f o r s t r u c t u r a l l o a d s f a r AS-504 a r e b e i x g compared.
Tki,,e e a s e s c o n s i d e r e d
are i d e a l e c n t r o E , a t t i t u d e o n l y , and d r i f t minimum c o n t r o l , u s i n g t h e
s y n t h e t i c wind p r o f i l e s t a r t i n g a t t h e grqund and a t some i n i t i a l
altitude.
The v a r i s n s p a r a m e t e r v a r i a t i o n s w i l l be c o n s i d e r e d i n e a c h
c a s e a d t h e RSS bendiqg rnGment determined.
�c,
AS-504,
505 and 506 S l o s h i n g Data
The s l o s h model p a r a m e t e r s (mass, f r e q . ) a r e b e i n g
c a l c u l a t e d f o r AS-504, 505 and 506 v e h i c l e s ,
The a r b i t r a r y shaped
t a n k program i s b e i n g u s e d ,
d.
D e t a i l e d Wind Study
The wind r e s p o n s e s t u d i e s f o r S a t u r n V v e h i c l e u s i n g
t h e h i g h speed a n a l o g a r e p r o g r e s s i n g .
Various c o n t r o l s y s t e m s a r e
being i n v e s t i g a t e d .
The winds e x c e e d i n g t h e 95 p e r c e n t l e v e l o n
bending moment have b e e n i s o l a t e d f o r i d e a l g y r o c o n t r o l law and a r e
( I ) winds
being studied.
Several interesting d e t a i l s are noticed:
w i t h v e r y s m a l l m a g n i t u d e u n t i l around 10 k i l t m e t e r s t h e n p o s s e s s i n g
l a r g e s h e a r s (wind speed change o f 45 m/sec i n 2080 m), b u t o n l y a v e r a g e
peak wind magnitude (50 m / s e c ) , cause exceedances o n t h e bending moment;
( 2 ) nominal wind s h e a r s (wind speed change of 20 m/sec i n 9000 ma w i t h
l a r g e wind magnitude (above 80 rn/see) a l s o c a u s e exceedances.
This is
v e r y i n t e r e s t i n g when compared w i t h t h e two s y n t h e t i c wfnd p r o f i l e s
used, one s t a r t i n g a t t h e ground and t h e o t h e r a t some a l t i t u d e ( 7 km).
The r e s u l t s show a p p r o x i m a t e l y 2 exceedances c u t o f 200 winds i n c a s e
one and a p p r s x h a t e l y 4 o u t o f 200 i n c a s e two.
The 200 winds used a r e
t h e Jimsphere prof i l e s f o r t h i s year.
4.
General
a.
Zero ''GR': The s u p p o r t work f o r t h e low 'kg"'
drop t e s t
is continuing.
Some problems e x p e r i e n c e d i n t h e d r o p mechanism have
been i s o l a t e d .
C o r r e c t i o n s a r e b e i n g made, and t e s t s s h o u l d b e g i n i n
a b o u t 2 weeks.
T e s t s w i l l cover t h e i n i t i a l s l o s h problem p l u s r e s p o n s e
t o impulse under low 'kg'',Tanks w i t h and w i t h o u t b a f f l e s w i l l be t e s t e d .
b.
Damping S t u d i e s : A l l v i b r a t i o n t e s t i n g o f t h e l / 5 s c a l e
A detailed final t e s t
model was completed d u r i n g t h e r e p o r t i n g p e r i o d .
r e p o r t i s being prepared,
c. Data Tape:
The g e n e r a l i z e d aerodynamic f o r c e c o e f f i c i e n t
program u s i n g t h e b e n d i n g mode t a p e a s i n p u t t o t h e d a t a t a p e h a s been
checked o u t , and h a s b e e n t u r n e d o v e r t o th.e p r o d u c t i o n u n i t i n t h e
Comp Lab.
d.
C o n t r o l Gains w i t h F i l t e r s : A p r o c e d u r e f o r c a l c u l a t i n g
t h e c o n t r o l g a i n s w i t h f i l t e r s f o r a r i g i d v e h i c l e h a s been c o m p l e t e d ,
This r e p o r t shows t h e e f f e c t i n t h e
and a r e p o r t i s b e i n g p r e p a r e d ,
c o n t r o l g a i n s o f v a r y i n g t h e l o c a t i o n of t h e a c c e l e r o m e t e r , t h e damping,
a n d t h e c o n t r o l f r e q u e n c y f o r t h e c a s e w i t h o u t f i l t e r s and u s i n g v a r i o u s
f i l t e r configurations.
Some g r a p h s a r e a l s o i n c l u d e d which show how t h e
c o n t r o l g a i n s v a r y w i t h time. .
�hbrk i s proceeding i n a s t u d y t o c a l c u l a t e t h e c o n t r o l
g a i n s w i t h f i l t e r s t h a t i n c l u d e s t h e bending v i b r a t i o n of t h e v e h i c l e . .
Four modes s f v i b r a t i o n a r e included i n t h e a n a l y s i s ; t h e s e e q u a t i o n s
of motion a r e now being solved,
e.
Progress Development (5-D Hybrid Simulat i o n ) : Development
of e q u a t i o n s f o r a h y b r i d computer c o n t r o l t r a j e c t o r y s i m u l a t i o n i n c l u d i n g
5 r i g i d body degrees o f freedom and 4 e l a s t i c body modes i n each of p i t c h
P r o g r a m i n g of t h e e q u a t i o n s w i l l
and yaw p l a n e s 1 s n e a r completion.
begin soon.
f.
Comparison of Bending Frequencies from t h e Dynamic
Test t o F l i g h t : An i n t e r n a l n o t e was published showing t h e cause of
frequency d i f f e r e n c e between c a l c u l a t e d normal modes and measured
f l i g h t frequenc ies.
g. Gust P e n e t r a t i o n : A s i m p l i f i e d e l a s t i c body r e s p o n s e
program, which c o n s i d e r s t h e e f f e c t s of g u s t p e n e t r a t i o n i n both r i g i d
body and e l a s t i e body r e s p o n s e s , i s being checked o u t .
The deck should
be i n p r o d u c t i ~ nby next month.
5.
Contractors
a.
Boeing
A r e p o r t of t h e work done on load r e l i e f schemes f o r
Saturn V v e h i c l e s was r e c e i v e d t h i s week. A f t e r t h i s work i s reviewed,
a r e p o r t w i l l be d i s t r i b u t e d .
Recent s t u d i e s showed a p o s s i b l e i n s t a b i l i t y i n t h e S-I1
and S-IT5 hydrogen t a n k s u s i n g the s l o s h damping p u b l i s h e d i n R-AERO-DDThe problem i s b e i n g a s s e s s e d by , f i r s t , r e e v a l u a t i n g t h e damping
20-65.
v a l u e s p u b l i s h e d i n DD-20-65 and, second, conducting response and
s t a b i l i t y s t u d i e s t o determine .the e x t e n t of t h e problem.
The problem
does n o t now seem a s s e v e r e a s f i r s t a n t i c i p a t e d and probably w i l l not
require redesign of baffles.
b,
General E l e c t r i c
The six-degrees-of-freedom d i g i t a l c o n t r o l t r a j e c t o r y
s i m u l a t i o n program i n c l u d i n g n o n i d e a l c o n t r o l system under development
has now g e n e r a t e d a nominal t r a j e c t o r y .
This f i r s t phase of t h e development i s being documented, and minor m o d i f i c a t i o n s a r e being made.
c.
North American
Dynamic t e s t i n g o f AS-501 ( c o n f i g u r a t i o n 111) has been
completed.
S t r u c t u r a l f a i l u r e occurred i n t h e i n t e r f a c e between t h e
s e r v i c e module and command module. The cause and time of f a i l u r e a r e
being i n v e s t i g a t e d .
�d.
Northrop
Work i s c o n t i n u i n g on t h e f i l t e r s y n t h e s i s problem.
A study i s being made t o determine u s a b l e f i l t e r s f o r S a t u r n 501 u s i n g
p o s i t i o n and r a t e gyros.
The i n i t i a l study t o determine requirements
The f i r s t r u n s t o g e t t h e
and t h e v e r i f i c a t i o n w i l l be done in-house.
requirements have j u s t been completed.
(1) During t h e r e p o r t p e r i o d , a computer program was
w r i t t e n which computes the n a t u r a l f r e q u e n c i e s o f a space v e h i c l e
This program i s now being checked
undergoing nonplanar o s c i l l a t i o n s .
o u t on two t e s t problems where s o l u t i o n s a r e known.
( 2 ) A procedure for o b t a i n i n g t h e r o o t s of n o n l i n e a r
a l g e b r a i c e q u a t i o n s i s b e i n g developed. A program t h a t works w e l l has
been checked o u t , and i s being documented.
( 3 ) Data a n a l y s e s d u r i n g t h i s p e r i o d included t h e
r e d u c t i o n o f v i b r a t i o n decay r e c o r d f o r each mode and f u e l c o n d i t i o n s
from s e v e r a l f o r c i n g a m p l i t u d e s , t h e c a l c u l a t i o n of damping from decay
r e c o r d s , frequency s h i f t s due t o added w e i g h t , and t h e a c c u r a t e p l o t t i n g
of v i b r a t i o n mode shapes,
(4) An approach t o i n c o r p o r a t e s t r u c t u r a l damping i n
a mathematical model of space v e h i c l e s has been e s t a b l i s h e d .
(5) The e q u a t i o n s governing t h e v i b r a t o r y motion of
t h e e l a s t i c tank and t h e f l u i d contained i n t h e tank were d e r i v e d .
Work i s b e i n g done t o s o l v e t h e s e e q u a t i o n s by expanding t h e s h e l l
displacement components and t h e f l u i d p o t e n t i a l i n a s e r i e s form.
f.
Hayes
Nonlinear s t r u c t u r a l feedback i n b o o s t e r c o n t r o l .
The
number o f approximate techniques being i n v e s t i g a t e d f a r p o s s i b l e use i n
t h e " a n a l y t i c a l model'' has been i n c r e a s e d t o f o u r d u r i n g t h i s r e p o r t
period.
These approximate techniques have been c a t e g o r i z e d a s f o l l o w s :
( I ) F i n i t e d i f f e r e n c e e q u a t i o n s der ived from t h e p a r t i a l
d i f f e r e n t i a l e q u a t i o n of beam l a t e r a l v i b r a t i o n .
( 2 ) F i n i t e difference d i f f e r e n t i a l derived d i r e c t l y
from v a r i o u s lumped parameter models of a continuous beam.
( 3 ) D i f f e r e n t i a l . e q u a t i o n s d e r i v e d from t h e p a r t i a l
d i f f e r e n t i a l e q u a t i o n of beam v i b r a t i o n s by u s i n g G a l e r k i n ' s Method
(modal t y p e s o l u t i o n ) .
�( 4 ) F i n i t e d i f f e r e n c e d i f f e r e n t i a l equations obtained
from e i t h e r a p a r t i a l d i f f e r e n t i a l e q u a t i o n o r a lumped parameter model
by u s i n g d i f f e r e n c e approximaticns t o d e r i v a t i v e s based on e i t h e r
Chrysler o r F o u r i e r s e r i e s approximation of t h e d e f l e c t i o n curve.
Work i s i n p r o g r e s s on a l l four c a t e g o r i e s .
D.
Advanced P r o j e c t s S t u d y Branch
1.
S-HVB Workshop
P r e l i m i n a r y payload and l i f e t i m e spectrums have been
generated f o r t h e S-H'~Bworkshop concept.
P r e s e n t l y , t h e primary
m i s s i o n i s t h e kh-day d i r e c t i n j e c t i o n .
Secondary m i s s i o n s a r e t h e
45-day workshop and the a r t i f i c i a l g r a v i t y experiment. P r e l i m i n a r y
c o n t r o l s t u d i e s an t h e a r t f f f c i a l
experiment have been c o o r d i n a t e d
w i t h R-AEWB-PO and R-ASTR-VD.
S t u d i e s have been i n i t i a t e d i n R-ASTR and R-P&VE, a t t h e
r e q u e s t 0 % R-AERO, t o i n v e s t i g a t e the removal ?r swing-back of LEM
shroud p a n e l s .
Docking problems, e ~ m u xcfa t i o n s and t o r q u i n g c o n t r o l
w i l l be s t u d i e d .
2.
Voyager
Performance has been analyzed i n support of t h e Voyager
progect f o r t h r e e v e h i c l e c o n f i g u r a t i o n s :
t h e Saturn V, t h e S a t u r n IB/'Q"
s t a g e c o n f i g u r a t i o n , and t h e S a t u r n ~ ~ / ~ e l t a u Ar .memorandum c o n t a i n i n g
the r e s u l t s wi13 be i s s u e d . A d d i t i o n a l c c n f i g u r a t i o n work i s being done
to i s o l a t e a v e h i c l e which w i l l y i e l d 25,008 I b s n e t payload a t Cg = 25.
This c o n f i g u r a t i o n would be a S a t u r n IB backup t o t h e S a t u r n V Voyager.
An ApoPEo a p p l i c a t i o n a n a l y s i s i s being conducted t o f i n d
an a c c e p t a b l e minimum m o d i f i c a t i o n m i s s i o n p r o f i l e f o r t h e synchronous
A t p r e s e n t i t appears t h a t t h e 3-burn S-IVB
a l t i t u d e o r b i t mission.
p r o f i l e i s o u t because of t h e e x t e n s i v e S-HW m o d i f i c a t i o n .
The two-stage
Saturn V t o t h e 100 nm parking o r b i t w i t h t h e S-BW i g n i t e d t w i c e , once
i n t h e p a r k i n g o r b i t and once a t synchronous apogee, may be o u t because
of the p r e s s u r i z a t i o n problem.
It appears t h a t a new s k i n p a n e l w i t h
helium b o t t l e hangers may have t o be i n s t a l l e d ; t h i s would n o t be a l l o w a b l e
f o r t h e e a r l y a l t e r n a t e m i s s i o n concept. The p r e s e n t a n a l y s i s i s concerned
w i t h f i n d i n g a p r o f f l e t h a t w i l l f a l l w i t h i n the S-ICVB ApoPlo p r o p e l l a n t
budget
.
4.
Manned Mars and Venus Flyby Study
A r e p r e s e n t a t i v e Venus f l y b y t r a j e c t o r y f o r t h e 1975
c o n j u n c t i o n has been computed and i s b e i n g documented.
�Work s t a t e m e n t s f o r t h e $600,000 f l y b y s t u d i e s all.otment
have been forwarded t o NASA Headquarters.
It i s a n t i c i p a t e d t h a t t h e
t o t a l sum w i l l be d i v i d e d i n t o t h r e e a r e a s when RFP'S a r e i s s u e d .
R-AERO-DP was r e p r e s e n t e d a t a s t u d y review concerning h i g h
speed e a r t h e n t r y h e l d a t Ames Research Center on November 16. The review
was conducted by Lockheed, Sunnyvale, who had been awarded t h e c o n t r a c t
by OART-MAD.
En subsequent d i s c u s s i o n s both OAR% and Lockheed i n d i c a t e d
t h a t t h e Apollo Command Module could be used f o r e n t r y speeds up t o
50,000 f t l s e c when t h e a p p r o p r i a t e amount s f h e a t s h i e l d i n g m a t e r i a l i s
added.
Lockheed, under c o n t r a c t t o MSC, i s concluding a s t u d y u s i n g t h e
Apollo CN f o r h y p e r b o l i c e n t r y .
5.
PRESTO
Lockheed, Paho A l t o , has a c o n t r a c t w i t h Langley Research
Center t o make c e r t a i n m o d i f i c a t i o n s and e x t e n s i o n s t o t h e t r a j e c t o r y
program PRESTO.
Langhey w i l l be c o n t a c t e d t o o b t a i n a c l e a r e r p i c t u r e
of t h e s i t u a t i o n .
6.
C o n t r a c t o r Support
a.
Northrop
(1) Convergence:
The convergence r o u t i n e has e s s e n t i a l l y
been developed; t h e major p a r t of r e c e n t e f f o r t s i n t h i s a r e a has been
d i v e r t e d t o a n a l y s i s of t h e 2-stage COV problem.
Recent e f f o r t s have
been d i r e c t e d toward f o r m u l a t i n g the problem i n a manner which, f o l l o w i n g
a Denbow-type t r a n s f o r m a t i o n , y i e l d s an e q u i v a l e n t probl.em i n t h e c l a s s
of problems f o r which t h e maximum p r i n c i . p l e i s a p p l i c a b l e .
( 2 ) Reentry: Phase 1 of t h e i n v e s t i g a t i o n s f r e e n t r y
t r a j e c t o r i e s has j u s t been completed, t h e r e s u l t s of which a r e documented
i n Technical Memo No. 138.
It has been concluded from Phase I t h a t a
b u i l d i n g block approach t o t h e r e e n t r y problem should. be undertaken;
t h i s i s now underway.
(3) Low Thrust:
Phase I of t h i s t a s k i s being documented.
As a r e s u l t of Phase I, i t has been concluded t h a t w h i l e t h e h e l i o c e n t r i c
phase of low t h r u s t has been g i v e n c o n s i d e r a b l e a t t e n t i o n , t h e e a r t h
escape and c a p t u r e phases have not.
The problem of escape under l o w - t h r u s t
a c c e l e r a t i o n w i l l now be s t u d i e d i n d e t a i l .
(4) Location o f Lander Probes f o r Maximum Comrnunicati.on
Time: T h i s t a s k should be completed d u r i n g t h e coming month.
R e s u l t s of
launching l a n d e r probes t o Mars from manned f l y b y v e h i c l e s i n d i c a t e t h e
following:
( a ) S e p a r a t i o n from f l y b y v e h i c l e must t a k e p l a c e a t extreme
distances.
( b ) Guidance requi.rements f o r e n t e r i n g M a r t i a n atmosphere
�a r e extremely sensiti-ve.
(c)
Very l a r g e r e t r o A V ' S a r e n e c e s s a r y .
( d ) Communication time between l a n d e r probe and f l y b y v e h i c l e i s v e r y
limited a t best.
These r e s a l t s were i n s t r u m e n t a l in e l i m i n a t i n g from
MSFC c o n s i d e r a t i o n t h e Eawnching @I l a n d e r p r o b e s from t h e f l y b y v e h i c l e s
f o r t h e in-house f l y b y s t u d y .
(5) N s r t h r o p i s making a p a r a m e t r i c a n a l y s i s o f g e o c e n t r i c
c o a s t i n g o r b i t c h a r a c t e r i s t i c s and launch r e q u i r e m e n t s f o r t h e proposed
Voyager m b s s f ~ n s . Thfe t a s k is i n s u p p o r t o f JPL'S r e q u e s t f o r S a t u r n V
l a u n c h vehFePes f o r t h e Vcyager s p a c e c r a f t , R e s u l t s a r e e x p e c t e d i n
t h r e e weeks.
Dnrbng October v e r y l i t t l e work was done on t h e Phase H I
add-on e o n t r a c t b e c a u s e of : t h e r e o m i t m e n t ~o f t h e o p e r a t i n g p e r s o n n e l .
A g r e a t deal ~ ) pf r L n g r e s swas -nade, however, toward f i n d i n g a t y p i c a l
engle-af-att a c k p r @ ,if i e P ~ l pa.n a b c r t t r a j e c t o r y .
m e t h e o r y t h a t 1 s borne c u t by some n u m e r i c a l
i s t h a t e x t e r n s 1 a b o r t t r a j e c t 3 r l e s ( t ? the terninan. c c n d i t i o n s
~ i c c wirh
~r
bank a . ~ g le s~s e n f , l a " r y z e r o .
If i t were n o t for t h e
e f f e c t s o f e a r t h r c l t a t i o n , t h e bdnk a n g l e would be e x a c t l y z e r o
aborts.
results
used)
minor
on t h e
T%-e r e s u l t s of t h e t a s k t a i n v e s t i g a t e powered f l y b y
of Mars d u r i n g t h e 1918 a p p c s i t i o n have been documented i n Lockheed
Technical Memo 54-30-69.
"Hke p a r a m e t r i c s t u d y o f v a r i o u s o r b i t a l c o n d i t i o n s
about Mars i s p r e e e e d f n g on s c h e d u l e and monographs p o r t r a y i n g t h e
r e s u l t s a r e being constructed.
L h e stud3 of m f d ~ o ~ r sr e q u i r e m e n t s f o r Mars and Venus
f l y b y and Venus s w i r g b y qEssE2n.s i s j u s t g e t t i n g underway.
1% w i l l
c c n s e r n i t s e l f w i t k t h e a n a l y s i s of t o t a l m i d e c u r s e ,5V r e q u i r e m e n t s
and t h e Fncrementing o f t h i s t o t a l for t h e above t y p e s o f m i s s i o n s .
W t h owboard g u i d a n c e and ground t r a c k i n g w i l l be c o n s i d e r e d .
?.I
1. A m e e t i n g o f cbe PEWC 0 ~ 7Sakuri-i 13 f l i g h t e v a l u a t i o n
t t r % o n t a t i n na d p l a n n i n g h e l d o n b1:vember 39, 1965, a t MSFC i n c l u d e d
p r e s e n t a t i : o s by CCSD, 3AC, Rocketdyne, and ISN o n p r e p a r a t i o n f o r t h e
�f u t u r e S a t u r n IB f l i g h t e v a l u a t i o n e f f o r t .
A l s o , MSFG r e p r e s e n t a t i v e s
p r e s e n t e d t h e f u n c t i o n s and a c t i v i t i e s o f t h e FEWG d u r i n g t h e S a t u r n 16B
program.
2.
A f l i g h t t e s t e v a l u a t i o n p l a n f o r S a t u r n I B haunch v e h i c l e s
AS-201 t h r o u g h AS-204 h a s been d i s t r i b u t e d t o a 1 1 members o f t h e F l i g h t
E v a l u a t i o n Working Group.
T h i s p l a n d e s c r i b e s f u n c t i o n s and r e s p o n s i b i l i t i e s assigned t o t h e v a r i o u s elements involved i n t h e evaluation.
P r o c e d u r e s f o r d a t a h a n d l i n g , a n a l y s i s , and r e p o r t i n g a r e o u t l i n e d i n
detail.
T h i s p l a n w i l l be r e v i s e d a s r e q u i r e d t o r e f l e c t c h a n g e s ,
a d d i t i o n s o r d e l e t i o n s n e c e s s a r y t o encompass t h e e v a l u a t i o n o f AS-201,
AS-202, AS-203 and AS-204.
CCSD w i l l p u b l i s h a s i m i l a r p l a n b e f o r e
f l i g h t t e s t o f AS-20.5.
3. The s e v e n t h m e e t i n g of t h e Plight E v a l u a t i o n P a n e l (FEP)
was h e l d a t Kennedy Space C e n t e r , F l o r i d a , November 9-10, 1965, P l a n s
and s c h e d u l e s fear A S - 2 0 1 / ~ ~ ~ - 0 0f l9i g h t e v a l u a t i o n were reviewed.
P r e s e n t a t i a n s were made on t h e p r e l a u n c h wind m o n i t o r i n g program,
planned AS-201 l a u n c h v e h f c l e and s p a c e c r a f t sequence o f e v e n t s ,
Apollo-Saturn PB p o s t f l i g h t guidance a n a l y s i s t e c h n i q u e s , and s p a c e
v e h i c l e l i f t - o f f and i n f l i g h t w e i g h t e v a l u a t i o n t e c h n i q u e s a n d
accuracies.
R e p o r t s from t h e Data Exchange C o o r d i n a t i o n and P o s t f l i g h t
T r a j e c t o r y Subpanels were h e a r d , a n d a t o u r o f AFETR Cape and KSC
f a c i l i t i e s was made.
The n e x t FEP m e e t i n g i s t e n t a t i v e l y s c h e d u l e d
f o r MSC o n March 1 6 , 1965.
B.
P l i g h t E v a l u a t i o n Branch
1..
Saturn I
The Pegasus o r b i t a l r o l l i n v e s t i g a t i o n was p u b l i s h e d a s
T e c h n i c a l Report ~ R ~ ~ / 2 0 0 8 -e1n ,t i t l e d "Analysis of P e g a s u s Fuel Vent
Impingement. " Work was performed by LMSC, Hunt s v i P l e , under Miss i o n
Support C o n t r a c t NAS8-20082 Appendix C-1, S c h e d u l e Order 5. A n a l y t i c a l l y
determined m o t i o n s a r e i n good agreement w i t h t e l e m e t e r e d r e s u l t s ,
s u p p o r t i n g t h e t h e o r y t h a t t h e r o l l i n g m o t i o n e x p e r i e n c e d by Pegasus
was due t o impingement o f v e n t p r o p e l l a n t s upon t h e extended p a n e l s .
2.
Saturn I B
The l o n g i t u d i n a l t h r u s t s h a p e f o r t h e S-IV s t a g e of Black I1
v e h i c l e s was a d i f f i c u l t p a r a m e t e r t o d e t e r m i n e . Q u i t e o f t e n Douglas
A i r c r a f t Company and P r a t t and Whitney c o u l d n o t a g r e e on t h e t r u e t h r u s t
shape, a l t h o u g h t h e c h a r a c t e r i s t i c s h a p e o f t h e t h r u s t c u r v e was r a t h e r
simple.
The p r e d i c t e d l o n g i t u d i n a l t h r u s t f o r AS-201 S-IVB s t a g e
c o n t a i n s l a r g e o s c i l l a t i o n s which a r e c a u s e d by '%built-in'" m i x t u r e r a t i o
shifts.
There a r e s t r o n g i n d i c a t i o n s t h a t , i f t h e S-HV s t a g e t h r u s t s h a p e
was d i f f i c u l t t o d e t e r m i n e , t h e S-IVB s t a g e s w i l l be c o n s i d e r a b l y more
difficult.
�To o b t a i n a r e l i a b l e s o l u t i o n and t o match t h e observed
t r a j e c t o r y through t h e use of t h e F l i g h t Simulation Method, i t i s
necessary t h a t t h e t r u e t h r u s t shape be known.
Therefore, a f e a s i b i l i t y
study i s underway f o r computing t h e t h r u s t shape u s i n g measured l o n g i t u d i n a l a c c e l e r a t i o n , an i n i t i a l mass (which may be i n e r r o r ) , and t h e
flow r a t e (which w i l . 1 have t h e c o r r e c t shape, b u t may have l e v e l s h i f t s ) .
3.
Saturn V
An ana l y s i s performed t o d e t e r m i n e t r a c k i n g requirements
f o r AS-501.
A s i m p l i f i e d method was used t o a s c e r t a i n how many guidance
e r r o r s could be s e p a r a t e d i f t h e d e v i a t i o n ( t r a c k i n g minus t e l e m e t e r e d
guidance) i n v e l o c i t y components amounts t o a p a r t i c u l a r v a l u e a t S-EVL(
c u t a f f.
The f i r s t s t e p was t o compute t h e v a r i o u s i n d i v i d u a l guidance
e r r o r terms n e c e s s a r y tc~account f o r t h e t o t a l d e v i a t i o n a t S-HVB c u t o f f .
A t r a c e was made throughout t h e f l i g h t of t h e s e i n d i v i d u a l e r r o r terms,
The next s t e p was t o d i f f e r e n c e each of t h e t r a c e s w i t h every o t h e r
t r a c e u n t i l a l l csmbfnaticns had been made,
S i x t y - s i x d i f f e r e n c e curves
were e s t a b l i s h e d .
T3 s e p a r a t e o r d i s t i n g u i s h one e r r o r from a n o t h e r , t r a c k i n g
a c c u r a c i e s would have t o be about h a l f a s l a r g e a s t h e d i f f e r e n c e between
any two e r r o r c o n t r i b u t i o n s .
To i l l u s t r a t e t h i s f u r t h e r , i f t r a c k i n g
a c c u r a c i e s o f 2.0 m/s ( i n v e l o c i t y components) a r e a v a i l a b l e , 33 p e r c e n t
of the guidance e r r o r s can be d i s t i n g u i s h e d i f t h e d e v i a t i o n a t S-IVB
c u t o f f i s 10 m/s.
Tf t h e d e v i a t i o n a t S-TVB c u t o f f i s 20 m/s, 64 p e r c e n t
s f t h e e r r o r s can be d i s t i n g u i s h e d .
4.
Contracts
a.
Saturn IB System C o n t r a c t (CCSD, New O r l e a n s )
CCSD i s c o n t i n u i n g t o develop t h e c a p a b i l i t y t o e s t a b l i s h
a postflight trajectory.
They have processed t h e SA-10 t r a c k i n g d a t a
and soon w i l l i s s u e a t r a j e c t o r y r e p o r t t o demonstrate t h e a b i l i t y t o
use t h e s e t r a j e c t o r y programs e f f e c t i v e l y .
It has been decided t h a t
CCSD w i l l assume r e s p o n s f b i l i % y f o r t h e i n t e r m e d i a t e t r a j e c t o r y ( 7 days
a f t e r launch) and t h e f i n a l t r a j e c t o r y (14 days a f t e r launch) beginning
w i t h SA-203.
The r e s p o n s i b i l i t y f o r the 24-hour t r a j e c t o r y w i l l remain
wFth MSPC f o r t h e e n t i r e S a t u r n I B s e r i e s because of d a t a d e l i v e r y
problems.
b.
S a t u r n V Systems C o n t r a c t (The Boeing Company)
The A e r o b a E l i s t i c s Unit of The Boeing Company i s
scheduled t o assume the r e s p o n s i b i l i t y f o r the p o s t f l i g h t t r a j e c t o r y
commencing w i t h AS-585,
Two work assignments were i n i t i a t e d which w i l l
h e l p Eoeing develop t h e c a p a b i l i t y t o e s t a b l i s h a p o s t f l i g h t t r a j e c t o r y .
The f i r s t work assignment (number R - A E R O - ~ ~ 1 e5 n) t i t l e d "Booster Free
�F l i g h t T r a j e c t o r y f s r e q u i r e s Boeing t o develop a computer program which
w i l l be used t o e s t a b l i s h t h e t r a j e c t o r i e s f o r t h e d i s c a r d e d S-IC and
S-I1 s t a g e s . T h i s program w i l l u s e t r a c k i n g d a t a a s i n i t i a l c o n d i t i o n s ,
and w i t h t h e six-degrees-of-freedom e q u a t i o n s i n c o n j u n c t i o n w i t h t h e
A Least
s e p a r a t i o n dynamics, w i l l g e n e r a t e a f r e e f l i g h t t r a j e c t o r y .
squares r o u t i n e w i l l t h e n be used t o c o n s t r a i n t h e f r e e f l i g h t t r a j e c t o r y
t o any t r a c k i n g d a t a t h a t may be a v a i l a b l e .
This work assignment w i l l
r e q u i r e one e n g i n e e r and one p r o g r a m e r u n t i l i t s campletton i n December
1966.
The second work assignment (nunber R-AEWO-FF/G) e n t i t l e d
" P o s t f l i g h t Reference T r a j e c t o r y " r e q u i r e s a'RG t o d e f i n e t h e a n a l y t i c a l
methods and f u n c t i o n a l p r o c e d u r e s necessary t o determine t h e p o s t f l i g h t
r e f e r e n c e t r a j e c t o r y from any on-board measurements and e x t e r n a l t r a c k i n g
d a t a t h a t may be a v a i l a b l e .
The m a ~ o re f f o r t under t h i s work assignment
w i l l be the development o f a program which w i l l . combine t h e t e l e m e t e r e d
guidance d a t a w i t h t h e d a t a from t h e v a r i o u s t r a c k i n g systems.
Also
r e q u i r e d i s t h a t t h e n e c e s s a r y u t i l i t y programs ( i n t e r p o l a t i o n , curve
f i t t i n g , t a p e merge, c o o r d i n a t e t r a n s f o r m a t i o n s , e t c . ) w i l l be a b l e t o
use any combination of d a t a t o a r r i v e a t t h e 24-hour, 7-day, and 14-day
postflight trajectories.
This work assignment w i l l u s e 5 e n g i n e e r s and
2 programmers u n t i l i t s completion i n December 1966.
c.
C o n t r a c t NAS8-20249 (General Dynamics / ~ o n v a i r )
This i s a s t u d y c o n t r a c t t o e v a l u a t e and t r u n c a t e
t r a c k i n g system e r r o r models f o r use i n S a t u r n TB and V p o s t f l i g h t
t r a j e c t o r y d e t e r m i n a t i o n . GD/C had emphasized t h e r e a l - t i m e a s p e c t s
of t h e c o n t r a c t r a t h e r t h a n t h e t r a c k e r e r r o r models.
This misunders t a n d i n g has been c o r r e c t e d and GD/@ personne 1 have r e d i r e c t e d t h e i r
efforts.
Expanded e r r o r models f o r Azusa, GEOTRAC, and t h e r a d a r systems
have been i n c o r p o r a t e d i n t o e x i s t i n g programs.
Cases a r e now being
c a l c u l a t e d t o determine what t r a c k i n g e r r o r s can be n e g l e c t e d because o f
i n s i g n i f i c a n c e and c o r r e l a t i o n . When t h i s i s completed, t h e r e l a t i o n s h i p
between t h e remaini.ng t r a c k e r e r r o r terms and t h e guidance e r r o r model
terms w i l l be s t u d i e d . This c o n t r a c t i s s t i l l about 5 t o 6 weeks behind
schedule b u t should be completed s i n c e a 2-month no-cost e x t e n s i o n has
been m u t u a l l y agreed upon and n e g o t i a t e d .
C.
P l i g h t Mechanics Branch
(1) The range s a f e t y t r a j e c t o r i e s a r e ready t o t r a n s m i t
to KSC and MSC on magnetic t a p e based upon t h e f i n a l o p e r a t i o n a l t r a j e c t o r y .
�( 2 ) The d i s p e r s i o n a n a i y s f s about t h e o p e r a t i o n a l
t r a j e c t o r y (update L), whfch i s about 95 p e r c e n t complete, should be
f i n a l i z e d seon. Also, a number of d i s p e r s i o n s which a r e o u t s i d e t h e
three-sigma t o l e r a n c e s a r e approximately 50 p e r cent complete.
( 3 ) The F l i g h t Mechanical S u m a r y , which i s 25 per c e n t
complete, should be a v a i l a b l e by t h e middle of December.
( 4 ) Data a r e b e i n g compiled E c r u s e i n t h e AS-201
p r e f l i g h t review, whfch w i l l be held on December 1 4 t h and 15th.
(5) Neither a n S-IB/S-I'ZEs t a g e s e p a r a t i o n impingement
n o r a p o s t - s t a g i n g c o n t r o l l a b i l i t y problem e x i s t s f o r a nonmalfunctisning
vehicle.
However, t h e r e %s no S - I B , S-TIQ s t a g e s e p a r a t i o n c a p a b i l i t y
due to r e t r o failures because o f t h e asymmetric plume impingement. A
s i n g l e u l l a g e failure dses not consf i t u t e an S-HC3 p r o p e l kant s e a t i n g
problen.
( 6 A l ~ f t - ~ fa nf a l y s i s cf AS-ZSI shcws that a
nonmalfunctioniqg v e h i c l e w i l l hzve s~ldficfe~~t
clo-aratlce f(-r a l l LC-34
s b r t r u c t i ~ n s . O f the f o l hi:wPng naif unctkc~ns, l ~ F Sc.f h y d r a u l i c power
fane e n g i v e ) , s i n g l e a c t u a t x h a r d o v e r , and s i n g l e c o n t r o l engine
f a i l u r e , t h e most c r i t i c s 1 i s t h e B a t t e r . E(-wever, nominally t h i s
f a i l u r e would not e e n s t i t u t e a col L i s i o n problem a f t e r about 2.5 seconds
o f f l i g h t time.
7
Wind speed l i m i t s f o r t h e AS-281 v e h i c l e have
been determined for t h e p r e d i c t e d maximum d y ~ a m i cp r e s s u r e time p o i n t
( t = '78 seconds).
These l i m i t s a r e p r e s e n t e d a s a f u n c t i o n of azimuth
i n memorandum R-AERO-FM-38-65, d a t e d November 3, 196'5.
A f i r s t - c u t o p e r a t i o n a l t r a j e c t o r y i s now a v a i l a b l e
and t h e p r o f i l e w i l l be documented s h o r t l y . MSG has accepted t h e
t e r m i n a l cLlnditions by phone.
The Aerospace P h y s i c s S e c t i o n , CCSD, i s p r e p a r i n g t h e
range s a f e t y package (Cape t a p e and d a t a r e p o r t ) f o r t h e r e f e r e n c e
trajectory.
CCSD has generated t h e r a l g e s a f e t y package f o r t h e
l a t e s t r e f e r e n c e t r a j e c t o r y . The Cape t a p e has been forwarded t o MSC
and KSC, and t h e range s a f e t y d a t a r e p o r t w i l l be ready by t h e middle
of December 1965.
�A meeting was h e l d a t KSC on November 1 8 t o b r i e f ETR
Range S a f e t y on t h e AS-206 mission. M r . Leonard p r e s e n t e d t h e launch
v e h i c l e f l i g h t p r o f i l e and o t h e r range s a f e t y d a t a . M r , S k s p i n s k i , MSC,
presented t h e f l i g h t p l a n f o r t h e spacecraft.
S u b o r b i t a l a b o r t and
a b o r t - t o - o r b i t p l a n s were d i s c u s s e d .
From l i f t - o f f t o j e t t i s o n o f t h e
Launch Escape System, t h e a b o r t s a r e performed by t h e EES, r e s u l t i n g
i n impacts i n t h e A t l a n t i c Ocean up t o a range of approximately 350 nm.
From LES j e t t i s o n up t o approximately 581 seconds, t h e launch a b o r t s
c o n s i s t of f r e e - f a l l r e t u r n w i t h t h e e n t r y guidance e s t i v a t e d t o s t e e r
t o a t a r g e t a r e a near t h e Canary I s l a n d s , which a r e approximately 3200 nm
downrange; from 581 seconds up t o i n s e r t i o n , t h e h a l f - L i f t impact p o i n t
i s beyond t h e 3200 nm t a r g e t .
The Apollo Guidance Computer, i n t h e event
of a b o r t i n t h i s r e g i o n , w i l l command a guided r e t r o g r a d e s e r v i c e
p r o p u l s i o n system burn and a c o n t r o l l e d e n t r y t o l a n d a t t h i s t a r g e t .
Amanual procedure i s used f o r r e c o v e r y a r e a c o n t r o l i n t h e e v e n t of a
guidance and n a v i g a t i o n f a i l u r e .
me impacts f r o a a l l s u b o r b i t a l a b o r t s
w i l l be i n t h e A t l a n t i c Ocean.
Frlm a p p r ~ u i r n a t e l y571 seconds up t o
insertion, the capability exists t o safely abort t o o r b i t , using the
s e r v i c e p r o p u l s i o n system.
Unless there i s a s p a c e c r a f t m a l f u n c t i o n
o r a crew s a f e t y problem r e q u i r i n g immediate r e t u r n , t h e a b o r t - t o - o r b i t
procedure i s t h e primary a b o r t made i n t h i s r e g i o n of t h e launch
trajectory,
M r . Leonard made a proposal t o Range S a f e t y , ETR, t o
change t h e format of t h e range s a f e t y d a t a r e p o r t s which a r e provided
f o r each v e h i c l e .
The proposed change would reduce t h e s i z e o f t h e
r e p o r t s , t h u s r e d u c i n g t h e c o s t . M r . Cobb and Lt. P e r r i n g , ETR, c a l l e d
November 30 t o i n d i c a t e t h e i r i n t e r e s t i n t h e proposal.
They p l a n t o
come t o MSFC on December 1 3 t o d i s c u s s t h e d e t a i l s .
I n the p a s t , i t has been v e r y d f f f i . c u 1 . t to g e t any
I t i s hoped t h a t t h e i r decisi,on t o
i n f o r m a t i o n from Range Safety.
v i s i t h e r e w i l l l e a d t o a b e t t e r understanding and b e t t e r r e l a t i o n s
i n the future.
2.
General.
A memorandum p r e s e n t i n g t h e r e s u l t s s f the t h r u s t o s c i l l a t i o n
study w i l l be published soon.
D.
Operations S t u d i e s Branch
1.
Saturn 1
A c l o s e watch o n p r o b a b l e decay d a t a f o r SA-5, 8 , 9 , and 10
i s being maintained.
We w i l l r e c e i v e r e a l - t i m e t r a c k i n g d a t a from Goddard
on SA-5, which has a nominal decay d a t e of February 1, 1966.
�2.
S a t u r n HB
a. Tracking coverage on AS-281 has been compiled f o r t h e
o p e r a t ionah t r a j e c t o r y r e p o r t .
This s s ~ t r i b u t i o nincluded t h e e l e v a t i o n
h i s t o r i e s of t h e t r a c k i n g and t e l e m e t r y network t o be c a l l e d up on AS-201,
a s we19 a s t h e s l a n t range h i s t o r i e s of t h e v e h i c l e through S-IVB impact.
b.
The R-AERB-EO c o n t r i b u t i o n t o the AS-204 r e f e r e n c e
This a n a l y s i s included e l e v a t i o n and
t r a j e c t o r y was s e n t t o R-AERB-DA.
azimuth h i s t o r i e s o f t h e t r a c k i n g and t e l e m e t r y network a n t i c i p a t e d
f o r AS-204.
c.
The sequencing of a c q u i s i t i o n and l o s s times f o r t h e
SA-203 o r b i t a l t r a j e c t s r y have been determined.
The sequencing times
i n c l u d e t h e p e r t u r b a t i o n o f ~ r b i t a lv e n t i n g . A j o i n t R-AEIPB-DA and
R-AERO-PO memorandum wf ll be pub li shed.
d.
The s e q u e ~ c f n gt i n e s of t r a c k i n g s t % t i o n a c q u i s i t i o n
and l o s s due t o v e l o c i t y d e f i c i t s on SA-28% have been published.
This
memo p r e s e n t e d the d e v i a t i o n s i n s t a t i o n a c q u i s i t i o n times f o r a 5'
e l e v a t i o n due to v e l o c i t y d e f i c i t s frnllm 5 t o 24 m/sec,
3.
Saturn V
a. Tracking and t e l e m e t r y coverage has been g e n e r a t e d
f o r AS-581 f o r t h e Qoint r e f e r e n c e t r a j e c t o r y . The d a t a w i l l be
included i n t h e J o i n t Reference T r a j e c t o r y Report.
The t r a c k i n g a n a l y s i s which has been completed f o r
b.
AS-582 f o r the L/V p r e l i m i n a r y r e f e r e n c e t r a j e c t o r y w i l l be included
i n the L / V p r e l i m i n a r y r e f e r e n c e t r a j e c t o r y r e p o r t .
c,
Some work has been done o n t h e S a t u r n V d i r e c t a s c e n t
mode t o determine t h e expected p o s i t i o n and v e l e c i t y e r r o r s from t r a c k i n g
d a t a a v a i l a b l e from Saturn V ground network.
d. Runs were made o n t h e o r b i t a l c o r r e c t i o n program t o
p r e d i c t t h e a c c u r a c y w i t h which we c a n determine i n s e r t i o n elements
f o r AS-581.
TWJ e a s e s were c o n s i d e r e d (5 i t e r a t i o n s each):
The f i r s t
used d a t a o n l y throlugh t h e f i r s t p a s s of the Carnarvon t r a c k i n g s t a t i o n ;
t h e second c a s e used d a t a from a l l s t a t i o n s viewing t h e v e h i c l e d u r i n g
the e n t i r e f i r s t o r b i t .
S t a t i o n s used were a s follows:
1 s t case
----
.=
Bermuda
I n s e r t i o n Ship
Canary I s land
Carnarvon
2nd Case
A11 f i r s t c a s e s t a t i o n s
White Sands
M ELA
Grand Bahama I s l a n d
Bermuda (second p a s s )
�Data f o r a l l t h e s e s t a t i o n s were generated from nominal i n s e r t i o n
c o n d i t i o n s , which were p e r t u r b e d and used a s t h e i n i t i a l e s t i m a t e .
A f t e r 5 i t e r a t i o n s , r e s i d u a l s were a s follows:
I s t Case
Range
AZ
EL
4.
2nd
Case
-
12m
.02"
.02"
General.
a.
O r b i t a l Decay
A memorandum was s e n t t o R-AERO-DA documenting t h e
suggested o r b i t a l decay parameters f o r S4-203 and AS-503 t r a j e c t o r i e s .
Included i n t h i s rnemilra~dumwere d a t a f o r t b e cerresponding drag
c o e f f i c i e n t , drag a r e a products f o r v a r i o u s v e h i c l e a t t i t u d e s , and t h e
expected a t m s p h e r i e d e n s i t i e s f o r lau~chd a t e s of J u l y 1, 1966, and
June 15, 1967. The d e n s i t i e s were p r e s e n t e d a s t h e r a t f o s f a timea l t i t u d e dependent a.tmospheris d e n s i t y t o t h e 1962 US Standard atmospheric
density.
b.
AAP
(1) A r e q u e s t has been r e c e i v e d from R-AERO-DP t o
compute t h e aerodynamic t o r q u e s f o r some p o s s i b l e AS-211 o r b i t a l
c o n f i g u r a t i o n s . M r . E a l l a n c e , R-AERO-AM, has c a l c u l a t e d C p and C N a s
a f u n c t i o n of a n g l e of a t t a c k . R e s u l t s of t h e s e t o r q u e s w i l l be used
by R-ASTR t o c a l c u l a t e c o n t r o l f o r c e s f o r AAP m i s s i o n s . P r e l i m i n a r y
d a t a were t r a n s m i t t e d t o R-AERO-DP; a memorandum i s being compiled t o
document t h e s e d a t a .
( 2 ) L i f e t i m e s t u d i e s made f o r t h r e e s p e c i a l c o n f i g u r a t i o n s
of t h e Manned O r b i t a l Laboratory a r e being documented.
( 3 ) The v a r i a t i o n s i n o r b i t a l l i f e t i m e af t h e manned
o r b i t a l workshop due t o t h e e x p u l s i o n of t h e LB, from t h e o r b i t i n g
S-IVB a r e being s t u d i e d and w i l l soon be documented.
(4)
Plans a r e being made t o p r e s e n t t h e work R-AERO-FO
has done on l i f e t i m e s and aerodynamic t o r q u e s f o r t h e manned o r b i t a l
workshop t o t h e Manned O r b i t a l Workshop Working Group. The t e n t a t i v e
agenda i s a s follows:
O r b i t a l l i f e t i m e f o r proposed manned
o r b i t a l l a b o r a t o r y con£ i g u r a t i o n
E. D. Fleischman
(15 minutes)
�P e r t u r b a t i o n on o r b i t s acd o r b i t a l
l i f e t i m e due t o e x p u l s i o n of EB,
Aerodyrimic t o r q u e s f o r m a n ~ e d
o r b i t a l workshop eonf i g u r a t i o n
Lee L7arnado
Tracki2g coverage f o r manned o r b i t a l
workshop m f s s i o ~ ,
J e a n SheBton'
(15 m i n u t e s )
QEO m i n u t e s )
Baser, E t h e l a n d Larry D. MulEi.-n_s,"Lac-ch WL~do~,rhrsf c r Two Types s f
O r b i t s Synchrorous w i t h t h e Ex-ar P?rf>a?id,FWASA'IN X-53354,
November 1 , 1965, iZ1lclassified.
Dalton, C. C.,
" ~ t a t i s t i c s k A ~ a L j is,
s
Phatogrephfa Meteor Data,
P a r t 11: ~ e r n i a z i ' sEumi:-ocs E f f l c l e ~ c yand Supplemented n i p p l e
Weight: s g , l o USA p"I X-53360, kbvember IS, 1965, V~e1ass-i.f
ied.
Dickey, Lyle R., "Linear Guidance Techniques, "'ASA
November 30, 3.965, t 7 ~ c l a s s i f f e d .
TM X-53362,
Haws, J. L., AQFeasibkEity
Study of a 1.3 Per Cent Groul~dWind
Model Which GobEd Be Tested i n a Proposed P u l l - S c a l e R e y ~ o l d s
Nmbers T e s t F a c i l i t y , Aero-As t r s d y a m i c s IyqternaE Note {I 26-65>
November 8 , 1455, Lr?.classif i e d .
MeMair, A. R. z.qd E. P. Woykin, " ~ a r t hO r b i t a l L i f e t i m e P r e d i c t i o n
I 2i tcesr n a l Note
27-65,
Model and Program," A e r ~ - A s t r ~ d j ~ ~ m
November 18, 1965, Vficlassfffed.
M d 1 6 3 s , L a r r y D. , ouLaa-r.ckP r o b a b i l t t y A n a l y s i s , " Aero-As t r o d y ~ a m i c s
I n t e r r a 1 Note 4 28-65, N~vember 18, 1965, Unclassified.
L e s t e r , R. C. and E. H. Bauer, " P r o b a b i l t t y of t h e S-IV-B/IU Lunar
Tvpact Due t o C ~ i d a c c eE r r o r s a t t h e Trarilslunar I ? j e c t i o n a s a
Furretio-h of Deviatiozls from I n j e c t i o n F a c i 9 h t y , " Aero-Astrodynmics
I n t e r m 1 Note +, 29-65, November 24, 1965, C o n f b d e ~ ~ t i a l .
Jump, Roger A, and V. K. Henssn, " Z ~ - F S i g h t V e ~ t f n gof Launch Vehicle
Compartments, " Aero-As trsdynamics I n t e r n a l h o t e {, 20-65, November
2 9 , 1965, i h c l a s s i f i e d ,
�9.
Jones, Jesse H., "Request for Support in Acquiring Meteorological
Data," Office Memo R-AERO-AU-65-60, November 18, 1965, Unclassified.
10,
Stahle, C. V., "An Experimental Investigation of Wind Induced
Oscillation Effects on Cylinders in Two-Dimensional Flow," ER-14019,
October 26, 1965, Unclassified.
APPROVAL
E. D. Geissler
Director, Aero-Astrodynamics Laboratory
Aero-Astrodynamics Laboratory
DISTRIBUTION
R-AERO-DIR
Dr. Geissler
Mr. Jean
R-AERO-P
(8)
R-DIR
-Dr, McCall
PA0
Mr, Kurtz
MS-H
R-AERO-R
Mr. Bulter (4)
Mrs. Hightower
Mrs. Jerrell
R-AERO-D
(16)
R-AERO-A
(20)
R-AERO-G
(5)
R-AERO-T
Mr.
Mr.
Mr.
Dr.
Dr.
Mr.
Mr.
Mr.
Dr.
Murphree
Reed
Cummings
Heybey
Sperling
Dickey
Jandebeur
Lavender
Liu
(3)
�
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Saturn V Collection
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000044
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: December 13, 1965."
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George C. Marshall Space Flight Center
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1965-12-13
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1960-1969
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Saturn Project (U.S.)
NASA space programs
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Progress reports
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Saturn V Collection
Box 15, Folder 41
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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Text
AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
J u n e - J u l y 1967
INDEX
Page
.
.........................
I1.
ADVANCED STUDIES OFFICE ................................
111.
AEROPWSICS DIVISION ...................................
A . F l u i d Mechanics Research. O f f i c e ....................
B . Mechanical Design O f f i c e ...........................
C . Aerodynamic Design Branch ..........................
D . E x p e r i m e n t a l Aerophysics Branch ....................
I
TECHNICAL AND SCIENTIFIC STAFF
E
F
.
.
.
.........................
.......................
Thermal Environment Branch
Unsteady Aerodynamics Branch
.........................
......................
...........................
.....................
..................
v.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION .............
A . O p t i m i z a t i o n Theory Branch .........................
B . Astrodynamics Branch ...............................
C . Guidance Theory Branch .............................
V I.
DYNAMICS AND FLIGHT MECHANICS DIVISION .................
A . M u l t i - P r o j e c t s .....................................
B . S a t u r n V ...........................................
C . S a t u r n IB ..........................................
D . AAP ................................................
E . Other P r o j e c t s .....................................
V I I.
FLIGHT TEST ANALYSIS DIVISION ..........................
A . S p e c i a l P r o j e c t s O f f i c e ............................
B . F l i g h t Mechanics Branch ............................
C . T r a c k i n g and O r b i t a l A n a l y s i s Branch ...............
D . F l i g h t E v a l u a t i o n Branch ...........................
V I I I . PROJECTS OFFICE ........................................
IV
AEROSPACE ENVIRONMENT DIVISION
A
Atmospheric R e s e a r c h F a c i l i t y
B
Space Environment Branch
C
T e r r e s t r i a l Environment Branch
D
Environmental A p p l i c a t i o n s Branch
.
.
.
.
�AERO-ASTRODYNAlfICS LABORATORY
BIlfONTHLY PROGRESS REPORT
June-July 1967
I.
TECHNICAL AND SCIENTIFIC STAFF
1.
Theory of S e c u l a r P e r t u r b a t i o n s
The most g e n e r a l t h e o r y was developed f o r t h e s e c u l a r p e r t u r b a t i o n s of t h e o r b i t of a s a t e l l i t e due t o t h e o b l a t e n e s s of t h e c e n t r a l
body and due t o t h e g r a v i t a t i o n a l a t t r a c t i o n of a t h i r d p e r t u r b i n g body
under t h e most g e n e r a l assumption f o r t h e o r b i t shapes and i n c l i n a t i o n s
of t h e p e r t u r b e d and t h e p e r t u r b i n g b o d i e s . The c o n s t a n t p a r t of t h e
perturbations i n the radius vector i s a l s o given a s well a s the d i f f e r e n t
d e f i n i t i o n s f o r t h e mean motion and t h e semi-major a x i s , and f i n a l l y ,
~ e p l e r ' st h i r d law i n t h e p e r t u r b e d motion. The problem of why a u t h o r s
have found d i f f e r e n t second-order terms i s a l s o d i s c u s s e d . I t has been
shown t h a t f o r any p l a n e t t h e r e e x i s t s a d i s t a n c e where t h e p e r t u r b a t i o n s
of a s a t e l l i t e due t o a t h i r d p e r t u r b i n g body (sun) overcome t h e o b l a t e ness p e r t u r b a t i o n s due t o t h e p l a n e t . The paper was p r e s e n t e d a t t h e
1967 N a t i o n a l Symposium of t h e American A s t r o n a u t i c a l S o c i e t y i n H u n t s v i l l e ,
Alabama (12 June 1967) under t h e t i t l e "The S e c u l a r P e r t u r b a t i o n s of t h e
O r b i t of a S a t e l l i t e Due t o t h e Oblateness of t h e C e n t r a l Body f o r t h e
2m-th Zonal Harmonics and Due t o t h e G r a v i t a t i o n a l A t t r a c t i o n of a Third
(H. Icrause)
Body
."
2. Research on t h e dynamic problems of two cable-connected s p a c e
s t a t i o n s w h i r l i n g about a n a x i s normal t o t h e i r o r b i t a l p l a n e has been
performed. D i f f e r e n t i a l e q u a t i o n s of v i b r a t i o n of t h e e l a s t i c c a b l e and
t h e a n g u l a r movements of t h e s t a t i o n s have been d e r i v e d . The motions of
t h e s t a t i o n s and v i b r a t i o n s of t h e c a b l e a r e coupled dynamically through
t h e boundary c o n d i t i o n s of t h e c a b l e . This mathematical d i f f i c u l t y i s
r e s o l v e d by u s i n g the concept of c o n c e n t r a t e d , f i c t i t i o u s masses. A
g e n e r a l n t h o r d e r d e t e r m i n a n t a l frequency e q u a t i o n of f r e e v i b r a t i o n s of
t h e system i s o b t a i n e d by using ~ a l e r k i n ' sapproach.
The problem of t h e dynamic responses of t h e system t o e x t e r n a l
a p p l i e d moments remains t o be s o l v e d .
(Liu)
3.
E a r l y E x t r a v e h i c u l a r Engineering A c t i v i t i e s
Attended a p r o g r e s s review a t North American A v i a t i o n , I n c .
(NAA), Downey, C a l i f o r n i a w i t h members of t h e Advanced Systems O f f i c e on
C o n t r a c t NAS8-18128 " E x t r a v e h i c u l a r Engineering A c t i v i t i e s (EVEA) Program
Some d i f f i c u l t i e s
Requirements w i t h Emphasis on E a r l y Experiments (P-105) . ' I
�had been experienced i n having NAA follow t h e c o n t r a c t u a l scope of
work and s u b s e q u e n t l y i s s u e d g u i d e l i n e s and d i r e c t i v e s . During t h e
review d e t a i l e d d i s c u s s ions were held among MSC and MSFC t e c h n i c a l
personnel and NAA i n o r d e r t o o b t a i n u s e f u l end products from t h e s t u d y
c o n t r a c t . The midterm review on t h i s s t u d y i s scheduled f o r MSFC on
August 9 , 1967 and f o r MSC on August 10, 1967.
During t h i s t r i p a v i s i t was made t o General ~ y n a m i c s / ~ o n v a i r ,
San Diego, C a l i f o r n i a t o review t h e r e l a t e d work on C o n t r a c t NAS8-18118
"Large Space S t r u c t u r e s Experiments f o r AAP" and feed r e s u l t s i n t o t h e
NASA.study.
4.
SEPTIM
No f u r t h e r p r o g r e s s has been made toward i n i t i a t i n g work on
t h e ESSA-proposed experiment " S a t e l l i t e E j e c t e d Packages f o r T e r r e s t r i a l
I o n o s p h e r i c Measurements (SEPTIM) . I 1 The reasons a r e (1) u n a v a i l a b i l i t y
of s t u d y f u n d s , ( 2 ) unwillingness of t h e proposer t o d e v o t e more than
10 p e r c e n t of h i s time t o t h e e a r l y s t a g e s of t h i s e f f o r t , and (3)
u n a v a i l a b i l i t y of R-AERO-Y s c i e n t i f i c manpower.
(Nathan)
5.
ODYSSEY
Recent experiment t r a d e s t u d i e s have suggested a package of
f o u r e a r t h o r b i t a l aeronomy experiments which i n c l u d e t h e p a s s i v e
s p h e r e ensemble, t h e p a d d l e w h e e l / d i f f u s e sphere/smooth s p h e r e combinat i o n , t h e d e n s i t o m e t e r and a mass spectrometer.
Reference m i s s i o n
p l a n s ( n o t t o be confused w i t h a c t u a l m i s s i o n which r e q u i r e s a launch
d a t e ) have been o u t l i n e d and p r e l i m i n a r y p r o j e c t d e f i n i t i o n s t u d i e s of
a p o s s i b l e experiment implementation concept have been completed.
Thermal a n a l y s e s have been conducted on t h e p a s s i v e s p h e r e ensemble
and t h e paddlewheel s a t e l l i t e r e s u l t i n g i n temperature time h i s t o r i e s
and h e a t r a t e s f o r s e v e r a l s u r f a c e l o c a t i o n s a t o r b i t a l environments.
Unsteady aerodynamic d e s i g n c r i t e r i a have been g e n e r a t e d r e l a t e d t o a
p o s s i b l e piggyback experiment c a r r i e r onboard a S a t u r n launch v e h i c l e .
A p r e l i m i n a r y NASA Form 1346 has been prepared and i s now being reviewed
" P r e - s e l l i n g " d i s c u s s i o n s were h e l d w i t h
b e f o r e a formal proposal.
M r . Lord and D r . Harvey H a l l , OMSF, MTX. They suggested a more fundamental approach b e taken i n a p r e - s e l l i n g campaign t o i n c l u d e informal
d i s c u s s i o n s w i t h members of OSSA. Consequently, M r . Edgar M. C o r t w r i g h t ,
OSSA Dep. Assoc. Admin., was c o n t a c t e d and arrangements were made f o r
(Few)
d i s c u s s ions w i t h D r . Fellows i n t h e P l a n e t a r y Atmospheres Off i c e .
6. A progrqm was i n i t i a t e d t o t e s t and, i f n e c e s s a r y and f e a s i b l e ,
t o improve on a n e x i s t i n g fundamental e v a l u a t i o n technique f o r c r o s s c o r r e l a t i o n e x p e r i m e n t a t i o n ( D i g i t a l Analysis of Random P r o c e s s e s by
Curve F i t t i n g Piecewise Estimated C o r r e l a t i o n F u n c t i o n s ) . P a s t e x p e r i ence has made. i t c l e a r t h a t c l o s e s u p e r v i s i o n and guidance of t h e
�of t h e c o n t r a c t o r e f f o r t i s c a l l e d f o r i n t h i s v i t a l s e c t o r of t h e
crossed-beam a n a l y s i s . The program i s s t i l l i n i t s f i r s t s t a g e s .
A paper published on mixed r e f l e c t i o n of s u n l i g h t (NASA TM X53617) clcvclops a mctllod f o r computing t h e l i g h t f o r c e a c t i n g on s a t e l l i t e s a s w e l l as t h e torque a s s o c i a t e d w i t h i t , i f p a r t of t h e r e f l e c t i o n
i s s p e c u l a r , p a r t i s d i f f u s e . Energy l o s s e s i n t h e process a r e a l s o
t a k e n i n t o a c c o u n t . (Heybey)
6.
Advanced Launch Vehicle T r a j e c t o r y Research
a.
In-House Research E f f o r t s and Northrop C o n t r a c t S. 0.26
(1)
A i r b r e a t h i n g Propuls i o n Model
The HTO-Airbreather computer model development has cont i n u e d . The s i m u l a t i o n of f l i g h t a t a c o n s t a n t dynamic p r e s s u r e i s
o p e r a t i o n a l . The system of smooth convergence of t h e f l i g h t p a t h d u r i n g
t h e minimum f u e l p r o f i l e (MFP) f l i g h t phase and t h e c o n s t a n t q f l i g h t
p a t h has a l s o been s u c c e s s f u l l y developed.
During t h e second r e p o r t p e r i o d , t h e a i r b r e a t h e r model
has been extended through t h e c o n s t a n t engine d u c t p r e s s u r e f l c g h t mode.
To m a i n t a i n t h e d e s i r e d maximum p r e s s u r e , a continuous t r a d e - o f f i n a l t i tude and v e l o c i t y i s r e q u i r e d .
(2)
Rocket P r o p u l s i o n Model
Equations have been w r i t t e n and a mathematical model
f o r three-dimensional maneuvering f l i g h t , s i m u l a t i n g t h e r e - e n t r y and
f l y b a c k , i n t h e atmosphere, of t h e f i r s t s t a g e of a two-stage advanced
l a u n c h v e h i c l e w i t h r o c k e t p r o p u l s i o n has been c o n s t r u c t e d and t r a n s m i t t e d
t o t h e c o n t r a c t o r f o r i n c l u s i o n i n t h e HTO/VTO models. For t h e c o n t r o l
of t h e r e c o v e r y t r a j e c t o r y , two c o n t r o l v a r i a b l e s , v i z . , a n g l e of a t t a c k
and bank a n g l e , have been chosen, p l u s a number of l o g i c s w i t c h i n g p o i n t s
s p e c i f i e d by i n p u t and o p e r a t i n g on t h e s t a t e v a r i a b l e s . Also, weight
e q u a t i o n s were o u t 1 ined f o r t h e launch v e h i c l e components p e r t i n e n t t o
atmospheric f l i g h t , a s w e l l a s t u r b o j e t and t u r b o f a n j e t performance d a t a ,
t o be turned over t o t h e c o n t r a c t o r . Benchmark engines chosen were t h e
P&W TF33P-7 of t h e C-141, and t h e advanced technology engines of t h e C-5A,
Boe ing 747 and Boe ing 27 07.
b.
Meeting on T r a j e c t o r y Research w i t h GD/C
A meeting was h e l d w i t h Louis Tramonti of GD/C t o conduct
renewed d i s c u s s ions of t h e i r work i n advanced launch v e h i c l e t r a j e c t o r y
r e s e a r c h which has been sparked by r e c e n t i n t e r e s t i n t h e near-term
r e u s a b l e launch v e h i c l e of t h e A i r Force. Their model i n c l u d e s p r o v i s i o n s
�f o r t h r e e m i x t u r e r a t i o v a l u e s i n t h e upper s t a g e and two t h r u s t l e v e l s
i n t h e f i r s t s t a g e ; t h e f l i g h t e q u a t i o n s a r e numerically i n t e g r a t e d i n
t h r e e d e g r e e s of freedom, r e f e r e n c e d t o a r o t a t i n g e a r t h , f o r a l l f l i g h t
modes, e x c e p t c r u i s e b a c k . I n g e n e r a l , i t appears t h a t t h e i r r e s e a r c h i s
l a g g i n g behind AERO' s c u r r e n t s t a t u s . . (v. Puttkamer)
7.
Advanced Systems and Mission S t u d i e s
a.
Low T h r u s t Sys tems Study
United A i r c r a f t Research L a b o r a t o r i e s p r e s e n t e d t h e e i g h t h
o r a l p r o g r e s s r e p o r t on t h e work performed on a Study of Low-Acceleration
Space T r a n s p o r t a t i o n Sys tems (NAS8-11309), mod. 4, c o n s i s t i n g e s s e n t i a l l y
of two p a r t s . I n the f i r s t p a r t , t h e n u c l e a r Rankine c y c l e s p a c e power
system, c o n s i s t i n g of a n u c l e a r r e a c t o r w i t h 4 t u r b i n e s and 12 g e n e r a t o r s
(producing 4 m e ) , i s being i n v e s t i g a t e d t o i d e n t i f y c r i t i c a l technology
a r e a s , such a s l o n g - l i f e r e l i a b i l i t y and i t s i m p l i c a t i o n s . For example,
i t was shown t h a t e n - r o u t e maintenance and r e p a i r i s v e r y much n e c e s s a r y
and a p p e a r s f e a s i b l e f o r most of t h e power p l a n t components. I n t h e
second p a r t , a handbook of l o w - t h r u s t t r a j e c t o r i e s and r e l e v a n t informat i o n s u i t a b l e f o r p r e l i m i n a r y m i s s i o n and systems a n a l y s e s i s being
compiled (by Ragsac).
b.
E l e c t r i c P r o p u l s i o n Miss i o n Engineering Study
General E l e c t r i c Co. p r e s e n t e d t h e f i n a l r e p o r t of a
Mission Engineering Study of E l e c t r i c a l l y Propelled Manned P l a n e t a r y
Vehicles.(NAS8-20372), based on a n i n - c o r e thermionic r e a c t o r a t t h e
3 MW l e v e l and c o n c e n t r a t i n g on a manned ~ a r m
s i s s i o n f o r t h e 1980
t o 1990 time p e r i o d , w i t h l a n d i n g c a p a b i l i t y .
c.
P r e s e n t a t i o n t o AS0
M r . Wilson and D r . Farmer of AERO-AT and M r . von Puttkamer
met w i t h M r . Hal Becker of AS0 t o p r e s e n t a s h o r t run-down on c u r r e n t
r e s e a r c h a p p l i c a b l e t o advanced launch v e h i c l e s and p r o p u l s i o n conducted
i n AERO. T r a j e c t o r y and systems s t u d i e s were d i s c u s s e d , a s w e l l as
s u p e r s o n i c i n j e c t i o n and mixing i n v e s t i g a t i o n s conducted by D r . Farmer.
A r e p o r t on some r e c e n t advanced technology meetings a t t h e West Coast
was g i v e n t o M r . Becker by M r . v . Puttkamer.
d.
Airborne Laser CAT D e t e c t i o n Sys tem
A s h o r t s t u d y of che o p e r a t i o n a l i m p l i c a t i o n s of a Laser
system f o r c l e a r - a i r t u r b u l e n c e (CAT) d e t e c t i o n on-board t h e SST was
conducted i n s u p p o r t of AERO-A (Mr. H u f f a k e r ) . Of p a r t i c u l a r i n t e r e s t
i s t h e CO;? pulsed l a s e r . To i n d i c a t e t h e c r i t i c a l i t y of time a v a i l a b l e
between d e t e c t i o n and encounter of t h e CAT, a n "evasion number" was
�d e f i n e d , g i v i n g t h e r a t i o of t h e mean r a d i u s of t h e d i s t u r b a n c e "bubble"
t o t h e d i s t a n c e t o t h e d i s t u r b a n c e from t h e a i r c r a f t a t f i r s t d e t e c t i o n .
For t h e SST c r u i s e , i t appears t h a t t h e e v a s i o n number should be s m a l l e r
than 0.1.
Since t h e i n t e r v a l between p u l s e s a p p e a r s t o be q u i t e l i m i t e d
by s u c h c o n s i d e r a t i o n s a s h e a t i n g , pumping c a p a b i l i t y , e t c . , t h e time
r e q u i r e d f o r f u l l development of t h e scanning m a t r i x could be c o n s i d e r a b l e ,
i n t h e o r d e r of t e n s of seconds. For a 1 0 x 10 scanning m a t r i x , f e a s i b i l i t y may be q u e s t i o n a b l e f o r a n SST, i f t h e p u l s e frequency cannot be
i n c r e a s e d t o somewhere i n t h e o r d e r of 1 0 t o 20 p u l s e s p e r second, r e s u l t i n g i n 5 t o 1 0 seconds per s c a n . During 10 seconds, t h e SST t r a v e l s 7 1 1 2
km.
It i s a l s o a p p a r e n t t h a t f e a s i b i l i t y may depend on a ranging c a p a b i l i t y of t h e (SST) l a s e r of a t l e a s t 100 km, i f n o t 150 km, and on t h e r e l a t i v e abundance of p r o p e r l y d i s p e r s e d p a r t i c u l a t e m a t t e r , as w e l l a s on
t h e r e q u i r e d s c a r c i t y of h i g h - a l t i t u d e water ( i c e ) , a t t h e S S T - a l t i t u d e s
around and above 70,000 f e e t . Aside from t h e SST, t h e l a s e r CAT d e t e c t i o n
system may a l s o be of c o n s i d e r a b l e i n t e r e s t f o r t h e Boeing 747, t h e USAF
(v. Puttkamer)
C-5A, and o t h e r f u t u r e "Jumbo"-Jets, such a s t h e A i r b u s s e s .
11.
ADVANCED STUDIES OFFICE
F l i g h t Performance and Miss i o n Analysis Group
A.
I n s u p p o r t of t h e S a t u r n Improvement S t u d i e s , two memorandums,
R-AERO-X-67-60, "Performance C a p a b i l i t y of t h e S a t u r n V U t i l i z i n g
Modified F-1 and 5 - 2 Engine C h a r a c t e r i s t i c s f o r Various Miss i o n P r o f i l e s "
and R-AERO-X-67-71 "Performance and T r a j e c t o r y Data f o r t h e S a t u r n SA-217
Vehicle Improvement S t u d i e s , " have been i s s u e d .
The f i n a l p r e s e n t a t i o n of t h e BOP-03 Computer Program by
Raytheon was h e l d J u l y 31, 1967 a t MSFC.
The proposals f o r t h e e x t e n s i o n of t h e BOP s e r i e s t o i n c l u d e
atmospheric guidance and rendezvous c a p a b i l i t y have been r e c e i v e d and
a r s being evaluated.
Performance d a t a have been g e n e r a t e d on t h e S a t u r n V t h r e e - s t a g e
t o e l l i p t i c a l assembly o r b i t f o r use i n t h e Manned P l a n e t a r y Flyby
Studies
.
Performance a s p e c t s f o r c e r t a i n proposed n u c l e a r v e h i c l e s have
R e s u l t s a r e now being documented.
been e v a l u a t e d a t t h e r e q u e s t of R-AS-V.
�B.
Systems A n a l y s i s Group
1. The second performance review of c o n t r a c t NAS8-21051 "Use
of Large S o l i d Motors i n Booster A p p l i c a t i o n s " w i t h DAC was conducted
a t MSFC on June 22. Personnel of Lockheed P r o p u l s i o n Company, t h e
p r o p u l s i o n s u b c o n t r a c t o r , have e s s e n t i a l l y completed t h e i r e f f o r t s on
g r a i n d e s i g n , p r o c e s s i n g a n a l y s e s and f i n a l SRM d e s i g n . The remaining
t a s k s f o r LPC a r e a s s o c i a t e d w i t h motor a v a i l a b i l i t y and c o s t s . DAC
d e s i g n a n a l y s e s have been updated t o r e f l e c t t h e f i n a l SRM d e s i g n .
Design of t h e s e l e c t e d c o n f i g u r a t i o n (see April/May Progress Report)
i s proceeding on s c h e d u l e w i t h no major problems having developed.
Review c o p i e s of t h e p o r t i o n of t h e f i n a l r e p o r t d e a l i n g w i t h t h e TVC
s y s tem comparison have been r e c e i v e d by MSFC and a r e b e i n g e v a l u a t e d .
2 . The f i r s t performance review of t h e CCSD s t u d y , NAS8-21107,
"Phase 111, S a t u r n I B Improvement Study" ( s e e April/May Progress Report)
was conducted a t MSFC on June 28. The work d u r i n g t h e r e p o r t i n g period
was concerned w i t h continued development of launch o p t i o n v e h i c l e d e s i g n
and t r a j e c t o r y c h a r a c t e r i s t i c s , plus t h e p r o g r e s s i v e evolvement of
v a r i o u s performance, environment, and d e s i g n a n a l y s e s . A problem has
developed w i t h t h e c o n f i g u r a t i o n employing a "Voyager" type payload
shape due t o the l e n g t h r e q u i r e d f o r packaging t h e payload. A payload
d e n s i t y of 6 1 b s / f t 3 using t h e f u l l performance c a p a b i l i t y w a s a ground
r u l e i n t h e s t u d y . A l o a d s problem and a c o n t r o l problem e x i s t e d , b u t
b o t h can be eased by r e l a x i n g t h e payload d e n s i t y requirement t o 8 l b s / f t 3 .
CCSD was i n s t r u c t e d t o t a k e t h i s approach i n t h e remainder of t h e s t u d y .
Schedules a r e being a d j u s t e d , b u t t h e r e s u l t s should s t i l l be on time t o
serve as input t o parallel studies.
3. The r e s u l t s of t h e t r a d e s t u d y p o r t i o n of t h e TBC s t u d y ,
NAS8-21105, "Saturn V Launch Vehicles w i t h 260-Inch Diameter S o l i d
Motors,"were p r e s e n t e d a t MSFC i n t h e f i r s t performance review. A
b a s e l i n e v e h i c l e w i t h a payload i n excess of 860,000 pounds i n t o
100 n a u t i c a l m i l e c i r c u l a r o r b i t was recommended. The v e h i c l e cons i s t e d
of s t a n d a r d l e n g t h S-IC and S- T I s t a g e s w i t h f o u r 260" SRM's a t t a c h e d t o
t h e S-IC s t a g e . Excess S-IC p r o p e l l a n t r e q u i r e d f o r f l i g h t performance
o p t i m i z a t i o n i s contained i n f o u r l i q u i d pods mounted over t h e s o l i d
motors. This tankage arrangement was d i c t a t e d by t h e h e i g h t l i m i t a t i o n imposed by t h e VAB. Lengthening t h e S-IC tanks w h i l e s a t i s f y i n g
t h e o v e r a l l v e h i c l e h e i g h t c o n s t r a i n t would y i e l d u n r e a l i s t i c a l l y
h i g h payload d e n s i t i e s . The SRM'S would burn f o r 130 seconds p a r a l l e l
w i t h S-IC burn. This recommendation was t e n t a t i v e l y a c c e p t e d by MSFC,
b u t f u r t h e r c o n s i d e r a t i o n led t o i t s replacement by a " z e r o s t a g e "
concept. The b a s e l i n e v e h i c l e f i n a l l y s e l e c t e d f o r d e t a i l e d s t u d y
y i e l d s a payload of over 700,000 pounds i n t o low e a r t h o r b i t . This
v e h i c l e has s t a n d a r d l e n g t h s t a g e s , y i e l d s a c c e p t a b l e payload d e n s i t i e s , and a v o i d s the compl i c a t i o n s of t h e a d d i t i o n a l l i q u i d pods.
The s t u d y i s now i n the d e s i g n phase, and work i s p r o g r e s s i n g
satisfactorily.
�C.
As trodynamics and Miss i o n Analysis Group
I.
IIanned P l a n e t a r y Flyby Missions Based on S a t u r n / ~ p o l l o
Sys tern
The f i n a l review of t h e above s u b j e c t s t u d y ( c o n t r a c t
number NAS8-18025) performed by North American A v i a t i o n , Space D i v i s i o n
was h e l d a t MSFC on August 2 , L967. More than 100 persons from t h e
v a r i o u s NASA c e n t e r s , Headquarters and t h e aerospace i n d u s t r y a t t e n d e d
t h e review.
The r e s u l t s of t h e s t u d y were w e l l r e c e i v e d . The c o n t r a c t o r
developed a recommended program c o n s i s t i n g of two m u l t i p l a n e t f l y b y m i s s i o n s . Based on t h e g u i d e l i n e s used i n t h e course of t h e s t u d y , t h e
s t a n d a r d S a t u r n V could n o t meet t h e i n j e c t e d payload and m i s s i o n r e q u i r e ments u n l e s s some compromise was made on t h e payload. The c o n t r a c t o r
recommended t h a t an uprated S a t u r n V be developed w i t h a two s t a g e t o
low e a r t h o r b i t payload c a p a b i l i t y of 400,000 l b s o r g r e a t e r . Based on
t h e development schedule prepared by North American A v i a t i o n , a program
"go-ahead" would be r e q u i r e d by 1970. The s t u d y review was g i v e n a t
NASA Headquarters on Thursday, August 3 . A t t h e c o n c l u s i o n of t h e
summary b r i e f i n g M r . George Trimble, D i r e c t o r of Advanced Manned Missions,
OMSF, r e q u e s t e d t h a t t h e summary b r i e f i n g be given t o D r . Seamans. The
p r e s e n t a t i o n t o D r . Seamans w i l l be g i v e n a t a l a t e r d a t e .
2.
In-House P l a n e t a r y Study Program
Plans a r e being f i n a l i z e d f o r a s t a r t of t h e in-house
Advanced Voyager S t u d i e s . The s t u d i e s w i l l be conducted by personnel
of t h e c o l l o c a t e d elements of t h e A s t r i o n i c s , P&VE, and Aero-Astrodynamics
L a b o r a t o r i e s , and t h e MSFC Advanced Systems O f f i c e . M r . Bob E l l i s o n of
t h i s o f f i c e w i l l be d i r e c t i n g t h e s e s t u d i e s .
3 . M r . Archie Young of t h i s o f f i c e w i l l p r e s e n t a paper
e n t i t l e d , "A Computer Simulation of t h e O r b i t a l Launch Window Problem,"
a t t h e ATAA Guidance, C o n t r o l , and F l i g h t Dynamics Conference, H u n t s v i l l e ,
Alabama, August 14-16.
111.
AEROPHYSICS DIVISION
A.
F l u i d Mechanics Research O f f i c e
1.
Aerodynamic Crossed-Beam Programs
A t r a c e r system has been i n s t a l l e d i n t h e Thermal A c o u s t i c
J e t F a c i l i t y d u r i n g June and a s e r i e s of t e s t s was performed u s i n g t h i s
system and one beam of a l a s e r cross-beam instrument t o d e t e c t t r a c e r
i n t e n s i t y and t h e p e n e t r a t i o n a b i l i t y of t h e l a s e r i n t h e l i q u e f a c t i o n
r e g i o n of t h e TAJF nozzles a t high chamber p r e s s u r e s .
Satisfactory
r e s u l t s were o b t a i n e d .
�A t e s t was i n i t i a t e d i n J u l y t o make s c h l i e r e n and shadowgraph p i c t u r e s of t h e plume and i n t e r a c t i o n r e g i o n of t h e S-11 engine
c l u s t e r i n the TAJF. These t e s t s were i n s u p p o r t of a program t o measu r e t h e t o t a l p r e s s u r e i n t h e c l u s t e r plumes and s h e a r l a y e r s and t o
make f l u c t u a t i n g p r e s s u r e measurements on t h e model b a s e .
2.
Atmospheric Crossed-Beam Program
P r e l i m i n a r y r e s u l t s have been obtained on t h e a t m o s p h e r i c
crossed-beam s y s tern during t h e i n i t i a l c a l i b r a t i o n and t e s t i n g period
a t MSFC. Two b a s i c s e r i e s of t e s t s were c a r r i e d o u t . F i r s t , t h e l i g h t
i n t e n s i t y f l u c t u a t i o n s induced by t h e atmosphere i n each i n d i v i d u a l
photometric d e t e c t o r o r "single-beam" system were recorded on magnetic
t a p e . The measured spectrum follows t h e -513 power law a t low f r e quencies which corresponds t o t h a t expected from atmospheric d e n s i t y
f l u c t u a t i o n s i n t h e boundary l a y e r of t h e troposphere.
Similar data
were o b t a i n e d by CSU personnel using hot-wire anemometers a t v a r y i n g
h e i g h t s up t o 40 meters on a m e t e o r o l o g i c a l tower. The second s e r i e s
of t e s t s was t o determine t h e l e n g t h of t h e d a t a samples r e q u i r e d t o
o b t a i n a measurable c o r r e l a t i o n between t h e crossed beams. The d a t a ,
recorded under i d e a l c l e a r - s k y v i e k i n g c o n d i t i o n s , contained a p p r o x i m a t e l y 85 minutes u s a b l e d a t a which a r e now being e v a l u a t e d .
B.
Mechanical Design Off i c e
1.
S - I 1 I n s u l a t i o n Shedding E f f e c t T e s t Equipment
Models, i n s u l a t i o n hopper, and' m o d i f i c a t i o n s of MSFC' s
1 4 x 14-inch wind t u n n e l f o r determining t h e c a t a s t r o p h i c e f f e c t s of
t h e shedding of t h e o u t e r i n s u l a t i o n of t h e S - I 1 s t a g e have been
d e s i g n e d , f a b r i c a t e d and d e l i v e r e d
.
2.
Equipment f o r Heat t r a n s f e r T e s t s on S - I 1 S t a g e due t o
Protuberance Flow I n t e r a c t i o n s
The d e s i g n f o r m o d i f i c a t i o n of Douglas designed "Hot
T r a n s f e r Sidewall Assembly" and t h e d e s i g n of new hardware t o o b t a i n
h e a t t r a n s f e r d a t a f o r i n t e r a c t i n g protuberance flow f i e l d s on t h e S - I 1
s t a g e have been completed. The t e s t w i l l be conducted by Boeing i n
L a n g l e y l s U n i t a r y Wind Tunnel.
3 . The f o l l o e i n g i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and
t h e i r current s t a t i s :
Visual Aid Gimbal Assembly (-F)
Fabrication
Modify Survey Probe Assembly (-AD)
Design
�O r b i t a l Workshop Model f o r Area
and Moment ~e termina t i o n (-AD)
Design
S l o s h Force Measuring Device (-D)
Drafting
Odyssey Display Model (-T)
Des i g n
~ o d i f i c a t i o n / ~ e - d iegsn of S p e c i a l T e s t
S e c t i o n 14-Inch Wind Tunnel f o r
5-inch O.D. Base Flow Models (-AM)
Fabrication
5-Inch O.D. S a t u r n V Base Flow Model
w i t h Pressure Instrumentation f o r
14" Wind Tunnel (-AM)
Crossed-Beam
Design
-
Diaphragm C u t t e r Assembly f o r t h e
High Reynolds Assembly (-AE)
Fabrication
Four-Percent S a t u r n V Force
Model - AEDC (-AD)
Fabrication
Remote Control Hardware f o r Floor and
TTS, 14" Wind
C e i l i n g Adjustment
Tunnel (-AE)
-
Temperature
-
Mismatch T e s t S e c t i o n (-AT)
P r e s s u r e Probes and Support System
14" Wind Tunnel (-AD)
Five-Component,
(-AE)
112-1nch O.D.
Drafting
-
Balance
V a r i a b l e P o r o s i t y Walls f o r TTS
14" Wind Tunnel (-AE)
Drafting
Delivered
Fabrication
-
S a t u r n V, Thin Skin Heat T r a n s f e r
Model
JPL (-AE)
-
Strap-on Booster f o r S-IC Model
(CAL Design
CAL) (-AT)
-
Fabrication
Fabrication
P a r t i a l Del.
& Fabrication
F l a t P l a t e Model (NSL Design)
(-AD)
- AMES
Fabrication
Free O s c i l l a t i n g Balance and Model
Assembly (Lockheed Design) (-AU)
Fabrication
Three-Cylinder Models f o r Low Density
Tes t ing (-AE)
Delivered
�C.
Aerodynamic Design Branch
1.
Saturn I B
-
LEM 1
The a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n IB AS-204
v e h i c l e r e f l e c t i n g t h e Lunar Module m i s s i o n and c o n f i g u r a t i o n have
been published i n R-AERO-AD-67-56.
The d a t a a r e based on previous
e s t i m a t e s f o r t h e AS-206 v e h i c l e which have been modified t o account
f o r t r a j e c t o r y induced v a r i a t i o n s i n b a s e p r e s s u r e .
2.
S a t u r n IB
-
Minuteman
Chrys l e r Corporation Space D i v i s i o n has conducted t e s t s
i n t h e hISFC 14" TWT t o determine s t a t i c s t a b i l i t y and a x i a l f o r c e
c h a r a c t e r i s t i c s f o r the c u r r e n t S a t u r n IB/MM c o n f i g u r a t i o n s
Tests
were a l s o conducted t o determine loads on t h e 70-inch diameter S a t u r n IB
tanks w i t h t h e Minuteman s t r a p p e d t o t h e S-IB t a i l b a r r e l .
.
3.
S a t u r n V / ~ o y a g e rS t a b i l i t y
Experimental wind t u n n e l t e s t s have been completed i n t h e
MSFC 14" TWT of t h e S a t u r n ~ / ~ o y a g ec o
r n f i g u r a t i o n . These t e s t s were
made u s i n g a 0.3366 p e r c e n t s c a l e d model, and were over a Mach number
range of from 0.50 through 4.96.
The range of a n g l e s of a t t a c k was
from - 3 t o +16 d e g r e e s . The procedures and t h e r e s u l t s of t h i s
i n v e s t i g a t i o n a r e presented i n R-AERO-AD-67-65.
4.
S a t u r n V L i f t - o f f Aerodynamics
Model d e s i g n and f a b r i c a t i o n of a 0.9 p e r c e n t s c a l e d model
of t h e S a t u r n V w i t h launch pad and LUT were reviewed on a r e c e n t t r i p
t o t h e Vought Aeronautics p l a n t . The d e s i g n i s a c c e p t a b l e , and model
d e l i v e r y i s scheduled f o r August 18, 1967, w i t h t e s t i n g t o b e g i n
August 2 1 , 1967, i n t h e LTV low speed wind t u n n e l f a c i l i t y .
Northrop Space L a b o r a t o r i e s has n e a r l y completed a comp u t e r program which w i l l c a l c u l a t e t h e flow f i e l d surrounding t h e
S a t u r n V with engines on i n t h e presence of ground winds. This flow
f i e l d w i l l be used t o c a l c u l a t e loads on t h e v e h i c l e d u r i n g l i f t - o f f .
The program can handle any wind d i r e c t i o n a t any v e h i c l e launch a l t i tude up t o t h e p o i n t where t h e v e h i c l e c l e a r s t h e tower. The d e l i v e r y
d a t e f o r t h i s program and r e s u l t s f o r s e v e r a l v e h i c l e a l t i t u d e s and
wind d i r e c t i o n s i s J u l y 28, 1967.
�5.
Saturn V
-
S t a t i c S t a b i l i t y and P r e s s u r e T e s t
T e s t i n g of a 4 p e r c e n t s c a l e model of t h e S a t u r n V launch
v e h i c l e i n t h e AEDC 1 6 - f o o t t r a n s o n i c wind t u n n e l t o determine h i g h
a n g l e - o f - a t t a c k s t a t i c s t a b i l i t y and d e t a i l e d load d i s t r i b u t i o n over
tllc t a i l b a r r e l i s scheduled f o r November 20, 1967.
The model d e s i g n i s complete, and f a b r i c a t i o n i s expected
by September 1 5 , 1967.
Generation of p r e t e s t i n f o r m a t i o n t o be p r e s e n t e d a t a
p r e t e s t conference a t AEDC i s underway. The Computation Laboratory
has agreed t o i n t e g r a t e t h e p r e s s u r e d a t a and provide o u t p u t i n
g r a p h i c and t a b u l a r form.
6.
Aerodynamic C h a r a c t e r i s t i c s of a n Uprated S a t u r n V Vehicle
The aerodynamic c h a r a c t e r i s t i c s of a t h r e e - s t a g e , t h r u s t augmented S a t u r n V v e h i c l e have been published i n R-AERO-AD-67-55.
These d a t a i n c l u d e normal f o r c e , a x i a l f o r c e , and c e n t e r of p r e s s u r e
f o r a S a t u r n V w i t h f o u r seven-segment 120-inch diameter s o l i d r o c k e t
motors s t r a p p e d on t h e S-IC s t a g e . These d a t a a r e provided throughout
t h e r e q u i r e d Mach number and a n g l e - o f - a t t a c k range.
7.
S a t u r n V/S-I1 Sidewall I n s u l a t i o n T e s t s
T e s t s a r e b e i n g cohducted i n t h e MSPC 14" TWT t o determine
t h e s t r u c t u r a l i n t e g r i t y of S a t u r n V/S-I1 s t a g e i n s u l a t i o n under simul a t e d f l i g h t aerodynamic environment. The t e s t samples f u r n i s h e d by
P&VE Laboratory w i l l b e t e s t e d a t f o u r dynamic p r e s s u r e l e v e l s a t a
Mach number of approximately 1.80. Also t o be i n v e s t i g a t e d a r e charact e r i s t i c i n s u l a t i o n c r a c k s and debonds a s s p e c i f i e d by P&VE. R e s u l t s
of t h e s e t e s t s w i l l be combined w i t h s i m i l a r t e s t r e s u l t s obtained by
NAA i n a j o i n t memorandum.
8.
Apollo-Saturn V Second S t a g e S t a b i l i t y and Drag
Characterist i c s
Supplemental aerodynamic s t a t i c s t a b i l i t y and a x i a l f o r c e
c h a r a c t e r i s t i c s f o r t h e second s t a g e f l i g h t c o n f i g u r a t i o n of t h e pol lo/
S a t u r n V v e h i c l e have been generated t o s u p p o r t low a l t i t u d e a n a l y s i s of
t h e v e h i c l e p r e d i c a t e d by a p o s s i b l e S-IC s t a g e m a l f u n c t i o n . The d a t a
a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-67-52.
�9.
I n - F l i g h t Vehting Analyses f o r t h e S-111s-IVB I n t e r s t a g e
of t h e Apollo/Saturn V Vehicle
Updated aerodynamic and t r a j e c t o r y i n p u t d a t a f o r t h e S - I I /
S - I m i n t e r s tagc i n f l igllt v e n t i n g a n a l y s i s have p r e d i c a t e d new i n f l i g h t
i n t e r n a l p r e s s u r e l l i s t o r i c s . These d a t a a r e published i n R-AERO-AD-6758 Tor the 503 and 504 f l i g h t t r a j e c t o r i e s .
10.
A p o l l o / S a t u r n V S-IC Stage Compartment I n t e r n a l
P r e s s u r e Time H i s t o r i e s f o r t h e SA-504 T r a j e c t o r y
I n f l i g h t p r e s s u r e h i s t o r y bands f o r t h e S-IC b a s e , S-IC
i n t e r s t a g e compartments, generated f o r t h e
i n t e r t a n k , and S-111s-IVB
SA-504 t r a j e c t o r y , a r e presented i n R-AERO-AD-67-60.
11.
S a t u r n IB/Apollo (Abort)
I n t h e e v e n t of a m i s s i o n f a i l u r e f o r t h e S a t u r n I ~ / A p o l l o
d u r i n g f i r s t s t a g e f l i g h t , t h e command module i s t o be j e t t i s o n e d .
Thus, s t a t i c l o n g i t u d i n a l s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s
f o r t h e v e h i c l e i n the a b o r t c o n f i g u r a t i o n a r e r e q u i r e d . Plans have
been made f o r a n experimental wind t u n n e l t e s t program t o be r u n i n
t h e MSFC 14" TWT f a c i l i t y . A 0.55 p e r c e n t s c a l e d model of t h e c u r r e n t
S a t u r n pol pol lo (AS-205) v e h i c l e c o n f i g u r a t i o n i s t o be used (MSFC
Model No. 3 2 7 ) . T e s t parameters i n c l u d e Mach numbers from 0.50 t o
4.96, a n g l e s of a t t a c k of from -2" t o +16O, and r o l l a n g l e s of 0 ° ,
45" a n d 90". The t e s t i s now scheduled t o be completed t h e f i r s t
week of August.
12.
Apollo/Saturn I B S t a b i l i t y Aerodynamics
A r e c e n t i n v e s t i g a t i o n of t h e Saturn I B AS-205 c o n f i g u r a t i o n i n d i c a t e d a forward s h i f t i n c e n t e r of p r e s s u r e a s compared t o
AS-201.
This s h i f t i.s s i g n i f i c a n t l y g r e a t e r than p r e s e n t aerodynamic
t o l e r a n c e s . Wind t u n n e l t e s t s were made a t t h e MSFC 14" TWT and
LTV & f o o t wind t u n n e l . New aerodynamic s t a b i l i t y and corresponding
load d i s t r i b u t i o n s a r e being generated f o r t h e AS-205 c o n f i g u r a t i o n .
The major f a c t o r s t h a t caused t h i s s h i f t a r e (1) removal of t h e t u r b i n e
exhaust d u c t , (2) removal of engine shrouds, ( 3 ) i n c r e a s e of t h e Apollo
u m b i l i c a l f a i r i n g h e i g h t from 4" t o 15", and (4) i n c r e a s e i n h e i g h t of
S-IB r e t r o - r o c k e t s from 15.5" t o 22.9".
13.
O r b i t a l Aerodynamics
Lockheed p e r s o n n e l , working under Schedule Order No. 83,
have c a l c u l a t e d o r b i t a l aerodynamic d a t a f o r s e v e r a l updated O r b i t a l
These d a t a , which r e f l e c t
Workshop and LM/ATM c l u s t e r con£ i g u r a t i o n s
r e c e n t changes i n t h e c o n f i g u r a t i o n geometry of t h e O r b i t a l Workshop
and LM/ATM c l u s t e r , a r e presented i n t h e f o l l o w i n g memorandums:
.
�( a ) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e Lunar
~ o d u l e / A p o l l oTelescope ( ~ I A T Mw)i t h and w i t h o u t t h e Docked Command
and S e r v i c e Module (CSM) (MSFC Dwg. SK10-7266, Rev. G ) , R-AERO-AD-67-54,
June 1 6 , 1967.
(b) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e LM/ATM
C l u s t e r C o n f i g u r a t i o n of t h e O r b i t a l Workshop (MSFC Dwg. SK107298),
R-AERO-AD-67-63, J u l y 20, 1967.
( c ) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e O r b i t a l
Workshop w i t h and w i t h o u t t h e Docked Command and S e r v i c e Module (MSFC
Dwg. SK10-7298, Rev. F ) , R-AERO-AD-67-66, J u l y 24, 1967.
Lockheed has a l s o c a l c u l a t e d aerodynamic drag d a t a f o r t h e
Voyager s p a c e c r a f t i n t h r e e e l l i p t i c o r b i t s around Mars. These d a t a
have n o t y e t been p u b l i s h e d .
14.
P a r a m e t r i c Strap-on Study
One approach t o u p r a t i n g launch v e h i c l e s i s t o use "strap-on"
s o l id p r o p e l l a n t t h r u s t a s s i s t . I n s u p p o r t of f e a s i b i l i t y s t u d i e s ,
p a r a m e t r i c aerodynamic d a t a a r e needed f o r v a r i o u s b a s i c / s e c o n d a r y body
combinations. Because of t h e complexity of t h e aerodynamics, a n e x p e r i mental p a r a m e t r i c s t u d y was i n i t i a t e d t o s t u d y n i n e s e p a r a t e parameters
i n approximately f i v e phases.
Phase I i s t h e s t u d y of t h e e f f e c t of v a r i o u s s i z e s t r a p - o n s
on t h r e e b a s i c b o d i e s of d i f f e r e n t f i n e n e s s r a t i o s . Because of t h e l e n g t h
of t h e r e q u i r e d t e s t program, i t was n e c e s s a r y t o r u n Phase I i n two
p a r t s . P a r t I of Phase I was completed i n t h e MSFC 14" TWT d u r i n g June
1967. Data from t h e f i r s t p a r t w i l l be e v a l u a t e d f o r t r e n d s and used t o
s e t g u i d e l i n e s f o r reducing t h e l e n g t h of t h e second p a r t . A f t e r t h e
completion of b o t h p a r t s of t h e t e s t program, a n i n t e r i m r e p o r t w i l l be
published.
15.
Drag T e s t s i n t h e Low Density Wind Tunnel
An experimental i n v e s t i g a t i o n has been conducted i n t h e Low
D e n s i t y Wind Tunnel, and i t has r e v e a l e d t h e need f o r improvements i n
b o t h t h e t e s t f a c i l i t y and t e s t equipment. 'Cwo recommendations f o r
improvements which could provide b e t t e r d a t a over a l a r g e range of
Knudsen numbers a r e a s follows:
(1) Cooling c o i l s which a r e a t t a c h e d t o
t h e o u t e r s u r f a c e of t h e wind t u n n e l n o z z l e should be a c t i v a t e d s o t h a t
some of t h e n o z z l e boundary l a y e r can be f r o z e n o u t . This could p o s s i b l y
( 2 ) A more s e n s i t i v e
p r o v i d e a n i s e n t r o p i c t e s t core a t lower p r e s s u r e s .
b a l a n c e i s needed s o t h a t s m a l l e r models could be t e s t e d a t low p r e s s u r e s .
T e s t s of s m a l l models a t low p r e s s u r e s would provide d a t a under n e a r l y
f r e e - m o l e c u l e flow c o n d i t i o n s .
�16.
Body of Revolution Viscous Cross -Flow I n v e s t i g a t i o n
C o n t r a c t NAS8-21152 has been awarded f o r t h e c o n t i n u a t i o n
of t h e v i s c o u s cross-flow i n v e s t i g a t i o n i n t h e LTV high speed wind
t u n n e l . The p r e s s u r e model, s t i n g , and a s s o c i a t e d hardware w i l l be
provided by MSFC. A t t h i s time, no f i r m t e s t d a t e has been s e t . Model
d e s i g n , f a b r i c a t i o n , and assembly a r e expected t o r e q u i r e approximately
f i v e months.
A s t u d y of i n s t r u m e n t a t i o n requirements, model s i z e , s t i n g to-model-diameter r a t i o s , d a t a accuracy and r e q u i r e d t e s t i n g time i s
being conducted f o r f u t u r e u t i l i z a t i o n of t h e proposed h i g h Reynolds
number t e s t equipment.
D.
Experimental Aerophysics Branch
1.
Low Dens i t y Wind Tunnel
T e s t s have been completed i n t h e Low Density Wind Tunnel
on m i c r o f o r c e drag measurements f o r 1 - i n c h t o 3-inch diameter s p h e r e s
and d i s c s and f o r 1-inch and 2-inch diameter cones w i t h 9' h a l f - a n g l e s .
A second pendulum-type m i c r o f o r c e b a l a n c e No. 220A , which
has approximately twice t h e s e n s i t i v i t y of balance No. 220 and extends
t h e range down t o 0.001 grams f o r c e , has been c a l i b r a t e d . A t o r s i o n a l
m i c r o f o r c e b a l a n c e i s being f a b r i c a t e d f o r measurement of a wider range
of drag f o r c e s i n t h e LDWT.
Three a d d i t i o n a l LN2 Dewars have been obtained a s excess
from R-TEST t o i n c r e a s e s t o r a g e c a p a c i t y and e f f i c i e n c y of t h e cryopumping system i n t h e LDWT. Arrangements a r e being made t o o b t a i n a
GHE r e f r i g e r a t o r t o be used a s a cryopumping system. This w i l l provide
t h e c a p a b i l i t y of using n i t r o g e n gas a s t h e Low Density Wind Tunnel
flow medium.
C a l i b r a t i o n has been resumed on t h e Mach 4 low d e n s i t y
nozzle.
S t a t i c p r e s s u r e s a r e being measured a l o n g t h e n o z z l e a x i s
f o r comparison w i t h computed v a l u e s based upon e a r l i e r measurements.
2.
Impulse Base Flow F a c i l i t y
A s h o r t d u r a t i o n p a r a m e t r i c base h e a t i n g model t e s t was
planned s e v e r a l y e a r s ago t o provi.de b a s i c b a s e h e a t i n g d a t a on a number
o:f m u l t i - e n g i n e c o n f i g u r a t i o n s . This t e s t was never conducted because
of h i g h e r p r i o r i t y work a s s o c i a t e d w i t h t h e v a r i o u s S a t u r n s t a g e s . A
t e s t i s now planned t o use some of t h e ha.rdware designed f o r t h e e a r l i e r
t e s t , b u t t h e emphasis has been s h i f t e d t o determining t h s e f f e c t of
model s c a l e on th.e r e c o v e r y temperatures and h e a t t r a n s f e r c o e f f i c i e i l t s
�i n t h e base r e g i o n . The program has f i v e s e p a r a t e phases, t h e purpose
and scope of which a r c b r i e f l y d e s c r i b e d i n t h e p r o j e c t summary AT-68.
Hardware d e s i g n and f a b r i c a t i o n f o r t h e above t e s t i s comp l e t e and cold flow checkout of t h e model w i l l begin t h e f i r s t week i n
Augus t.
3.
High Reynolds Number S p e c i a l T e s t Equipment
A summary meeting of t h e High Reynolds Number T e s t Equipment s t a t u s was h e l d J u l y 21, 1967. The following is a l i s t of major
items and t h e i r expected d e l i v e r y d a t e s :
-
(a)
Supply tube
(b)
S e t t l i n g chamber
(c)
Building
(d)
Sphere
(e)
Other items
-
-
October 1967.
-
December 1967.
December 1967.
January 1968.
-
May 1968.
I n s t r u m e n t a t i o n was t h e major concern of t h i s meeting.
Because of quick-response i n s t r u m e n t a t i o n r e q u i r e m e n t s , l o c a t i o n of
t h e t r a n s d u c e r w i t h r e s p e c t t o model measuring o r i f i c e i s c r i t i c a l .
P r e s e n t p l a n s a r e t o house pressure-measuring i n s t r u m e n t a t i o n w i t h i n
t h e s t i n g a s c l o s e t o t h e model a s p o s s i b l e . . Following a s e r i e s of
t r a n s d u c e r response t e s t s , i t was concluded t h a t 'tubing of 0.085-inch
I . D . and 3 f e e t i n l e n g t h would provide adequate response. Run times
of 100 m i l l i s e c o n d s i s expected a f t e r 300 m i l l i s e c o n d s of s t a r t i n g
process.
Model s t a r t i n g l o a d s a t maximum Reynolds number & 200 x l o 6
per f o o t ) a r e a l s o of concern, e s p e c i a l l y a t h i g h a n g l e s of a t t a c k , s i n c e
t h e model must be s e t a t t h e d e s i r e d a n g l e of a t t a c k b e f o r e flow i n i t i a tion.
S t u d i e s a r e underway t o e s t a b l i s h t h e maximum number of
d a t a channels which may be provided w i t h t h e p r e s e n t model, s t i n g , and
transducer constraints
.
4.
Thermal Acoustic J e t F a c i l i t y
A t e s t program i s underway on t h e cold flow d u c t f o r
R-AERO-AF t o i n v e s t i g a t e p r e s s u r e f l u c t u a t i o n s i n t h e base r e g i o n of a
c l u s t e r e d j e t and t o determine t h e t o t a l p r e s s u r e v a r i a t i o n s i n t h e
e x h a u s t plumes. A p r i o r t e s t was r u n t o map t h e flow f i e l d s photog r a p h i c a l l y and t o a i d i n t h e o v e r a l l a n a l y s i s of t h e f i n a l d a t a .
�1 i.11111 l i c a t c r c o n t r a c t d e l i v c r y d e a d l i n e of 111id-September
1967 w i l l probably bc mct.
T l i c Iic
5.
7 x 7-Inch B i s o n i c Wind Tunnel
The BWT has been s u f f i c i e n t l y r e p a i r e d t o a l l o w t e s t i n g .
A p r e l i m i n a r y i n v e s t i g a t i o n was run by Wyle f o r R-AERO-AU t o determine
the shock l o c a t i o n on s e v e r a l forward-facing wedges of v a r i o u s p e r c e n t a g e s
of blockages. The tunnel i s scheduled f o r a complete c a l i b r a t i o n b e f o r e
future tests
.
6.
1 4 x 14-Inch T r i s o n i c Wind Tunnel
The following t e s t s were r u n d u r i n g June and J u l y 1967:
a . A t e s t of t h e s t a t i c l o n g i t u d i n a l s t a b i l i t y and
a x i a l f o r c e c h a r a c t e r i s t i c s of t h e uprated S a t u r n I (AS-205) f o r R-AERO-AD.
T o t a l r u n s : 99.
b . A p a r a m e t r i c s t u d y f o r R-AERO-AD of t h e aerodynamic
c l l a r a c t e r i s t i c s of s o l i d p r o p e l l a n t "s trap-on" t h r u s t a s s i s t a s a p p l i e d t o
S a t u r n - t y p e v e h i c l e s . T o t a l r u n s : 128.
c. A t e s t f o r R-AERO-AD by C h r y s l e r t o determine t h e
t o t a l f o r c e s and moments on t h e 70-inch diameter tanks on models of t h e
S a t u r n IB/LM and Apollo launch v e h i c l e s w i t h Minuteman s t r a p - o n conf i g u r a t i o n s . T o t a l r u n s : 53.
d . An i n v e s t i g a t i o n t o determine t h e s t a t i c s t a b i l i t y
and a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n ~B/LM/Minutemanand S a t u r n IB/
Apoll.o/Minuteman con£ i g u r a t i o n s . This i s a supplemental t e s t t o t h e prev i o u s i n v e s t i g a t i o n . T o t a l runs : 190.
e . A t e s t f o r R-AERO-AD, i n c o n j u n c t i o n w i t h P&VE, t o
determine t h e s t r u c t u r a l i n t e g r i t y of t h e S a t u r n V/S-I1 s t a g e i n s u l a t i o n
a t v a r i o u s t u n n e l dynamic p r e s s u r e s . High 'speed movies were taken of
v a r i o u s panel c o n f i g u r a t i o n s , a l o n g w i t h l o c a l mean and f l u c t u a t i n g
p r e s s u r e measurements. T o t a l r u n s : 140.
The tunnel i s c u r r e n t l y running a t a reduced r a t e because
I n t e r n a l combust ion caused t h e
t h e main compressor i s i n o p e r a t i v e
compressor' s t h i r d s t a g e a f t e r c o o l e r t o blow a p a r t , caus ing c o n s i d e r a b l e
damage. A committee from Aerophysics D i v i s i o n i s i n v e s t i g a t i n g t h e causes
of t h e combustion t o determine a r e l i a b l e f i x . The compressor w i l l b e
down f o r a b o u t two months. P r e s e n t o p e r a t i o n i s from R-TEST'S 3500 p s i
air.
.
�7.
O r b i t a l Aerodynamics Scanner Sys tems
The d e s i g n , f a b r i c a t i o n , and checkout of t h e improved
v c r s i o n of the h i g h speed d i g i t a l T.V. scanner s y s tem have been complctccl. Minor problems were encountered i n p r o p e r l y i l l u m i n a t i n g t h e
modcl. Dcsign oE a l i g h t box t o e l i m i n a t e t h e problem is underway.
I n t h e p r e s e n t system, t h e d a t a a r e recorded on IBM c a r d s
f o r l a t e r r e d u c t i o n i n R-AERO-AE's computer f a c i l i t i e s . A program was
w r i t t e n and checked o u t f o r computing moments, a r e a s , and c e n t r o i d s of
a body a b o u t b o t h t h e X and Y axes based upon d a t a d i g i t i z e d by t h i s
system. A new v e r s i o n of t h e T.V. system i s under c o n s i d e r a t i o n t h a t
w i l l compute t h e a r e a s and moments on l i n e , t h e r e b y e l i m i n a t i n g t h e
mass of d a t a c a r d s t h a t a r e p r e s e n t l y r e q u i r e d .
The p h o t o - c e l l scanner f o r determining moments and p r o j e c t e d
a r e a s has been completed and i s about 95 p e r c e n t checked o u t . A few
minor items r e q u i r e d rework. The system w i l l be o p e r a t i o n a l w i t h i n
1 0 days.
8.
I n s trumenta t i o n
P i l o t s t u d i e s of r e a l - t i m e , o n - l i n e d i g i t i z i n g of c r o s s e d beam d a t a have been s t a r t e d . The d a t a s y s tem from t h e shock t u n n e l i s
t o be used a s a n a n a l o g - t o - d i g i t a l c o n v e r t e r , and t h e o u t p u t s t o r e d on
d i g i t a l magnetic t a p e f o r computer e n t r y . The d a t a system was t o be
modified f o r d i g i t a l magnetic t a p e o u t p u t i n a d d i t i o n t o t h e e x i s t i n g
card o u t p u t . The d i g i t a l t a p e u n i t was purchased; b u t upon a r r i v a l ,
i t was dropped on i t s f a c e i n t h e r e c e i v i n g a r e a of Technical S e r c i e s
O f f i c e . Because of t h e e x t e n s i v e damage, i t i s being r e t u r n e d t o t h e
f a c t o r y f o r r e p a i r , which w i l l t a k e about two months.
9.
Data Reduction
D i g i t a l magnetic t a p e s of t h e 4 p e r c e n t S a t u r n V model
s t a t i c p r e s s u r e d a t a were converted t o c a r d s f o r p l o t t i n g . About twot h i r d s of t h e s t a t i c d a t a have been machine p l o t t e d f o r R-AERO-AU.
A program was wriLten t o c o r r e c t the t r a n s o n i c o v e r a l l
sound p r e s s u r e l e v e l d a t a from t h e Saturn V 4 p e r c e n t a c o u s t i c model.
These c o r r e c t i o n s were f o r human e r r o r s , bad c h a n n e l s , c a l i b r a t i o n
c o r r e c t i o n s , e t c . , t h a t became e v i d e n t a f t e r t h e t e s t . Work has n o t
s t a r t e d on measuring and d i g i t i z i n g t h e o v e r a l l sound p r e s s u r e l e v e l s
from t h e s u p e r s o n i c phase; i t w i l l probably n o t s t a r t u n t i l t h i s w i n t e r .
�LO.
Miscellaneous
A magnetic t a p e r e c o r d e r and e l e c t r o n i c s were s e t up a t
R-COMP t o p l a y back ground winds d a t a .
S e v e r a l items of e l e c t r o n i c s , which a r e p a r t of t h e ground
winds t e s t i n g damper system, and a S a t u r n I ~ / ~ e n t a u
model
r
were s e n t t o
Lockheed f o r s y s tem t e s t i n g and checkout.
Work has been completed on r e c o n d i t i o n i n g and equipping
t h e v a n - t r u c k a s an i n s t r u m e n t a t i o n v e h i c l e f o r f i e l d t e s t i n g of t h e
crossed-beam program. The two-telescope t r a i l e r s have been completed,
covers made, c a b l e r a c k s i n s t a l l e d , and t h e t e l e s c o p e s mounted. The
f a c i l i t i e s have been used by IITRI f o r t h e p a s t f o u r weeks. T e s t i n g
a t t h e AMICOM 400-foot tower i s expected t o s t a r t i n mid-August.
E.
Thermal Environment Branch
1.
M u l t i p l e Protuberance T e s t s
Wind t u n n e l t e s t i n g of t y p i c a l S a t u r n v e h i c l e protuberance
arrangements i s being planned f o r e a r l y f a l l . The o b j e c t i v e of t h e
t e s t s i s t o r e s o l v e t h e u n c e r t a i n t y i n p r e d i c t i o n of protuberance h e a t ing e f f e c t s i n r e g i o n s where t h e i n d i v i d u a l protuberance e f f e c t s o v e r l a p
o r i n t e r s e c t w i t h a d j a c e n t protuberances.
In addition, the t e s t i s
designed t o v e r i f y t h e thermal environment r e s u l t i n g from t h e a d d i t i o n
of a n t i - f l u t t e r h a t s e c t i o n s on t h e S-IVB s t a g e . The t e s t s a r e t o be
run i n t h e Langley Research c e n t e r ' s U n i t a r y P l a n Wind Tunnel. Work on
t h e protuberance models and n e c e s s a r y m o d i f i c a t i o n of t h e t e s t p l a t e i s
being done a t MSFC. The Boeing Company i s providing e n g i n e e r i n g s u p p o r t .
2.
High Angle-of-Attack T e s t s
An RFQ has been i s s u e d t o provide e n g i n e e r i n g s u p p o r t f o r
wind t u n n e l t e s t i n g of a S a t u r n I B con£ i g u r a t i o n a t h i g h a n g l e s of
a t t a c k (15"-25"). The o b j e c t i v e of t h e t e s t i s t o provide aerodynamic
h e a t i n g d a t a on a S a t u r n c o n f i g u r a t i o n a t a n g l e s of a t t a c k which would
be encountered d u r i n g b o o s t i n t o a p o l a r o r b i t . T e s t i n g i s planned f o r
t u n n e l A a t AEDC a t a d a t e y e t t o be determined. C o n s t r u c t i o n of t h e
model by MSFC i s e s s e n t i a l l y complete. Work i s c o n t i n u i n g in-house on
a d a t a r e d u c t i o n scheme t o be used a s a back-up t o t h e one r e q u e s t e d of
the contractor.
3.
Strap-on Heating T e s t
The aerodynamic h e a t i n g e f f e c t s a s s o c i a t e d w i t h t h e proposed a d d i t i o n of Minuteman s o l i d motors t o t h e S-IB s t a g e i s being
i n v e s t i g a t e d . Plans a r e b e i n g formulated i n c o n j u n c t i o n w i t h C h r y s l e r
Corporation personnel t o t e s t a s t r a p - o n motor model a t Langley Research
�Center u s i n g t h e t e s t p l a t e b u i l t f o r protuberance t e s t i n g . It i s
cspcctcd t h a t aerodynamic h e a t i n g d a t a f o r the v e h i c l e and the s t r a p - o n
mounting s t r u c t u r e can be obtained r a p i d l y and inexpensively t h i s way.
T e s t i n g i s planned f o r l a t e 1967.
4.
Compression Corner Heating
The h e a t i n g p r e d i c t i o n techniques i n a compression c o r n e r ,
p a r t i c u l a r l y w i t h s e p a r a t e d flow, c o n t i n u e t o be h i g h l y u n s a t i s f a c t o r y .
An e f f o r t has been undertaken t o make a comprehensive survey of t h e
l i t e r a t u r e i n t h e hope of d i s c o v e r i n g , i n t h e myriad of r e p o r t s a l l u d i n g
t o t h e i n v e s t i g a t i o n of compression corner e f f e c t s , some r e s u l t s wh.ich
would a l l e v i a t e the inadequacy. U n f o r t u n a t e l y , t h e amount of h e a t i n g
d a t a i s s c a n t y , and i t was n o t p o s s i b l e t o make any s e n s i b l e c o r r e l a t i o n
between t h o s e which were a v a i l a b l e . It i s f e l t t h a t a worthwhile t e s t
program designed t o c o r r e c t t h e d e f i c i e n c i e s encountered would be of such
magnitude a s t o be u n f e a s i b l e a t t h i s time. A r e p o r t documenting t h e
l i t e r a t u r e s e a r c h i s being prepared.
5.
Voyager Thermal Environments
Work i s continuing on thermal environment a n a l y s e s f o r t h e
S a t u r n VIVoyager. The a n a l y s i s f o r t h e a s c e n t p o r t i o n i s completed and
has been published i n Memo R-AERO-AT-5-67, June 1 2 , 1967. Work on t h e
e a r t h o r b i t a l p o r t i o n i s e s s e n t i a l l y complete, and t h e a n a l y s i s of t h e
i n t e r p l a n e t a r y p o r t i o n i s w e l l underway.
6.
P r e c u r s o r R a d i a t i o n Study
Work has begun t o a n a l y z e t h e p r e c u r s o r e f f e c t i n a h i g h
e n t h a l p y gas stream. The i n i t i a l e f f o r t i s d i r e c t e d toward e s t a b l i s h i n g
t h e r a d i a t i o n e m i t t e d by helium-hydrogen s l a b s w i t h dimensions and prop e r t i e s t y p i c a l of shock l a y e r s around J u p i t e r e n t r y v e h i c l e s .
7.
J o v i a n Entry Probe
A s t u d y t o determine t h e h e a t p r o t e c t i o n requirements of a
J u p i t e r e n t r y probe i s being i n i t i a t e d . Best e s t i m a t e s of t h e J o v i a n
atmosphere w i l l b e used i n c o n j u n c t i o n w i t h v a r i o u s h e a t i n g p r e d i c t i o n
techniques t o o b t a i n r e a l i s t i c h e a t p r o t e c t i o n requirements. O b j e c t i v e s
of t h e s t u d y a r e t o e s t i m a t e s u r v i v a b i l i t y , i n d i c a t e t h e r e q u i r e d t r a j e c t o r y shaping f o r low h e a t i n p u t , and e s t i m a t e the e x t e n t of RF
a t t e n u a t i o n communication problems. The r e s u l t s of t h e p r e c u r s o r r a d i a t i o n s t u d y w i l l be a p p l i e d a s a v a i l a b l e .
�8.
Odyssey Thermal A n a l y s i s
A d d i t i o n a l work i s b e i n g performed t o b e t t e r d e f i n e t h e
tllermal e n v i r o n m e n t of t h e Odyssey Experiments Package. S p e c i f i c a l l y ,
t h e o r b i t which p r o d u c e s t h e maximum t e m p e r a t u r e g r a d i e n t s w i l l b e
d e t e r m i n e d , e f f e c t s of d i f f e r e n t m a t e r i a l s a n d / o r s u r f a c e f i n i s h e s w i l l
b e i n v e s t i g a t e d , and e f f e c t s of d i f f e r e n t s p i n r a t e s w i l l be s t u d i e d .
9.
Des i g n A s s u r a n c e
A g e n e r a l a n a l y s i s of e x h a u s t plume c o n v e c t i v e h e a t i n g
e n v i r o n m e n t s d u r i n g S a t u r n V l i f t - o f f h a s b e e n documented.
This
a n a l y s i s d e f i n e s t h e c o n v e c t i v e h e a t i n g caused by t h e s e a l e v e l S-IC
e x h a u s t f l o w f i e l d impinging a g a i n s t a f l a t p l a t e and v a r i o u s s i z e s of
cy L i n d e r s and s p h e r e s .
A p r e l i m i n a r y a n a l y s i s was completed which d e f i n e d e x h a u s t
plume impingement a r e a s on t h e LUT d e c k . An i n v e s t i g a t i o n was a l s o
made o f t h e c o o l i n g p o t e n t i a l o f w a t e r (50,000 GPM) o n t o t h e LUT d e c k .
P r e l i m i n a r y r e s u l t s show t h a t t h e w a t e r s h o u l d p r o v i d e more t h a n a d e q u a t e
c o o l i n g ; however, l o c a l " h o t s p o t s " on t h e d e c k s u r f a c e w i l l o c c u r .
P r e l i m i n a r y s t r u c t u r a l and component t e m p e r a t u r e s and p r e s s u r e s f o r t h e LUT deck and wind damper were r e l e a s e d i n C o o r d i n a t i o n
Preliminary review of
S h e e t s ATT-E.1-044 and ATT-H-046, r e s p e c t i v e l y .
t h e s t r u c t u r a l t e m p e r a t u r e s by t h e S t r e n g t h and V i b r a t i o n s S t r e s s Group
has i n d i c a t e d o n l y l o c a l warping of t h e deck panels d u r i n g launch.
T h i s a n a l y s i s n e g l e c t e d t h e e f f e c t s o f w a t e r on t h e deck. The component
s t u d y h a s i n d i c a t e d t h a t a number of t h e components on t h e wind damper
exceed t h e i r d e s i g n o p e r a t i n g t e m p e r a t u r e . The MGSE T r a n s p o r t a t i o n and
H a n d l i n g Group i s e v a l u a t i n g t h i s c o n d i t i o n and a s s e s s i n g t h e amount of
refurbishment necessary a f t e r each launch.
A p r e l i m i n a r y a n a l y s i s was performed t o e v a l u a t e t h e
e f f e c t of d e l e t i n g t h e S-IC r e t r o - m o t o r s on f i r s t p l a n e s t a g i n g e n v i r o n m e n t s . R e s u l t s of t h e t h e r m a l a n a l y s i s a r e r e p o r t e d i n Boeing Coordinat i o n S h e e t G&C-H-061, d a t e d J u n e 1 4 , 1967.
F.
Unsteady Aerodynamics Branch
1.
I n f l i g h t F l u c t u a t i n g P r e s s u r e and A c o u s t i c Environments
a.
The s u p e r s o n i c phase (M = 1 . 6 t o 3 . 0 ) o f t h e 4 p e r c e n t
S a t u r n V f l u c t u a t i n g p r e s s u r e t e s t t h a t was conducted i n t h e AEDC 1 6 - f o o t
wind t u n n e l h a s been completed. Data r e d u c t i o n f o r t h i s phase o f t h e
s t u d y i s p a r t i a l l y complete.
�b.
Reduction of t h e f l u c t u a t i n g p r e s s u r e d a t a from t h e
t r a n s o n i c p o r t i o n 01 t h e AEDC e x p e r i m e n t i s a t t h e f o l l o w i n g s t a g e s :
( I ) O v e r a l l sound p r e s s u r e l e v e l s have been computed and p l o t t e d and
a r e b e i n g r e v i e w e d ; (2) s p e c t r u m a n a l y s i s of t h e a v a i l a b l e d a t a i s
b e i n g c o n t i n u e d ; and ( 3 ) a c o n t r a c t w i t h Baganoff A s s o c i a t e s , I n c . t o
p e r f o r m t h e c o r r e l a t i o n a n a l y s i s of t h e AEDC d a t a has been o b t a i n e d .
2.
Launch S i t e A c o u s t i c Environments
a . The n o i s e s o u r c e c h a r a c t e r i s t i c s e x p e r i m e n t b e i n g p e r formed under Wyle C o n t r a c t NAS8-21060 ( I n v e s t i g a t i o n of t h e Noise
G e n e r a t i o n Mechanisms of D e f l e c t e d and U n d e f l e c t e d S u p e r s o n i c Rocket
E x h a u s t ) h a s been completed. Data r e d u c t i o n and a n a l y t i c a l a n a l y s i s of
the acoustic data a r e i n progress.
b.
A c o u s t i c d a t a from AMTF
t e s t s a r e being analyzed t o determine t h e
d i f r e r e n c e s on t h e a c o u s t i c environment.
completed, and now a complete s e t of d a t a
cone e n g i n e n o z z l e t e s t s .
on t h e b e l l - c o n e e n g i n e n o z z l e
e f f e c t s of t h e n o z z l e e x p a n s i o n
A d d i t i o n a l t e s t s have been
has been o b t a i n e d f o r t h e b e l l -
c.
Data from t h e planned c l u s t e r t e s t s have n o t y e t b e e n
r e c e i v e d b e c a u s e of T e s t L a b o r a t o r y s c h e d u l i n g problems.
T h i s informat i o n i s e x p e c t e d w i t h i n two months t o a l l o w a more thorough e v a l u a t i o n
o f t h e e f f e c t s of e n g i n e f l o w p r o x i m i t y . A c o u s t i c d a t a from s i n g l e
e n g i n e t e s t s w i t h t h e e x i t p r e s s u r e a s a v a r i a b l e have n o t y e t been
acquired.
d.
The 1 1 2 0 t h s c a l e model of t h e S a t u r n V i n v o l v i n g phase
c o r r e l a t i o n s f o r t h e s i m u l a t e d v e h i c l e s k i n i s complete and i s a w a i t i n g
i n s t r u m e n t a t i o n checkout.
The microphones, j u s t r e c e i v e d from LTV, have
n o t r i g i d l y met s p e c i f i c a t i o n s b e c a u s e t h e y were more v i b r a t i o n s e n s i t i v e
t h a n e x p e c t e d . This problem i s b e i n g c o r r e c t e d and t e s t s a r e e x p e c t e d
w i t h i n s e v e r a l months.
e.
The j e t impingement t e s t d a t a have been r e q u e s t e d f o r
t h i r d - o c t a v e band s p e c t r a l a n a l y s i s and time h i s t o r y p r e s e n t a t i o n .
S e v e r a l t e s t s which a r e l a c k i n g f o r c o m p l e t i o n of t h e program a r e
e x p e c t e d t o be performed soon.
f.
A m e e t i n g was h e l d June 22 w i t h R-AS-VGand t h e cont r a c t o r s (Douglas and IBM) t o d i s c u s s t h e MLV con£ i g u r a t i o n s o f t h e
S a t u r n IB. A r e q u e s t was t h e n made of R-AERO-AU t o p r o v i d e a c o u s t i c
This environmental
environments f o r s p e c i f i c v e h i c l e con£ i g u r a t i o n s
i n f o r m a t i o n was f u r n i s h e d i n memo R-AERO-AU-67-63 "Response t o Request
f o r A c o u s t i c Environment f o r S a t u r n IB MLV C o n f i g u r a t i o n s , ' ' August 1,
1967. S p e c t r a and o v e r a l l SPL v a l u e s were p r o v i d e d f o r on-pad and
i n f l i g h t c o n d i t i o n s f o r MLV c o n f i g u r a t i o n s of a s i n g l e 260-inch s o l i d
p r o p e l l a n t b o o s t e r and a l s o f o r f o u r 156-inch s o l i d p r o p e l l a n t r o c k e t s
making up t h e b o o s t e r
.
.
�g . A m e e t i n g was held a t Michoud w i t h C h r y s l e r p e r s o n n e l
c o n c e r n i n g t h e three-month s t u d y o f s t r a p - o n Minuteman s o l i d r o c k e t
motor t h r u s t a u g m e n t a t i o n f o r tlie S a t u r n I B v e h i c l e . The a c o u s t i c
environment, which i s q u i t e s e v e r e f o r p o r t i o n s of t h e v e h i c l e i n
c e r t a i n s t r a p - o n c o n f i g u r a t i o n s , i s t o be p r e d i c t e d by C h r y s l e r .
P r o g r e s s i n t h a t a r e a was r e v i e w e d ; t h e o n l y problem of c o n c e r n t o b o t h
t h e s t r u c t u r a l and a c o u s t i c a r e a s was t h a t KSC had s u g g e s t e d t h a t t h e
SRM s t r a p - o n s b e a t t a c h e d a t somewhat h i g h e r p o i n t s on t h e v e h i c l e t h a n
was p r a c t i c a l from t h e s t r u c t u r a l v i e w p o i n t . This was due o n l y t o KSC'S
l o c a t i o n o f t h e d e f l e c t o r s f o r t h e SRM's f l o w s . It was hoped t h a t KSC
c o u l d s o l v e t h e i r d e f l e c t o r problems and p e r m i t t h e s o l i d s t o b e lowered
s o t h a t t h e d i s t a n c e between t h e n o z z l e p l a n e s o f t h e S-IB and SRM's
would b e m i n i m i z e d , t h u s r e d u c i n g t h e a c o u s t i c problems i n l o c a l a r e a s
t o t h e f l o w and a l l e v i a t e c e r t a i n a t t a c h m e n t d i f f i c u l t i e s .
A memorandum, "J-2X Program A c o u s t i c Data A c q u i s i t i o n , "
h.
d a t e d J u l y 1 4 , 1967, was s e n t t o T e s t Lab r e q u e s t i n g t h e s p e c i f i c t e s t s
t o b e m o n i t o r e d f o r a c o u s t i c d a t a on t h e f u l l s c a l e h o r i z o n t a l J-2(X)
e n g i n e f i r i n g . T e s t s o f chamber p r e s s u r e v a l u e s down t o 5 0 p s i and up
t o 750 were r e q u e s t e d a l o n g w i t h t h e t h r o t t l a b l e r u n s t h a t a r e s c h e d u l e d
f o r e n g i n e e x p a n s i o n r a t i o s of 1 4 : 1 , 2 7 . 5 : l and 4 0 : l .
F l i g h t a c o u s t i c d a t a from AS-201, 202 and 203 have
b e e n r e r u n by Comp Lab u s i n g t h e c o r r e c t RACS c a l i b r a t i o n s i g n a l . The
program f o r a c o u s t i c d a t a a n a l y s i s p r e v i o u s l y h a v i n g e r r o n e o u s b a n d w i d t h
v a l u e s h a s b e e n c o r r e c t e d and now a p p e a r s t o b e o p e r a b l e .
i.
j.
The model t e s t s f o r t h e m u f f l e r scheme f o r t h e High
Reynolds Number T e s t Equipment have b e e n completed. S e v e r a l t e s t s
i n v o l v i n g ground c o v e r a g e f o r a p o r t i o n of t h e s p h e r e were c o n d u c t e d ,
and t h e d i r e c t i v i t y of t h e a c o u s t i c f i e l d a b o u t t h e s p h e r e was a l s o
a c q u i r e d d u r i n g s e v e r a l t e s t s . The d a t a a r e b e i n g a n a l y z e d and a
r e p o r t i s forthcoming .
k.
The r e v i e w copy of a t e c h n i c a l n o t e " F a r - F i e l d A c o u s t i c
E n v i r o n m e n t a l P r e d i c t i o n s f o r Launch o f S a t u r n V and a S a t u r n V MLV Conf i g u r a t i o n " h a s b e e n c o r r e c t e d and h a s b e e n forwarded f o r f i n a l p r i n t .
1.
A c o o r d i n a t i o n m e e t i n g w a s h e l d among p e r s o n n e l o f
MSFC and Langley R e s e a r c h C e n t e r on J u l y 1 9 , 1967 t o d i s c u s s a p o s s i b l e
c o o r d i n a t i o n e f f o r t i n t h e a r e a of a c o u s t i c s c o n c e r n i n g problems a s s o c i a t e d w i t h t h e s u p e r s o n i c t r a n s p o r t (SST). Problem a r e a s o f main conc e r n a r e t h e s u p p r e s s i o n o r r e d u c t i o n of t h e j e t e x h a u s t n o i s e , p r e d i c t i o n
methods, s t a n d a r d i z e d methods of s p e c i f y i n g j e t e n g i n e n o i s e , p r i m a r y
n o i s e g e n e r a t i n g mechanisms o f j e t e n g i n e f l o w s , and h a z a r d c r i t e r i a .
�m.
A r e q u e s t was r e c e i v e d from P&VE ( J u l y 28) f o r t h e
a c o u s t i c environments f o r t e n MLV c o n f i g u r a t i o n s f o r b o t h S a t u r n I B and
S a t u r n V.
Because the r e s u l t s were r e q u i r e d w i t h i n one week, t h e
v e h i c l e s were d i v i d e d i n t o zones f o r convenience of p r e d i c t i o n . Maximum o v e r a l l sound p r e s s u r e l e v e l s were g i v e n per zone f o r b o t h i n f l i g h t
and on-pad c o n d i t i o n s . The magnitude of t h e work was enormous f o r pres e n t i n g s p e c t r a f o r each zone f o r a l l t e n v e h i c l e s w i t h i n one week;
t h e r e f o r e , t h e more d e t a i l e d environments a r e t o be provided on r e q u e s t
For t h e more l i k e l y c a n d i d a t e s f o r t h e MLV program (Reference memo
R-AER~-AU-~~-~~).
3.
A e r o e l a s t i c C h a r a c t e r i s t i c s of S a t u r n I B and V
a.
P i t c h Damping
Because of s i g n i f i c a n t s 1ippage of t h e MSFC 14- i n c h
t u n n e l s c h e d u l e , p i t c h damping t e s t s on SA-203 and 206 forebody conf i g u r a t i o n s w i l l n o t begin u n t i l . mid-Augus t 1967. Furthermore, t h e
proposed aerodynamic p i t c h damping t e s t s of t h r e e - c o n e - c y l i n d e r bodies
have been removed from t h e p r e s e n t s c h e d u l e .
b.
Quasi-Steady O s c i l l a t i n g Wake Study
The f o u r t h phase of t h i s s t u d y i s scheduled t o begin
i n t h e l a t t e r p a r t of September 1967. Included i n t h i s phase i s a n
e x t e n s i v e c a l i b r a t i o n , which w i l l be made i n s u p p o r t of e a r l i e r t e s t s .
A d d i t i o n a l t e s t s using a f r e e - o s c i l l a t i o n b a l a n c e w i l l be r u n .
c.
F l u t t e r and Divergence
A f e a s i b i l i t y s t u d y i s being made t o determine t h e
p o s s i b i l i t y of running a p a r a m e t r i c t e s t t o a s c e r t a i n t h e t o r s i o n a l
f l u t t e r and divergence c h a r a c t e r i s t i c s of t h e S a t u r n I B Minuteman s t r a p ons. I f p o s s i b l e , a e r o e l a s t i c a l l y s c a l e d models w i l l be used i n t h e
MSFC 14-inch wind t u n n e l .
d.
Panel F l u t t e r
An i n v e s t i g a t i o n of n o n l i n e a r o s c i l l a t i o n s of a t h r e e dimensional f l u t t e r i n g p l a t e i s underway f o r S a t u r n I B v e h i c l e s 204 t o
207 using the E . H. Dowell a n a l y t i c a l method. The problem of two- and
three-dimensional p l a t e s i n a s u p e r s o n i c flow undergoing l i m i t o s c i l l a t i o n s has been s t u d i e d by Dowell over a c o n s i d e r a b l e range of Mach
numbers, a i r - t o - p l a t e - m a s s r a t i o s , and p l a t e - l e n g t h - t o - w i d t h r a t i o s .
The p r e s e n t s t u d y involves t h e a p p l i c a t i o n of t h e n o n l i n e a r p l a t e t h e o r y
and the f u l l y l i n e a r i z e d aerodynamic t h e o r y of ow ell's method t o l a r g e r
c h a r a c t e r i s t i c v a l u e s which e x i s t f o r t h e S a t u r n IB v e h i c l e .
�4.
S a t u r n V Ground Winds
The t h r e e - p a r t ground wind t e s t program a t Langley on models
01 t h e MET t o w c r , t h e PIobile S e r v i c e S t r u c t u r e , and t h e S a t u r n V was comp l c t c d J r ~ n c 16, 1967.
Tllc S a t u r n V model t e s t program, a v e r y s h o r t o n e ,
was t o d c t c r m i n c i f tllc dynamic r e s p o n s e o f t h e were s i g n i f i c a n t l y d i f f c r c n t wit11 t h e model s u b j e c t e d t o b o t h a u n i f o r m and a nonuniform ( v e r y
l a r g e boundary l a y e r ) wind p r o f i l e . The nonuniform wind p r o f i l e was
e s t a b l i s h e d by u s e of a g r i d i n s t a l l e d i n t h e t u n n e l ; however, L a n g l e y
p e r s o n n e l a r e a n a l y z i n g t e s t d a t a t o d e t e r m i n e t h e e x a c t boundary l a y e r
p r o f i l e . Although problems were e n c o u n t e r e d w i t h m a i n t a i n i n g a c o n s t a n t
v a l u e o f model damping d u r i n g t h e t e s t program, i t can b e concluded from
p r e l i m i n a r y d a t a a n a y s e s t h a t t h e model dynamic l o a d s were n o t r e d u c e d
wit11 t h e nonuniform wind p r o f i l e .
In f a c t , the t e s t data indicate the
p o s s i b i l i t y of t h e dynamic l o a d s b e i n g l a r g e r w i t h t h e nonuniform p r o f i l e
o v e r t h e l o a d s w i t h t h e u n i f o r m wind p r o f i l e .
A c o n t r a c t was n e g o t i a t e d t h e l a s t o f J u n e f o r d e s i g n and
f a b r i c a t i o n of a S a t u r n ~ I V o y a g e rground winds model, The f a b r i c a t i o n
s h o u l d b e completed i n December 1967. A l s o , t h e e l e c t r o m a g n e t i c damper
s y s t e m w i l l b e m o d i f i e d f o r i n s t a l l a t i o n i n t h e Voyager model.
5.
S a t u r n I B Ground Winds
P r e s e n t l y , t h e S a t u r n I ~ I C e n t a u rground winds model, b u i l t
by A t k i n s and M e r r i l l C o r p o r a t i o n , i s b e i n g checked o u t by Lockheed o f
H u n t s v i l l e t o s e e i f t h e dynamic c h a r a c t e r i s t i c s a r e s u c h t h a t t h e model
c a n b e m o d i f i e d t o r e p r e s e n t t h e AS-204 c o n f i g u r a t i o n . The model w i l l b e
m o d i f i e d by L a n g l e y and wind t u n n e l t e s t t i m e w i l l b e r e q u e s t e d from them.
A l s o , t h e S a t u r n I B / C e n t a u r model w i l l b e used t o c h e c k o u t
and modify t h e e l e c t r o m a g n e t i c damper s y s t e m t o b e used f o r t h e AS-204
and S a t u r n V/Voyager ground wind t e s t s .
IV.
AEROSPACE ENVIRONMENT DIVISION
A.
Atmospheric R e s e a r c h F a c i l i t y
During t h i s p e r i o d , 125 rawinsonde f l i g h t s were made a t t h e
Atmospheric R e s e a r c h F a c i l i t y . These f l i g h t s were made i n s u p p o r t o f
a c o u s t i c s t u d i e s , s t a t i c t e s t s , and t o e s t a b l i s h a s t a t i o n h i s t o r y .
T h e r e were 1 0 f l i g h t s i n s u p p o r t of a c o u s t i c s t u d i e s ; 55 f l i g h t s were
made i n s u p p o r t of s t a t i c t e s t s :
37 f l i g h t s f o r t h e F-1 e n g i n e t e s t s ;
17 f o r t h e S-IB t e s t s , and 1 f o r t h e 5 - 2 e n g i n e t e s t . F i f t y - n i n e d a i l y
f l i g h t s were made f o r s t a t i o n h i s t o r y .
�A l 1 m e t e o r o l o g i c a l requirements f o r T e s t ~ a b o r a t o r ys' a c o u s t i c
model f a c i l i t y have been completed. These requirements were t h a t wind
s p e e d , wind d i r e c t i o n , and temperature be measured a t t h e 2-meter,
4-meter, 8-meter, and 16-meter l e v e l s . A l l systems have been checked
o u t and turned over t o T e s t Laboratory personnel f o r o p e r a t i o n .
The CPS-9 Weather Radar components have a r r i v e d a t MSFC w i t h
t h e c x c e p t i o n of t h e azimuth u n i t and the tower assembly hardware k i t s .
The azimuth u n i t was shipped t o t h e A i r ~ o r c e ' sOrdnance Depot f o r
renovation.
The hardware k i t s a r e on o r d e r . MSFC's requirements i n
t h e i n s t a l l a t i o n of t h e r a d a r system have been completed. These r e q u i r e ments were (1) t o provide e l e c t r i c a l power f o r t h e antenna c o n t r o l u n i t ,
( 2 ) t o provide c a b l e r o u t i n g t r a y s from t h e antenna t o t h e console u n i t
and (3) t o provide antenna tower p i e r s w i t h grounding system.
S p e c i a l t e s t s were conducted i n connection w i t h t h e towerp i b a l wind speed comparison s t u d y . A t o t a l of 172 p i b a l r e l e a s e s were
made f o r t h e s e t e s t s
.
Personnel from
r e c o r d i n g equipment and
a c o u s t i c wind measuring
w i l l be o p e r a t i o n a l f o r
t h e Atmospheric Research F a c i l i t y checked
power s u p p l i e s and made minor r e p a i r s t o t h e
f a c i l i t y a t Kennedy Space Center. The f a c i l i t y
t h e n e x t S a t u r n launch.
The m e t e o r o l o g i c a l requirements f o r t h e cross-beam program
were completed. This included t h e mounting and o r i e n t a t i o n of wind
speed and wind d i r e c t i o n s e n s o r s on t h e Army's 400-foot tower l o c a t e d
i n T e s t Area No. 1. These s e n s o r s were mounted on t h e southwest c o r n e r
a t t h e 1 0 0 - f o o t , 200-foot, 300-foot, and 400-foot l e v e l s w i t h t h e wind
d i r e c t i o n s e n s o r o r i e n t a t e d t o magnetic n o r t h . Wind r e c o r d i n g and s i g n a l
c o n d i t i o n i n g equipment were mounted i n t h e c r o s s -beam i n s t r u m e n t a t i o n
van. A l l systems have been checked o u t and a r e o p e r a t i o n a l . O f f i c e
memorandum R-AERO-225-67, "Anemometer I n s t r u m e n t a t i o n f o r Cross-Beam
C o r r e l a t i o n Study," has been d i s t r i b u t e d .
The ionosphere sounding s t a t i o n a r r i v e d a t MSFC from Kennedy
Space C e n t e r . The e n t i r e system has been unpacked and t h e system i s
b e i n g checked o u t . A f t e r t h e checkout, t h e system i s scheduled t o be
mounted i n a van and moved t o t h e o p e r a t i o n s a r e a near B u i l d i n g 4820.
Data a c q u i s i t i o n i s c o n t i n u i n g f o r t h e tower i n t e r f e r e n c e s t u d y
and wind p r o f i l e mapping program from t h e 150-meter m e t e o r o l o g i c a l tower
a t Kennedy Space C e n t e r .
�The maintenance and p r e v e n t i v e maLntenance performed on t h e
tower d u r i n g t h i s p e r i o d i n c l u d e d r e o r i e n t a t i o n o f a l l s e n s o r s and
i n s t a l l a t i o n of n y l o n b u s h i n g s on t h e s e n s o r mounts on t h e cross-arms
The n y l o n b u s h i n g s were i n s t a l l e d i n a n e f f o r t t o e l i m i n a t e c o r r o s i o n
of t h e s e n s o r h o u s i n g s and f r e e z i n g t o t h e mounting b a r .
levels.
B.
.
Dew c e l l s were mounted a t t h e 3-meter, 60-meter, and 150-meter
These w i l l b e used t o measure and r e c o r d dew p o i n t .
Space Environment Branch
" P r e l i m i n a r y Models and Confidence Envelopes f o r t h e Mars
Atmosphere," w r i t t e n by M r . Don K . Weidner was p r e s e n t e d a t t h e second
m e e t i n g of T r a j e c t o r i e s , Performance, N a v i g a t i o n and Guidance Working
Group (Voyager) and a t t h e June 21, 1967, Voyager S c i e n c e P a n e l m e e t i n g .
The model atmospheres p r e s e n t e d i n t h i s paper have been developed f o r
u s e i n t h e s p a c e c r a f t d e s i g n and p l a n n i n g of t h e Voyager program.
F u r t h e r s t u d y i n t h i s a r e a w i l l p r o v i d e model atmospheres t h a t d e f i n e
t h e s e a s o n a l , l a t i t u d i n a l , and d i u r n a l v a r i a t i o n s i n t h e Mars atmosphere
and a l s o w i l l c o n s i d e r t h e e f f e c t of s o l a r c y c l e v a r i a t i o n s i n t h e upper
a t m o s p h e r e . I n g e n e r a t i n g t h e models, a h i g h l y r e f i n e d p l a n e t a r y
atmosphere computer program t h a t may be used f o r any p l a n e t a r y atmosp h e r e was d e v e l o p e d .
T h e o r e t i c a l s t u d i e s c o n c e r n i n g t h e f e a s i b i l i t y of o b t a i n i n g
p l a n e t a r y a t m o s p h e r i c informati.on through vacuum chamber s i m u l a t i o n
e x p e r i m e n t a t i o n a r e c o n t i n u i n g . The most promising p o t e n t i a l e x p e r i ments s t u d i e d t h u s f a r a r e r e l a t e d t o (1) r e a c t i o n r a t e s f o r t h e
v a r i o u s a t m o s p h e r i c chemical p r o c e s s e s , (2) t h e time c o n s t a n t f o r C02
s u b 1 i m a t i o n i n t h e M a r t i a n atmosphere, and (3) t h e r e l a t i o n s h i p between
t e m p e r a t u r e and c o m p o s i t i o n i n t h e upper atmosphere. The r e s u l t s of
t h e s e s t u d i e s w i l l b e used i n d e v e l o p i n g more r e f i n e d p l a n e t a r y
atmospheres.
A h i g h l y r e f i n e d computer program h a s been e s t a b l i s h e d f o r
g e n e r a t i n g p l a n e t a r y atmospheres. Further s t u d i e s r e l a t e d t o p l a n e t a r y
atmospheric processes w i l l provide a d d i t i o n a l refinements. A preliminary
summary of t h i s computer program i s g i v e n i n R-AERO-IN-5-67.
I n f o r m a t i o n r e s u l t i n g from s t u d i e s c o n c e r n i n g t h e r e l a t i o n s h i p s between c o m p o s i t i o n and t e m p e r a t u r e a t h i g h a l t i t u d e s i n p l a n e t a r y
a t m o s p h e r e s h a s been used i n t h e development of more r e f i n e d M a r t i a n
a t m o s p h e r i c models. These models a r e p r e s e n t e d i n TI4 X-53616, " N a t u r a l
Environment Design C r i t e r i a G u i d e l i n e s f o r MSFC Voyager S p a c e c r a f t f o r
Mars 1973 M i s s i o n , ' ' which w i l l be d i s t r i b u t e d i n August 1967. T h i s
document was developed f o r t h e MSFC Voyager Phase C RFR, b u t t h e r e i s
some chance t h a t i t w i l l b e adopted f o r t h e e n t i r e Voyager program by
t h e Voyager P r o j e c t O f f i c e .
�M r . Robert B. Owen s u p e r v i s e d the f i n a l acceptance t e s t s of
tlic cryogcnic d c n s i t o m e t e r . The f i n a l r e p o r t on t h e development of
t h i s gilugc i s due t h c f i r s t .i~eelcof August 1967; t h e gauge i t s e l f w i l l
bc d c l i v c r e d a t a l a t e r d a t e .
Two papers on the r e s i l l t s of t h e thermosphere probe launches
i n January 1967 have been prepared and a r e scheduled t o be p r e s e n t e d
a t the COSPAR meeting i n London t h e l a s t week of J u l y . One paper conc e r n s t h e n e u t r a l p a r t i c l e measurements, w h i l e t h e o t h e r concerns t h e
charged p a r t i c l e measurements. Both s e r i e s of measurements i n d i c a t e
g r e a t e r v a r i a b i l i t y i n t h e upper atmosphere than c u r r e n t models p r e d i c t .
Measurements of n e u t r a l molecular n i t r o g e n a r e s t i l l a f a c t o r of two
o r t h r e e lower than v a l u e s computed from models based on d e n s i t i e s
deduced from the a n a l y s i s of s a t e l l i t e o r b i t a l decay.
Progress on s t u d i e s of t h e f e a s i b i l i t y of performing gass u r f a c e i n t e r a c t i o n experiments i n f l i g h t continues t o be s a t i s f a c t o r y .
A l l t h r e c c o n t r a c t s a r e planned t o be concluded on 20 August 1967.
F u t u r e p l a n s , a t t h e p r e s e n t time, a r e f o r a c o n t i n u a t i o n i n t o a
Phase B s t u d y of a s p e c i f i c f l i g h t experiment which w i l l combine t h e
r c s u l t s of t h e s e t h r e e Phase A s t u d i e s .
The model C4 ionosonde from Cape Kennedy t h a t i s t o be used
i n t h e s tudy on I o n o s p h e r i c Disturbances Associated w i t h S t a t i c T e s t
F i r i n g s has a r r i v e d and i s being t e s t e d b e f o r e i n s t a l l a t i o n i n a
modified van s o t h a t t h e equipment can be used a t b o t h MSFC and Cape
Kennedy a s r e q u i r e d . A n t i c i p a t e d d a t e f o r t h i s equipment t o go i n t o
o p e r a t i o n i s now about August 1 5 , 1967.
N e g o t i a t i o n s f o r the a c o u s t i c g r a v i t y wave experimental program
have been completed and s i t e equipment i s now being modified and i n s t a l l e d .
Thc c r y s t a l c o n t r o l o s c i l l a t o r s a r e being mounted s o t h a t any and a l l
combinations of the t h r e e f r e q u e n c i e s may be used. A d d i t i o n a l f a n s a r e
being i n s t a l l e d i n t h e t r a n s m i t t e r s f o r temperature c o n t r o l . The antenna
tower bases a t b o t h NASA s i t e 1.ocations have been poured, and communicat i o n s equipment and commercial power l i n e s have been i n s t a l l e d . The
antenna towers a r e a t t h e s i t e s and w i l l be e r e c t e d w i t h i n t h e n e x t two
t o t h r e e weeks. P r e l i m i n a r y a n a l y s i s of s i n g l e s i t e d a t a has proved
somewhat i n c o n c l u s i v e f o r t h e p o s i t i v e i d e n t i f i c a t i o n of t r a v e l i n g
i o n o s p h e r i c d i s t u r b a n c e s (TIDs) following s t a t i c t e s t f i r i n g s
The
i n c l u s i o n of two a d d i t i o n a l s i t e s may improve t h i s s i t u a t i o n , b u t t h e
ionosonde r e c o r d s should be of g r e a t h e l p i n i d e n t i f y i n g s m a l l s c a l e
disturbances.
The equipment i s a l s o being r e t r o f i t t e d s l i g h t l y t o
i n c l u d e a means of measuring phase p a t h d i r e c t l y i n s t e a d of t h e r a t e
of change of phase. There i s a l s o t h e p o s s i b i l i t y of o b t a i n i n g a
pulsed-phase sounder which would provide e x c e l l e n t and e x t e n s i v e phase
p a t h r e c o r d s t h a t now appear t o be n e c e s s a r y t o t h e s t u d y .
.
�S o l a r F l a r e P r o b a b i l i t ~ rModels: Methods of developing probable
f l u x energy s p e c t r a f o r s o l a r f l a r e s a r e being s t u d i e d . Our c u r r e n t
method r e s u l t s i n a t o t a l f l u x model f o r missions l a s t i n g n days. I n
a d d i t i o n , we have been examining t h e occurrence of s o l a r f l a r e s i n r e l a t i o n t o tlle g i v e n s o l a r f l a r e index v a l u e s . T e s t s run s o f a r have
i n d i c a t e d t h a t a r e l i a b l e long range (up t o one y e a r ) p r e d i c t i o n technicli~cmay be found f o r l a r g e s o l a r f l a r e s .
More information on t h i s
s cllcme w i l l be forthcoming
.
C.
T e r r e s t r i a l Environment Branch
1.
Reports
a . "Revised Wind S t a t i s t i c s f o r Apollo S p a c e c r a f t Abort
S t u d i e s , " O f f i c e Memorandum R-AERO-YT-19-67, June 1 , 1967.
b. 11A Comparison of Shroud Length S t u d i e s Versus 10-14 km
Wind P r o b a b i l i t i e s f o r Saturn V/Voyager , I 1 Off i c e Memorandum R-AERO-YT21-67, June 2, 1967.
c.
"Frequency D i s t r i b u t i o n s of t h e L a r g e s t Monthly and
t h e L a r g e s t Yearly Mean R e l a t i v e Sunspot Numbers," O f f i c e Memorandum
R-AERO-YT-24-67, June 19, 1967.
.
d
"Frequency Dis t r i b u t i o n s of t h e L a r g e s t Monthly and
t h e L a r g e s t Yearly Mean R e l a t i v e Sunspot Numbers," O f f i c e Memorandum
I<-AERO-YT-25-67, June 19, 1967.
2 . A computer program i s being prepared f o r the t h e o r y of
extreme v a l u e s developed by t h e l a t e E. J . Gumbel f o r use i n g e n e r a t i o n
of t h e o r e t i c a l p r o b a b i l i t i e s of encountering v a r i o u s atmospheric cons t r a i n t s f o r S a t u r n v e h i c l e launches and o p e r a t i o n s a t Cape Kennedy,
Florida.
D
.
Environmental A p p l i c a t i o n s Branch
1.
MSFC1s M e t e o r o l o g i c a l Tower I n t e r f e r e n c e Program
A d r a f t of a r e p o r t on t h e o r e t i c a l flow t h e o r y f o r wind
flow a b o u t NASA's 150-meter m e t e o r o l o g i c a l tower was r e c e i v e d from t h e
c o n t r a c t o r (Boeing Co., H u n t s v i l l e , Ala. ) on June 22, 1967. R-AERO-YE
personnel reviewed t h e r e p o r t , and comments were r e l a y e d t o t h e Boeing
personnel i n a meeting on J u l y 6 , 1967. It i s expected t h a t t h e
t h e o r e t i c a l flow t h e o r y r e p o r t w i l l be made a n appendix t o t h e tower
i n t e r f e r e n c e document t o be published soon.
�2.
Turbulence C h a r a c t e r i s t i c s of NASA's 150-Meter
Meteorological Tower Data
Data now being a c q u i r e d a t NASA's 150-meter m e t e o r o l o g i c a l
tower, 1<SC, Fl oricla, c o n s t i t u t e l>otli r o u t i n e measurements of wind v e l o c i t y , temperature, and o t h e r atmospheric v a r i a b l e s , a s w e l l a s s p e c i a l
measurements of wind speed f o r t h e s t u d y of t u r b u l e n c e c h a r a c t e r i s t i c s .
So f a r , t h i r t y hours of s p e c i a l wind measurements have been a c q u i r e d and
s t o r e d on computer tapes a t t h e MSFC Computation Laboratory. Computer
programs a r e being developed, i n a d d i t i o n t o e x i s t i n g programs, t o
p r o c e s s t h e s e d a t a s o t h a t they may be analyzed by t h e Environmental
A p p l i c a t i o n s Branch (R-AERO-YE) and by t h e Pennsylvania S t a t e U n i v e r s i t y
under C o n t r a c t NAS8-21140.
These t u r b u l e n c e d a t a have been presented t o
v a r i o u s personnel of MSFC. This p r e s e n t a t i o n concerned t h e s p e c t r a l
n a t u r e of t u r b u l e n c e and t h e a n a l y s i s of g u s t f a c t o r .
3.
Gust Factor Analysis
The memorandum R-AERO-YE-10-67, "Some Observed Wind P r o f i l e
C h a r a c t e r i s t i c s from NASA' s 150-m Meteorological Tower, KSC, F l o r i d a , "
dated February 8 , 1967, presented p r e l i m i n a r y r e s u l t s of a n a n a l y s i s
r e l a t i n g g u s t f a c t o r t o h e i g h t and mean wind speed. A more d e t a i l e d
a n a l y s i s t o determine the g u s t f a c t o r t o a h e i g h t of 150 meters was
p r e s e n t e d i n memorandum R-AERO-YE-51-67, "Gust F a c t o r Analysis from Wind
Data Measured d u r i n g September 1966 a t NASA'S 150-m Meteorological Tower
F a c i l i t y , ICSC, F l o r i d a , " dated June 8 , 1967. From t h i s a n a l y s i s , i t can
be concluded t h a t t h e g u s t f a c t o r d e c r e a s e s w i t h h e i g h t and i n c r e a s i n g
wind speed and t h a t a g u s t f a c t o r of 1 . 4 i s a r e p r e s e n t a t i v e d e s i g n v a l u e
f o r winds from t h e ground t o 150 m e t e r s . The a n a l y s i s of t h e g u s t f a c t o r
i s c o n t i n u i n g f o r o t h e r months of d a t a and v a r i o u s time-averaging p e r i o d s
usecl t o d e f i n e t h e mean wind speed.
4.
NASAIASCE V i s i t t o NASA-Langley Research Center
M r . John IJ. Kaufman, R-AERO-YE, a t t e n d e d and p a r t i c i p a t e d
i n a meeting on wind loads on l a r g e s t r u c t u r e s a t NASA-Langley Research
Center, Langley S t a t i o n , Hampton, V i r g i n i a , on June 1 4 , 1967. Personnel
of t h e A e r o e l a s t i c i t y Branch of LRC and members of t h e American S o c i e t y
of C i v i l E n g i n e e r s , S t r u c t u r a l D i v i s i o n , sponsored t h e meeting. M r .
Kaufman gave a b r i e f p r e s e n t a t i o n of NASA's 150-m M e t e o r o l o g i c a l Tower
F a c i l i t y which i s l o c a t e d on M e r r i t t I s l a n d a t Cape Kennedy. This pres e n t a t i o n cons i s ted of a review of t h e tower f a c i l i t y and t h e type of
lower atmospheric d a t a being measured. Much d i s c u s s i o n followed t h e
p r e s e n t a t i o n because of t h e g r o u p ' s i n t e r e s t i n lower atmospheric
c r i t e r i a which can commonly occur a t t h e Saturn v e h i c l e launch s i t e .
�5.
Space A p p l i c a t i o n s Summer S t u d y Program
M r . K e l l y H i l l a t t e n d e d t h e Space A p p l i c a t i o n s Summer S t u d y
Program on J u n e 27-28, 1967 a t t h e N a t i o n a l Academy o f S c i e n c e s i n Woods
Hole, M a s s a c h u s e t t s . M r . H i l l , R-AERO-YE, and M r . Ted P a l u d a n , R-ASTR-IM,
r e p r e s e n t e d MSFC a s o b s e r v e r s a t t h e g e n e r a l b r i e f i n g s by NASA's Program
Managers on OSSA programs. P a n e l p a r t i c i p a n t s i n t h i s s t u d y i n c l u d e d
s c i e n t i s t s , e n g i n e e r s and o t h e r e x p e r t s i n f i e l d s r e l a t e d t o m e t e o r o l o g y ,
e a r t h r e s o u r c e s , geodesy and s e n s o r s f o r s p a c e a p p l i c a t i o n . D r . M o r r i s
T e p p e r , D i r e c t o r , OSSA M e t e o r o l o g i c a l Programs, s t a t e d t h a t a l l m e t e o r o l o g i c a l e x p e r i m e n t s i n t h e T i r o s and Nimbus programs a r e a p p r o v e d .
Although s u r v e y s a r e b e i n g made, no m i s s i o n h a s b e e n approved f o r t h e
e a r t h resources experiments.
6.
J i m s p h e r e Temperature S e n s o r Program
D r . James R . Scoggins and M r . Dennis W . Camp v i s i t e d GCA
C o r p o r a t i o n , Bedford, M a s s a c h u s e t t s , on J u l y 11-12, 1967, t o d i s c u s s t h e
c o n t r a c t (NAS8-20588) under which t h e J i m s p h e r e t e m p e r a t u r e s e n s o r i s
b e i n g d e v e l o p e d , and t o w i t n e s s a f l i g h t d e m o n s t r a t i o n o f t h e s e n s o r .
Problems w i t h b a t t e r i e s , b a l l o o n - b o r n e a n t e n n a , and s e n s o r c a l i b r a t i o n
a r e s t i l l p l a g u i n g t h e development o f t h e t e m p e r a t u r e s e n s o r . The
f l i g h t t e s t of t h e s e n s o r was p a r t i a l l y s u c c e s . ; f u l , and t h e r e were
i n d i c a t i o n s t h a t t h e s e n s o r could b e made t o p e r f o r m s a t i s f a c t o r i l y .
Work i s c o n t i n u i n g , a t t h e GCA C o r p o r a t i o n , on t h e t e m p e r a t u r e s e n s o r .
V.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
O p t i m i z a t i o n Theory Branch
1.
Voyager
a.
Launch V e h i c l e A t t i t u d e C o n t r o l S t u d i e s
An Aero I n t e r n a l Note g i v i n g l a u n c h p r o b a b i l i t y v e r s u s
wind s p e e d f o r S a t u r n ~ / ~ o y a g ev re h i c l e u s i n g a n a t t i t u d e c o n t r o l s y s t e m
is b e i n g p r e p a r e d f o r p u b l i c a t i o n . The l a u n c h p r o b a b i l i t y i s b a s e d on
t h e time d u r i n g a g i v e n l a u n c h p e r i o d t h a t a n a l l o w a b l e windspeed w i l l
n o t b e exceeded. The a l l o w a b l e wind h a s b e e n d e t e r m i n e d as a f u n c t i o n
of s h r o u d l e n g t h , and i s c o r r e l a t e d w i t h t h e wind l e v e l p r o b a b i l i t y f o r
t h e g i v e n l a u n c h windows.
b.
Launch V e h i c l e Load R e l i e f S t u d i e s
(NAS8-21171)
-
Honeywell
O b j e c t i v e : To improve t h e performance of t h e l o a d
r e l i e f c o n t r o l s y s t e m f o r t h e S a t u r n V l ~ o y a g e rd e s i g n e d by Honeywell
under NAS8-11206.
�Work under t h e c o n t r a c t began on June 27, 1967.
I n i t i a l e f f o r t s have c e n t e r e d on t h e c o o r d i n a t i o n of t h e ground r u l e s
of t h e s t u d y , t r a n s m i s s i o n of t h e r e f e r e n c e d a t a , and p r e p a r a t i o n of
computer programs.
c.
S p a c e c r a f t A t t i t u d e Control
A r i g i d body parameter s t u d y d i r e c t e d toward t h e prel i m i n a r y f u n c t i o n a l d e s i g n of t h e Voyager s p a c e c r a f t unpowered f l i g h t
a t t i t u d e c o n t r o l system has been documented.
Further s t u d i e s a r e being
made t o examine t h e low-g s l o s h e f f e c t s on t h i s mode of c o n t r o l .
d.
Lockheed
-
Schedule Or,der /I45
Coordination meetings were h e l d w i t h Lockheed personnel
t o o u t l i n e t h e i r r e s p o n s i b i l i t i e s a s t h e members of t h e s u p p o r t cont r a c t o r team f o r Voyager launch v e h i c l e and s p a c e c r a f t c o n t r o l s t u d i e s .
Lockheed i s reviewing t h e a v a i l a b l e i n £orma t i o n t o i d e n t i f y problem
a r e a s and t o develop schedules f o r t h e programs under c o n s i d e r a t i o n .
e.
Northrop
(1)
-
Schedule Order /I45
Shroud S e p a r a t i o n Study
O b j e c t i v e : Determination of t h e r e l a t i v e t r a j e c t o r i e s of t h e two s p a c e c r a f t , a f t shroud, and S-IVB f o l l o w i n g s e p a r a t i o n
in interplanetary transfer orbit.
A p r e l i m i n a r y s t u d y of t h e a n g u l a r displacements
of t h e f o u r bodies w i t h r e f e r e n c e t o t h e o r i g i n a l v e l o c i t y v e c t o r r e s u l t ing from i n s t a n t a n e o u s , s e q u e n t i a l s e p a r a t i o n of t h e forward s p a c e c r a f t ,
a f t shroud, and a f t s p a c e c r a f t a t d i f f e r e n t i n e r t i a l a n g l e s and d i f f e r e n t
s e p a r a t i o n v e l o c i t i e s has been completed. From t h i s , d e s i r a b l e o r i e n t a t i o n of t h e S-IVB and minimum s e n s i t i v i t y of t h e o r i e n t a t i o n s t o v a r i a t i o n s i n t h e s e p a r a t i o n v e l o c i t i e s . The s t u d y i s proceeding t o i n c l u d e
3 - D e f f e c t s , f i n i t e times between s e p a r a t i o n s , e f f e c t of r e s i d u a l a n g u l a r
r a t e s i n l i m i t c y c l e o p e r a t i o n of t h e S-IVB APS, and d e t e r m i n a t i o n of
t h e v e l o c i t y v e c t o r s and p o s i t i o n s of t h e f o u r bodies two t o f i v e days
a f t e r s e p a r a t i o n ( a t t h e time of t h e f i r s t midcourse c o r r e c t i o n ) .
(2)
Spacecraft T h r u s t Vector Control
O b j e c t i v e : To d e s i g n and a s s e s s t h e performance
of t h r u s t v e c t o r c o n t r o l systems f o r t h e Voyager which o p e r a t e d u r i n g
p r o p u l s i v e maneuvers.
It was p r e v i o u s l y r e p o r t e d t h a t p r e l i m i n a r y s t u d i e s
showed t h a t t h e use of simple a t t i t u d e l a t t i t u d e - r a t e feedback would n o t
meet performance requirements i n t h e presence of expected CG o f f s e t s and
�.
and t h r u s t misalignments
F u r t h e r examination has sholan t h a t t h i s
r e s u l t i s h i g h l y s e n s i t i v e t o t h e magnitude of CG o f f s e t and t h e t h r u s t
lnisalignment assumed
For t h e s m a l l e r CG o f f s e t s and t h r u s t m i s a l ignments used by t h e s p a c e c r a f t c o n t r a c t o r s , a t t i t u d e c o n t r o l i s s u f f i c i e n t ;
t h i s a g r e e s w i t h t h e conclusions of t h e c o n t r a c t o r s . The q u e s t i o n a s t o
wlm t a r e d e s i g n CG o f f s e t s and t h r u s t misalignments should be r e s o l v e d .
.
2.
T r a j e c t o r y Optimization
a . Work on t h e t r a n s f o r m a t i o n of t h e Hamiltonian which
d e s c r i b e s t h e optimal t r a j e c t o r y of a r o c k e t i n a p u r e l y K e p l e r i a n g r a v i t a t i o n a l f i e l d i s c o n t i n u i n g . Numerical c a l c u l a t i o n s i n d i c a t e d t h a t a
b a s i c problem i n t h e t r a n s f o r m a t i o n e x i s t e d . Consequently, a second
t r a n s f o r m a t i o n technique (due t o Hunt) i s being a p p l i e d . I f d i f f e r e n t
r e s u l t s a r e obtained from t h e s e p a r a t e methods, s t u d i e s of t h e r e a s o n s
Tor t h e s e d i f f e r e n c e s w i l l be made. Improved techniques f o r a n e c e s s a r y
i n t e r p o l a t i o n r o u t i n e have been developed. Work on improved numerical
i n t e g r a t i o n techniques i s now under way.
b. A new problem, which t r e a t s t h e s u p e r p o s i t i o n of a
p l a n a r f o r c e f i e l d over a K e p l e r i a n f i e l d , i s being considered. This
problem has been solved a n a l y t i c a l l y by s e p a r a t i o n of t h e HamiltonJ a c o b i e q u a t i o n i n p a r a b o l i c c o o r d i n a t e s . Numerical c a l c u l a t i o n s on
t h e SDA 930 computer have been coupled w i t h a Calcomp p l o t t e r . This
procedure r e s u l t s i n immediate v i s u a l d i s p l a y of d i f f e r e n c e s due t o
changes i n i n i t i a l c o n d i t i o n s of s t r e n g t h of t h e p l a n a r f i e l d .
c.
Northrop
-
Schedule Order #32
O b j e c t i v e : To determine t h e a p p l i c a b i l i t y of funct i o n a l a n a l y s i s t o t h e o p t i m i z a t i o n of a e r o s p a c e v e h i c l e t r a j e c t o r i e s .
The computer program which uses f u n c t i o n a l a n a l y s i s
and i s capable of handling optilnum bang-bang c o n t r o l o p t i o n s has been
checked o u t . S t u d i e s on s o l v i n g two-point boundary v a l u e problems, i n
t h e l a r g e , f o r bang-bang c o n t r o l have been i n i t i a t e d . T h e o r e t i c a l
s t u d i e s f o r improving convergence a r e s t i l l i n p r o g r e s s . Future work
w i l l i n c l u d e completion of t h e p r e s e n t numerical s t u d i e s . Dependent
upon t h e s e r e s u l t s , f u t u r e work w i t h more complex p h y s i c a l models w i l l
be i n i t i a t e d .
d.
North American A v i a t i o n (NAS8-21077)
Orb j e c t i v e :
To d e v e l o p methods of f i n i t e t h r u s t
optimal t r a n s f e r .
The two-body, three-dimensional q u a s i - l i n e a r program
i s b e i n g checked o u t on t h e IBM 360165. Major r e v i s i o n s of c e r t a i n
�s u b r o u t i n c s have bccn r e q u i r e d . Runs a r e now being made on t h e impulsive
t r a n s f e r i n t h e r e s t r i c t e d three-body model. Programming on t h e f i n i t e
t h r u s t , two-dimensional two-body problem i s continuing.
3.
F l i g h t Control
a.
Cornell (NAS8-18054)
O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g
optimal c o n t r o l theory t o t h e s y n t h e s i s of launch v e h i c l e c o n t r o l systems.
P r e l i m i n a r y copies of t h e f i n a l r e p o r t have been r e c e i v e d
A f t e r minor r e v i s i o n , t h e r e p o r t w i l l be d i s t r i b u t e d w i t h a cover memo
o u t l i n i n g t h e r e s u l t s of t h e s t u d y .
b.
Boeing (NAS8-21070)
O b j e c t i v e : To s t u d y t h e a p p l i c a t i o n of t h e S a t u r n V/
Voyager load r e l i e f system and o t h e r load r e l i e f sys tems t o t h e S a t u r n V/
Apollo.
The rigid-body, f r o z e n c o e f f i c i e n t analog s t u d y i s comp l e t e and a hybrid s t u d y of t h e f l e x i b l e , time-varying v e h i c l e i s being
initiated.
Three systems have been s e l e c t e d f o r f u r t h e r study:
normal a c c e l e r a t i o n c o n t r o l , which y i e l d e d a 2 1 p e r c e n t r e d u c t i o n i n
pcalc l o a d s compared w i t h a t t i t u d e c o n t r o l ; t h e system developed by
A s t r i o n i c s w i t h a 25 p e r c e n t load r e d u c t i o n ; and a system w i t h s a t u r a t ing elements i n t h e load r e l i e f loop ( e i t h e r of t h e above) which reduced
t h c load by 30 p e r c e n t . These f i g u r e s a r e f o r t h e r i g i d body s t u d y and
the Apollo d e s i g n wind peaking a t max qa.
O b j e c t i v e : To f u r t h e r i n v e s t i g a t e t h e a p p l i c a t i o n of
t h e s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206.
Under t h i s c o n t r a c t , f l e x i b l e - b o d y e f f e c t s w i l l be
c o n s i d e r e d , some t h e o r e t i c a l a s p e c t s of t h e technique w i l l be inves tig a t e d , and t h e e f f e c t of parameter v a r i a t i o n s w i l l be c o n s i d e r e d .
The c o n t r a c t o r was i n s t r u c t e d t o use t h e S a t u r n V/
Voyager a s h i s s t u d y v e h i c l e because of t h e p o t e n t i a l a p p l i c a t i o n of
Since t h e c o n t r a c t o r
t h i s technique t o t h e Voyager load r e l i e f problem.
MV
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d
a
t
a
,
f
o
r
which
he
had
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a
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i
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t
o
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expected
he did n o t i n c l u d e d a t a r e d u c t i o n i n t h e c o s t e s t i m a t e . However, a n o t h e r
Honeywell d i v i s i o n i s d e s i g n i n g a c u r r e n t l y f e a s i b l e l o a d - r e l i e f c o n t r o l
�system f o r t h e Voyager under NAS8-21171 ( s e e above) and i s having t o do
s i m i l a r d a t a r e d u c t i o n , which was included i n t h e i r c o s t e s t i m a t e . To
avoid d u p l i c a t i o n of e f f o r t and t o avoid i n c r e a s e d funding, t h e inves t i g a t o r on NAS8-21063 has stopped working on t h e c o n t r a c t t o t a k e advantage
of the d a t a r e d u c t i o n being performed under NAS8-21171, and w i l l resume
e f f o r t s upon completion of t h e d a t a r e d u c t i o n . A r e q u e s t f o r e x t e n s i o n
of t h e c o n t r a c t a t no a d d i t i o n a l c o s t has been submitted by t h e
contractor.
B
.
As t r o d ynamics Branch
I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House)
1.
a . Work on t h e g e n e r a t i o n of t h e n i n e t r a j e c t o r i e s f o r
use i n Voyager p r e l i m i n a r y design s t u d i e s has been slowed somewhat by
problems w i t h the i s o l a t i o n r o u t i n e being used. S i x t r a j e c t o r i e s have
been s u c c e s s f u l l y i s o l a t e d ; i t i s planned t o p u b l i s h t h e s e s i x w h i l e
work c o n t i n u e s on i s o l a t i n g t h e o t h e r t h r e e .
b . I n g e n e r a l m i s s i o n a n a l y s i s s t u d i e s , p l o t s have been
completed showing t r a n s f e r t r a j e c t o r i e s f o r t h e 1975, 77, and 79 launch
opportunities.
The t r a j e c t o r i e s were s e l e c t e d t o show v a r i a t i o n s i n
t r a n s f e r geometry which might b e expected a s a r e s u l t of v a r i a t i o n s i n
e a r l y and l a t e launch and a r r i v a l d a t e s . Charts and graphs have been
generated and assembled which w i l l a l l o w d e t e r m i n a t i o n of c o a s t times
needed f o r Type I t r a j e c t o r i e s f o r 1973, 75, 7 7 , and 79 and a l s o Type I1
t r a j e c t o r i e s f o r 1975 and 1977.
c. A program has been developed f o r use on t h e 1130 comp u t e r which w i l l g e n e r a t e i n t e r r e l a t e d parameters a s s o c i a t e d w i t h
t r a d e o f f s t u d i e s on Mars o r b i t s i z i n g . The s t u d y i s intended t o produce t r a d e o f f s which can be made w i t h r e s p e c t t o o r b i t s i z e , a r r i v a l
energy, and o r b i t i n s e r t i o n AV requirements.
This should provide a n
easy method f o r s t u d y i n g t r a d e - o f f s between s c i e n t i f i c and e n g i n e e r i n g
cons t r a i n t s
.
d . An a n a l y s i s of t h e two main s e c u l a r p e r t u r b a t i o n s
( t h e motion of t h e l i n e of a p s i d e s and t h e motion of t h e argument of
p e r i a p s i s ) on t h e o r b i t a l p a t h of a s a t e l l i t e of Mars due t o t h e
Martian o b l a t e n e s s has been conducted, and t h e r e s u l t s published.
A l t i t u d e s a t p e r i a p s i s range from 1000 t o 5000 k i l o m e t e r s , and a l t i tudes a t a p o a p s i s range from 2000 t o 20,000 k i l o m e t e r s .
2.
I n t e r p l a n e t a r y T r a n s i t S t u d i e s (Support C o n t r a c t o r )
a . Work has continued on t h e g r a p h i c a l p r e s e n t a t i o n of
d a t a d e f i n i n g t h e e a r t h launch windows and e a r t h parking o r b i t r e q u i r e ments f o r t h e 1973, 1975, 1977, and 1979 launch o p p o r t u n i t i e s f o r Mars
miss ions u s i n g Type I i n t e r p l a n e t a r y t r a n s f e r s .
�b.
A computer program has been developed by LMSCIHREC f o r
de tcrmining t h e o c c u l t a t i o n c h a r a c t e r i s t i c s of v a r i o u s Mars s a t e l l i t e
o r b i t s and i s being checked o u t . The program uses a s i n p u t s t h e s i x
o r b i t a l elements ( a , e , i, 11, i i , and To) which d e f i n e t h e d e s i r e d Mars
s a t e l l i t e o r b i t , and t h e l a t e s t times of p e r i c e n t e r passage of t h e e a r t h
and sun p r i o r t o t h e epoch d a t ~To. A l l of t h e s e elements a r e d e f i n e d
r e l a t i v e t o a Mars e q u a t o r i a l c o o r d i n a t e system. P l o t r o u t i n e s have
been included which p l o t t h e l a t i t u d e - l o n g i t u d e h i s t o r i e s of the
o r b i t e r , d e f i n i n g t h e r e g i o n s i n which t h e e a r t h , sun, and Canopus a r e
o c c u l t e d . Thus, t h i s computer program i s designed t o permit t h e r a p i d
c a l c u l a t i o n and g r a p h i c a l p r e s e n t a t i o n of t h e o c c u l t a t i o n c h a r a c t e r i s t i c s f o r a wide range of Mars s a t e l l i t e o r b i t parameters.
c . Work has continued on t h e a n a l y s i s of broken-plane
t r a n s f e r s i n a n e f f o r t t o determine t h e f e a s i b i l i t y of modifying some
oE t h e o p e r a t i o n a l s i n g l e - p l a n e computer programs t o c o n s i d e r t h e
broken-plane cases when near-180-degree h e l i o c e n t r i c t r a n s f e r s a r e
encountered.
d.
I n a d d i t i o n t o t h e optimal t r a n s f e r of a v e h i c l e from
a n incoming h y p e r b o l i c o r b i t t o a n e l l i p t i c o r b i t a b o u t Mars, t h e
problem of o p t i m a l l y t r a n s f e r r i n g a v e h i c l e from a s l i g h t l y e c c e n t r i c
parking o r b i t t o a n outgoing h y p e r b o l i c o r b i t w i t h a g i v e n a s y m p t o t i c
v e l o c i t y i s being i n v e s t i g a t e d . To o b t a i n s u f f i c i e n t l y simple equat i o n s , c e r t a i n approximations t o t h e f u e l optimal t r a n s f e r were cons i d e r e d . P r e l i m i n a r y a n a l y s e s have been performed t o f i n d convenient
approximations f o r s o l v i n g t h e r e l e v a n t system of e q u a t i o n s .
e . Copies of t h e r e p o r t documenting t h e v a r i o u s f l i g h t
parameters f o r Type I1 Earth-Mars t r a j e c t o r i e s i n t h e 1973-1979 time
period have been r e l e a s e d and a r e now being reviewed.
f . The c o n s t a n t energy, f l i g h t parameter p l o t s f o r
e n e r g i e s up t o 40 km2/sec2 d u r i n g t h e 1973-1979 time period have been
completed and a r e being reviewed.
3.
United A i r c r a f t Corporation (NAS~-21091)
The l i t e r a t u r e s e a r c h phase of t h e Impulsive T r a n s f e r
Study c o n t r a c t i s almost complete w i t h a c u r r e n t l i s t i n g of a p p r o x i m a t e l y 300 e n t r i e s ; a p r e l i m i n a r y c l a s s i f i c a t l o n of impulsive t r a n s f e r
t o p i c s i s being d r a f t e d . This c l a s s i f i c a t i o n w i l l undoubtedly be subs t a n t i a l l y a l t e r e d b e f o r e r e a c h i n g i t s f i n a l form. However, i t can
s e r v e a s a s t a r t i n g p o i n t i n t h e c l a s s i f i c a t i o n phase of t h e c o n t r a c t .
�C.
Guidance Theory Branch
I.
Si~pport Contract S t u d i c s
a.
Voyager P r o j e c t Support S t u d i e s
P o s s i b l e use of t h e Voyager P l a n e t a r y Vehicle a s a
"kick" s t a g e t o o b t a i n h i g h e r i n j e c t i o n e n e r g i e s i s being s t u d i e d . The
h i g h e r i n j e c t i o n e n e r g i e s would r e s u l t i n longer launch o p p o r t u n i t i e s .
e f f e c t of
using the
the d r i f t
injection
A guidance a n a l y s i s i s being conducted t o determine t h e
t h e l a r g e r d r i f t and d r i f t r a t e s t h a t occur a s a r e s u l t of
load r e l i e f c o n t r o l system d u r i n g high winds. The e f f e c t of
and d r i f t r a t e s w i l l be determined i n terms of payload and
accuracy.
Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange Mu1 t i p l i e r s
b.
The r e s u l t s of t h i s s t u d y a r e being documented.
c.
Quasi-Optimal Guidance Study
S i m p l i f i e d guidance s i m u l a t i o n s t u d i e s have been undertaken. The scheme works extremely w e l l f o r t y p i c a l c u t o f f s u r f a c e s
s u c h a s r , v , 0, i. P r e s e n t l y , a burn-coast-burn o r b i t a l t r a n s f e r
c a p a b i l i t y i s b e i n g developed and checked o u t .
2.
Contracts
a.
Vanderbil t U n i v e r s i t y
Work has continued on o b t a i n i n g s u f f i c i e n t c o n d i t i o n s
f o r t h e extended m u l t i s t a g e Bolza problem w i t h i n e q u a l i t y c o n s t r a i n t s
and c o n t r o l v a r i a b l e s . This work has been d i r e c t e d toward f i n d i n g a
f o u r t h n e c e s s a r y c o n d i t i o n i n a computationally u s a b l e form.
b
.
Lockheed-Rendezvous Guidance
Equations c o r r e c t through f i r s t o r d e r a r e being programmed f o r t h e f i r s t burn. A s e n s i t i v i t y a n a l y s i s of t h e e q u a t i o n s
f o r t h e second burn i n d i c a t e t h a t b o t h t h r u s t d i r e c t i o n and magnitude
need t o be c o n t r o l l e d t o ensure near-optimum rendezvous.
c
.
General P r e c i s i o n
The guidance s i m u l a t i o n computer program developed by
General P r e c i s i o n has been used a l o n g w i t h t h e IGM guidance package
s u b r o u t i n e t o determine on what type of t r a j e c t o r i e s t h e IGM e q u a t i o n s
�a r e inadequate. Also, t h e implementation of t h e quasi-optimal c o n t r o l
technique i s n e a r i n g completion s o t h a t t h i s new approach can be
evaluated.
3.
In-House S t u d i e s
a.
Voyager S t u d i e s
A s t u d y has been i n i t i a t e d t o determine t h e p o s s i b l e
g a i n i n launch o p p o r t u n i t y v i a plane change maneuver w i t h t h e S-IVB.
P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t two o r t h r e e e x t r a days of launch
o p p o r t u n i t y may b e o b t a i n e d .
The impact of t h e h e a v i e r MSFC s p a c e c r a f t weight upon
t h e 73-79 launch o p p o r t u n i t i e s i s being s t u d i e d
.
The Mars o r b i t i n s e r t i o n guidance s t u d y has been
expanded t o i n c l u d e o r b i t i n s e r t i o n of up t o 20° away from p e r i a p s i s .
b . The closed form s o l u t i o n s f o r t h e s t a t e v a r i a b l e s and
t h e Lagrange m u l t i p l i e r s a c r o s s a c o a s t a r c have been i n c o r p o r a t e d i n t o
a computer program t h a t i s designed t o compute o r b i t a l t r a n s f e r s . A t
p r e s e n t , t h e program i s unable t o i s o l a t e t h e s w i t c h i n g times w i t h s u f f i c i e n t a c c u r a c y t o a c h i e v e ccnvergence. The g e n e r a l i z e d s e c a n t i s o l a t i o n procedure may a l l e v i a t e t h i s problem w i t h o u t having t o use extended
p r e c i s i o n f o r the computations.
c . Various forms of t h e boundary e q u a t i o n s i n two-point
boundary v a l u e problems a r e being i n v e s t i g a t e d . Of t h r e e s e t s of t r a n s v e r s a l i t y c o n d i t i o n s d e r i v e d f o r a C 3 c u t o f f s u r f a c e , t h e s i m p l e s t one
w i t h r e s p e c t t o t h e number of a r i t h m e t i c o p e r a t i o n s involved r e q u i r e d
o n l y - 6 , t h e number of i t e r a t i o n s of t h e most complicated one. T h i s
s i g n i f i c a n t r e d u c t i o n i s p a r t l y due t o decreased t r u n c a t i o n and computer
round-off e r r o r s . This idea i s being pursued f o r o t h e r t y p i c a l c u t o f f
surfaces t o obtain similar reductions.
VI.
DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Multi-Projects
1.
Miss i o n P r o f i l e
a.
Rendezvous Guidance
An a n a l y s i s of t h e guidance and phasing problems a s s o c i a t e d w i t h a c h i e v i n g a dual rendezvous of s p a c e c r a f t s has r e v e a l e d
s e v e r a l d i f f i c u l t i e s i n e s t a b l i s h i n g a launch window of any s i g n i f i c a n t
�d u r a t i o n f o r t h e planned AAP m i s s i o n s . The a n a l y s i s assumed a p a s s i v e
o r b i t a l s p a c e s t a t i o n i n a g i v e n o r b i t and two r e s u p p l y l a u n c h v e h i c l e s
i n which one would be manned and t h e o t h e r unmanned.
The o p e r a t i o n a l
p l a n c a l l c d f o r l a u n c h i n g t h e manned c o n f i g u r a t i o n f i r s t i n t o a low
c i r c t t l a r o r b i t (: 120 n.mi.) and l a t e r l a u n c h t h e unmanned v e h i c l e i n t o
a n elliptical p l ~ a s i n go r b i t w i t h t h e manned c o n f i g u r a t i o n t r a n s f e r r i n g
i n t o Lhe unmanned o r b i t a t a g i v e n p o s i t i o n i n t e r c e p t p o i n t . The manned
and unmanned docked c o n f i g u r a t i o n would t h e n a c h i e v e a second rendezvous
w i t h t h e o r b i t a l s p a c e s t a t i o n ( 2 240 n.mi. c i r c u l a r ) . I n d i c a t i o n s a r e
t h a t t h e performance c r i t i c a l manned c o n f i g u r a t i o n could n o t a c h i e v e t h e
r e q u i r e d maneuvers t o g e n e r a t e a l a u n c h window of any s i g n i f i c a n t l e n g t h .
The unmanned l a u n c h v e h i c l e was a n a l y z e d f o r e q u i v a l e n t performance t o
d e t e r m i n e t h e maximum apogee h e i g h t f o r a f i x e d p e r i g e e h e i g h t of 80 n.mi.
t h a t would correspond t o t h e performance r e q u i r e d f o r a g i v e n c i r c u l a r
o r b i t . The e q u i v a l e n t performance f o r a 120 n.mi. c i r c u l a r o r b i t gave
a maximum apogee h e i g h t o f 230 n.mi. and 1 , 5 0 0 n.mi. f o r a 240 n.mi.
circular orbit.
( D G / N ot~h r o p )
b.
6-D E l a s t i c Response S i m u l a t i o n
C o n t r a c t NAS8-18005, w i t h General E l e c t r i c f o r a d a p t i v e
modular a n a l y s i s i s ended a s of J u l y 28, 1967. The c o n t r a c t work has
b e e n t o d e v e l o p a 6-D e l a s t i c r e s p o n s e of t h e l a u n c h v e h i c l e c o n s i d e r i n g
coinpensat i o n networks a n d n o n l i n e a r aerodynamics. V e h i c l e l o a d i n g may
b e o b t a i n e d f o r m a l f u n c t i o n e d f l i g h t such a s e n g i n e o u t . A f i n a l r e v i e w
was h e l d on J u l y 21, 1967, and a rough d r a f t of t h e f i n a l documentation
was d e l i v e r e d . A l l of t h e o b j e c t i v e s of t h i s one y e a r c o n t r a c t have
(DDD/GE)
been accomplished.
B.
Saturn V
1.
Guidance
a.
S a t u r n V Guidance t o E a r t h Synchronous O r b i t
Work has been performed t o d e t e r m i n e t h e optimum i t e r a t i v e g u i d a n c e mode i g n i t i o n time f o r t h r u s t i n g from t h e t r a n s f e r c o n i c
i n t o a n e a r t h synchronous o r b i t w i t h a n i n c l i n a t i o n e q u a l t o 28.5 d e g s .
P r e l i m i n a r y r e s u l t s i n d i c a t e d t h a t i f apogee r a d i u s of t h e t r a n s f e r
c o n i c (Ra) i s v e r y c l o s e t o t h e e a r t h synchronous o r b i t r a d i u s (RESO) ,
t h e i g n i t i o n time f o r t h e apogee burn was n o t c r i t i c a l . The payload i n
e a r t h synchronous o r b i t v a r i e d o n l y s l i g h t l y f o r i g n i t i o n time r a n g i n g
from 200 s e c o n d s b e f o r e t o 25 seconds a f t e r apogee p a s s a g e . However,
i f R, i s g r e a t e r t h a n RESO, t h e maximum payload i n t o o r b i t was o b t a i n e d
by b u r n i n g i n t o t h e f i r s t p o i n t of t h e t r a n s f e r c o n i c and RESO i n t e r section.
(DG)
�b.
S a t u r n V AS-504 Guidance E q u a t i o n s
The f i n a l g u i d a n c e e q u a t i o n s have been r e c e i v e d and
(~G/Boeing)
approved w i t h a q u a l i f y i n g cover l e t t e r .
c.
Guidance Improvements
C o n s i d e r a b l e e f f o r t i s b e i n g expended t o s t r e a m l i n e t h e
I@fe q u a t i o n s s o t h a t t h e y a r e more f l e x i b l e w i t h r e s p e c t t o t a r g e t v a l u e s
r e q u i r e d and t o m i s s i o n s and s o t h a t t h e y a r e i n a form which i s e a s i e r
t o program. A new, more a c c u r a t e g r a v i t y p r e d i c t i o n h a s b e e n s i m u l a t e d
f o r t h e S a t u r n V i n t o e a r t h p a r k i n g o r b i t . Other m i s s i o n s , p a r t i c u l a r l y
w i t h l o n g e r r a n g e a n g l e s t h a n our p r e s e n t l y d e f i n e d m i s s i o n s , a r e b e i n g
i n v e s t i g a t e d . Closed l o o p s i m u l a t i o n s of ~ a m b e r t ' stheorem a s t a r g e t i n g
f o r IGM have been made f o r a few c a s e s . The e q u a t i o n s have been formul a t e d t o a c h i e v e a n e n e r g y c u t - o f f r a t h e r t h a n t o c o n s t r a i n p o s i t i o n and
v e l o c i t y s e p a r a t e l y , which r e d u c e s t h e amount of i n p u t r e q u i r e d .
2.
Dynamics and C o n t r o l
-
S a t u r n V Bending A n a l y s i s
Recent a s s e s s m e n t of t h e s p a c e c r a f t t o r s i o n s t r u t d e s i g n
change and i n c o r p o r a t i o n of dynamic t e s t r e s u l t s i n t o t h e math mode
h a s i n d i c a t e d a need t o r e v i s e t h e bending mode d a t a t o i n c l u d e t h e s e
changes. These changes have b e e n i n c o r p o r a t e d i n t o t h e 3-D math model
by The Boeing Company and checked a g a i n s t dynamic t e s t r e s u l t s . C o r r e l a t i o n between d a t a o b t a i n e d froin t h e math model and dynamic t e s t was
good. The Boeing Company has been committed t o r e l e a s e AS-501 d a t a f o r
one s t a g e a t a time d u r i n g August w i t h a t o t a l document b e i n g r e l e a s e d by
September 11, 1967. Data f o r AS-503 w i l l be r e l e a s e d a s a t o t a l document
by September 7 , 1967.
(~~S/~oeing)
3.
P r o j e c t Information Applicable t o Individual Vehicles
a.
SA-504, F l i g h t Dynamics A n a l y s i s
The i n i t i a l document on SA-504 f l i g h t dynamics a n a l y s i s
has b e e n r e l e a s e d . R e s u l t s of changes a r e shown f o r (1) S-IC f l i g h t
c o n t r o l s y s t e m d a t e d 3 / 2 2 / 6 7 , (2) yaw b i a s d u r i n g l i f t - o f f , and (3)
e n g i n e m i s a l i g n m e n t s based on s t a t i c f i r i n g d a t a .
(~~/Boeing)
b.
501 C o n t r o l S t a b i l i t y R e - e v a l u a t i o n
Runs have been made on t h e c o n t r o l s y s t e m r e - e v a l u a t i o n and t h e documentation i s b e i n g completed. Some d i f f i c u l t y h a s
b e e n e n c o u n t e r e d i n o b t a i n i n g t h e r o o t s f o r t h e l a s t few r u n s on t h i s
s t u d y . T h i s d i f f i c u l t y w i l l n o t a r i s e on f u t u r e s t u d i e s when t h e Q-R
t r a n s f o r m a t i o n t e c h n i q u e i s i n c o r p o r a t e d i n t h e g a i n and phase r o o t
l o c u s program. R e s u l t s show t h a t t h e d e s i g n of t h e 501 c o n t r o l s y s t e m
i s a c c e p t a b l e i n a l l a s p e c t s of f l i g h t i n c l u d i n g bending modes and
propellant oscillations.
(DDD)
�c.
AS-5011s-IVB Low "g" S l o s h
A d r a f t of tile f i n a l documentation of a n a n a l o g s t u d y
on Low 'lg" s 10~11on AS-501 11as been d e l i v e r e d by N o r t h r o p . The purpose
oL t h i s s t u d y was ( 1 ) t o i n v e s t i g a t e t h e S-IVB r i g i d body and s l o s h
b e l u v i o r under l o g "gl' c o n d i t i o n s , ( 2 ) t o i n v e s t i g a t e t h e s y s t e m s t a b i l i t y f o r v a r i o u s i n i t i a l c o n d i t i o n s , and (3) t o compare t h e performance
of a n o n l i n e a r s l o s h model t o t h a t of t h e l i n e a r "spring-mass-damper"
model n o r m a l l y u s e d . R e s u l t s show t h a t , f o r r e s p o n s e v a l u e s e x p e c t e d
i n f l i g h t ( 1 and 2 m e t e r s l o s h a m p l i t u d e ) , t h e l i n e a r model g i v e s s u f f i c i e n t l y a c c u r a t e r e s u l t s t o a l l e v i a t e t h e need f o r l e n g t h y r u n s w i t h
t h e n o n l i n e a r model.
(DDD/Northrop)
d.
S a t u r n V Node Change C a p a b i l i t y
This s t u d y , made t o i n v e s t i g a t e t h e f e a s i b i l i t y of a n
a l t e r n a t e m i s s i o n f o r AS-503, was extended t h i s p e r i o d . The b a s i c p u r pose of t h i s a l t e r n a t e m i s s i o n is t o t e s t t h e r e s t a r t c a p a b i l i t y of
t h e S-IVB w i t h o u t b u r n i n g i n t o t h e h i g h apogee e l l i p s e p r e s e n t l y proposed.
T h i s i s done by u s i n g t h e S-IVB p r o p e l l a n t t o make a p l a n e
changc i n s u c h a way a s t o keep t h e o r b i t a l i n c l i n a t i o n c o n s t a n t and
m e r e l y skew t h e l i n e of nodes. By performing t h i s maneuver a t t h e
b e g i n n i n g of t h e t h i r d o r b i t , a n a t t r a c t i v e b y - p r o d u c t i s o b t a i n e d i n
t h a t t h e r e s u l t i n g ground t r a c k l i e s n e a r t h a t of t h e f i r s t o r b i t ,
improving t h e t r a c k i n g s i t u a t i o n . During t h i s p e r i o d , a n o p t i m i z e d
t r a j e c t o r y and a s s o c i a t e d ground t r a c k was o b t a i n e d f o r t h e node change
maneuver and c o a s t . The 44' node change c a p a b i l i t y o b t a i n e d by t h e
i m p u l s i v e s t u d y was v e r i f i e d i n t h e o p t i m i z e d t r a j e c t o r y . However, two
problem a r e a s were i d e n t i f i e d by t h i s s t u d y . F i r s t , i t was found t h a t
i f t h e S-IVB e x p e r i e n c e d a n e a r l y e n g i n e shutdown, t h e v e l o c i t y magnitude
d u r i n g t h e b u r n was d e c r e a s e d t o t h e p o i n t of c a u s i n g impact i n l e s s
t h a n h a l f a n o r b i t . This problem could be e l i m i n a t e d by c o n s t r a i n i n g
t h e v e l o c i t y d u r i n g t h e b u r n a t t h e expense of r e d u c i n g t h e maximum
node change c a p a b i l i t y . Secondly, t h e yaw s t e e r i n g r e q u i r e d exceeds
t h e p r e s e n t h a r d s t o p s of t h e g y r o p l a t f o r m . T h i s second problem could
p o s s i b l y b e a l l e v i a t e d by a n a z i m u t h b i a s a t l a u n c h . D e t a i l s and r e s u l t s
of t h i s s t u d y were p r e s e n t e d t o t h e FMP m e e t i n g 21. Documentation h a s
been completed.
(DAO)
C.
S a t u r n IB
P r o j e c t Information Applicable t o Individual Vehicles
AS-204 Nose Cone S e p a r a t i o n f o r Abort: A s t u d y of t h e p o s s i b i l i t y of a n e a r l y s e p a r a t i o n of t h e AS-204 n o s e cone b e f o r e l a u n c h of t h e
S-IVB s t a g e p r e m a t u r e l y s h u t down h a s been completed and documented i n
Memorandum R-AERO-DCC-6-67, "AS-204 Nose Cone S e p a r a t i o n f o r A b o r t , "
J u l y 24, 1967. R e s u l t s of t h e s t u d y i n d i c a t e t h a t , f o r e n g i n e s h u t down
�a f t e r 165 seconds of f l i g h t , r e l e a s e of t h e nose cone a f t e r t h r u s t decay
would a l l o w t h e LM t o be launched.
A s i m i l a r s rudy assuming t h a t t h e S-IVB s t a g e engine never
i g n i t e s has bccn initiated. (DCC)
D.
AAP
1.
Cluster
a.
Mission P r o f i l e
(1)
Miss i o n Planning Logic Development
With regard t o m i s s i o n planning, a master p l a n
which can handle a magnitude of AAP miss ions involving a n o r b i t a l workshop has been p a r t i a l l y developed. A f t e r a planned b a s e l i n e m i s s i o n
(beginning of a d u a l launch) any sequence of s i n g l e and d u a l launch may
be used t o complete the mission. The master p l a n i s n o t dependent on
t h e type of o r b i t a l experiments o r any s e t number of v e h i c l e s s i n c e i t
c o n t a i n s o n l y high l e v e l d e c i s i o n s and a c t i o n s of a g e n e r a l n a t u r e . The
m s t e r p l a n comprises a compressed b a s e l i n e , v a r i o u s contingency expans i o n s , and a r a t h e r unique m i s s i o n c o n t i n u a t i o n planning expansion.
Many important c o n s i d e r a t i o n s such a s long and s h o r t CSM o v e r l a p time,
e r e c t i o n of two manned v e h i c l e s f o r a s i n g l e launch, and t h e changing
of unmanned f o r manned payloads on t h e pad a r e covered i n t h e expansion.
Logic has been developed f o r t h e compressed b a s e l i n e m i s s i o n continuat i o n planning. S i n g l e and dual launch ( f o r a manned-unmanned o r d e r )
c o n t i n g e n c i e s s t i l l t o be developed a r e t h e rendezvous and docking d u a l
launch ( f o r unmanned-manned o r d e r ) and o r b i t a l experiment performance
contingcncies. It i s f e l t t h a t f i n a l development of t h i s master p l a n
w i l l r e s u l t i n a v e r y f l e x i b l e and v e r s a t i l e m i s s i o n planning t o o l .
(DAO)
(2)
Uprated S a t u r n I payload Improvement
J-2s Engine I d l e Mode Operation: Completion of
t h i s t a s k has been delayed f o r e x t e n s i v e m o d i f i c a t i o n s r e q u i r e d t o
i n c o r p o r a t e low t h r u s t c a p a b i l i t y i n t o t h e t r a j e c t o r y r o u t i n e . However,
one f a c t which has become e v i d e n t i n t h e s t u d y i s t h a t because of l a r g e
burn times and r e s u l t a n t g r a v i t y l o s s e s , d i r e c t i n j e c t i o n i n t o a 260 n.mi.
o r b i t u s i n g a h i g h - i d l e - h i g h o r h i g h - i d l e mode r e s u l t s i n payload l o s s
r a t h e r than g a i n .
S-IVB R e s t a r t :
This i s being continued by cons i d e r ing t h e payload improvement a s s o c i a t e d w i t h r e s t a r t i n g t h e J- 2s
engine i n o r b i t . The mode which involves a p e r i g e e i n j e c t i o n i n t o a
81 x 260 n.mi. o r b i t and a c o a s t t o apogee i s a t t r a c t i v e s i n c e t h e J - 2 s
�engine does n o t r e q u i r e l a r g e amounts of r e s t a r t p r o p e l l a n t . A d i s c u s s i o n w i t h P&VI;:p r o p u l s i o n personnel r e v e a l e d t h a t the p r o p e l l a n t r e q u i r e d
f o r t h c c i r c u l a r i z a t i o n burn was enough t o i n s u r e r e s t a r t and t h e r e f o r e
p r o p e l l a n t r e s i d u a l s necd n o t be i n c r e a s e d . An e s t i m a t e of 2000 l b s of
~lddccl S-TVD system cquipmcnt i s includecl. A p r e l i m i n a r y e s t i m a t e sllovs,
\tit11 tllis moclc, a n ~lpproximatcg a i n 01 7,300 l b s over d i r e c t i n j e c t i o n .
S-IB S o l i d Strap-Ons: A s t u d y i s under way t o
provide a s c r u t i n y of performance g a i n s by t h e a d d i t i o n of f o u r Minuteman
s o l i d r o c k e t motors t o t h e S-IB s t a g e . I g n i t i o n sequence, n o z z l e c a n t
a n g l e , and j e t t i s o n sequence have been parameterized. Both CSM and
unmanned v e h i c l e s a r e being considered. P r e l i m i n a r y e s t i m a t e s show t h a t
t h e CSM v e h i c l e payload g a i n i s 6700 pounds i n t o a n 81 x 120 MM e l l i p t i c
o r b i t , w h i l e t h e unmanned v e h i c l e g a i n i s 7200 pounds i n t o a 260 NM c i r c u l a r o r b i t . These g a i n s a r e quoted f o r a sequence of two MFI i g n i t e d
a t l i f t - o f f and t h e remaining two i g n i t e d a t 70 seconds. Two MM c a s e s
a r c j e t t i s o n e d a t 85 seconds and t h e remaining two c a s e s remain f i x e d t o
tllc S-IB s t a g e . The f o u r MM were n o t canted w i t h r e s p e c t t o t h e S-IB
c c n t e r l i n c . Performance and o t h e r f 1i g h t mechanics s t u d i e s c o n t i n u e .
(~A~/~hrysler)
(3)
S a t e l l i t e Occultation i n Earth Orbit
A s t u d y has been i n i t i a t e d t o f i n d t h e o c c u l t a t i o n
period of a n e a r t h s a t e l l i t e . The e s s e n t i a l problem solved was t h e
d e t e r m i n a t i o n of t h e o r i e n t a t i o n of t h e s a t e l l i t e ' s o r b i t a l p l a n e r e l a t i v e t o t h e e a r t h - s u n l i n e . The s o l u t i o n t o t h i s problem was t h e n used
t o determine t h e a n g l e through which t h e s a t e l l i t e moved w h i l e i n t h e
e a r t h ' s shadow and, u l t i m a t e l y , t o f i n d t h e f r a c t i o n of t h e t o t a l
o r b i t a l p e r i o d t h a t the s a t e l l i t e was i n t h e s u n l i g h t . The s o l u t i o n
was then programmed i n such a manner t h a t , i f t h e launch time, i n c l i n a t i o n of t h e o r b i t a l plane and c o o r d i n a t e s of t h e launch s i t e were
s p e c i f i e d , t h e t o t a l time i n t h e s u n l i g h t was o b t a i n e d . Regression
of t h e nodal l i n e was a l s o taken i n t o account. This s t u d y i s being
f u r t h e r used i n a subsequent problem, namely, t h a t of s p e c i f y i n g t h e
c o o r d i n a t e s of t h e sun r e l a t i v e t o a s e t of axes f i x e d i n a space
s t a t ion.
(DAO)
(4)
High I n c l i n a t i o n P l a n a r and O r b i t a l Phasing
Launch Windows
This i s a s t u d y of t h e ground launch window and
o r b i t a l phasing r e q u i r e d f o r rendezvous a t high i n c l i n a t i o n s . This work
i s p r i m a r i l y aimed a t d e f i n i n g m i s s i o n plans f o r t h e second c l u s t e r
m i s s i o n . Based upon a t a r g e t body i n s e r t e d i n t o a 260 n.mi. c i r c u l a r
o r b i t and i n c l i n a t i o n of 5 0 ° , a 20-minute ground launch window can be
c r e a t e d f o r a payload t r a d e o f f of 1,000 pounds. This i s t r u e f o r b o t h
n o r t h e r l y and s o u t h e r l y launches; however, t h e n o r t h e r l y f l i g h t s have
�impact p o i n t s i n Newfoundland and Europe, w h i l e t h e s o u t h e r l y l a u n c h e s
v i o l a t e l a r g e r e g i o n s of S o u t h America. I f s o u t h e a s t e r l y l a u n c h e s a r e
r e q u i r e d , l a r g e payload l o s s e s a r e i n c u r r e d by d o g l e g g i n g around t h e
e a s t e r n c o a s t of S o u t h America, and t h e l a u n c h window payload t r a d e o f f
increases greatly.
The o r b i t a l phas i n g r e q u i r e m e n t s f o r l a u n c h opport u n i t i e s (20-minute l a u n c h window) e v e r y day r e q u i r e s from one t o s i x t e e n
r e v o l u t i o n s i n a 120 n.mi. c i r c u l a r p a r k i n g o r b i t .
I f opportunities a r e
chosen e v e r y t h i r d d a y , t h e p h a s i n g r e q u i r e m e n t s can b e k e p t t o l e s s t h a n
8 revolutions.
The i n v e s t i g a t i o n of t h e u s e of e l l i p t i c o r b i t s
(~AO/~orthrop)
t o reduce phasing requirements i s continuing.
(5)
1969 (Second C l u s t e r ) Miss i o n D e c i s i o n L o g i c
Three l e v e l s of m i s s i o n d e c i s i o n l o g i c were p r e s e n t e d a t t h e M i s s i o n P l a n n i n g Task F o r c e Second C l u s t e r Summary Meeting
a t NASA H e a d q u a r t e r s , Washington, D . C . on J u l y 25, 1967. The t h r e e
l e v c l s of l o g i c c o n s i s t e d o f a m a s t e r p l a n ( d e s c r i b e d under a n o t h e r t o p i c
i n t h i s r e p o r t ) , a b a s e l i n e summary and c o n t i n g e n c y c h a r t , and d e t a i l e d
b a s e l i n e and c o n t i n g e n c y d i a g r a m s . The b a s e l i n e summary was a l m o s t a
t r i v i a l consequence of c o n s i d e r i n g s i x v e h i c l e s i n a 2-1-2-1 b a s e l i n e
and a c c o u n t i n g f o r o n l y s i n g l e v e h i c l e f a i l u r e s . The d e t a i l e d b a s e l i n e
c o n t i n g e n c y p o s i t i o n was p a t t e r n e d a f t e r t h e Gemini f l i g h t o p e r a t i o n a l
m i s s i o n l o g i c i n t h a t i t c o n t a i n e d countdown, l i f t - o f f , powered f l i g h t ,
i n j e c t i o n , e t c . However, t h i s second c l u s t e r m i s s i o n l o g i c was more
open-ended s i n c e i t r e p r e s e n t e d a n i n t e r m e d i a t e m i s s i o n l o g i c p h a s e .
During t h i s r e p o r t i n g p e r i o d , DAO and N o r t h r o p developed and p r e p a r e d
(~AO/Northrop)
the presentation material.
(6)
Launch Sequence f o r AAP 1 - 2
A s t u d y h a s b e e n completed on t h e l a u n c h s e q u e n c e
f o r l a u n c h s u c c e s s p r o b a b i l i t y of manned f i r s t v s t h e unmanned f i r s t
mode. The a s s u m p t i o n s used i n t h e s t u d y and t h e r e s u l t s and c o n c l u s i o n s
o f t h e s t u d y a r e p r o v i d e d i n memorandum R-AERO-DAM-10-67.
Briefly, the
s t u d y showed t h a t t h e h i g h e s t l a u n c h s u c c e s s mode i s manned f i r s t . Howe v e r , i f t h e a u x i l i a r y a t t i t u d e c o n t r o l s y s t e m i s added t o t h e unmanned
v e h i c l e , t h e n t h e r e i s no s i g n i f i c a n t d i f f e r e n c e i n l a u n c h s u c c e s s
p r o b a b i l i t y u s i n g e i t h e r mode, i . e . , manned f i r s t v s unmanned f i r s t .
There i s some g a i n i n l a u n c h s u c c e s s i f t h e IU i s m o d i f i e d t o p r o v i d e
g r e a t e r t h a n 7 112 h o u r s l i f e t i m e . However, t h i s g a i n does n o t become
s i g n i f i c a n t u n t i l t h e r e i s a t l e a s t 24 h o u r s a d d i t i o n a l l i f e t i m e s i n c e
(DAM)
t h e l a u n c h windows a r e s e p a r a t e d by 24 h o u r s .
�b.
P r o j e c t I n f o r ~ n a t i o nApplicable t o Many Vehicles
Experimental Determination of the S t a b i l i t y of S p i n n i n g
Cable-Connected Space S t a t i o n s : The moment of i n e r t i a a b o u t t h e p r i n c i p a l
axes of t h e two models were determined e x p e r i m e n t a l l y by t r e a t i n g .each a s
a simplc pendulum. The weight of each of t h e masses t h a t a r e t o be
a t t a c h e d t o t h e models t o v a r y t h e i r moments of i n e r t i a has been d e t e r mined, and each model, w i t h o u t t h e a t t a c h e d masses, weighed a c c u r a t e l y .
Work has begun on making t h e two models a s n e a r l y i d e n t i c a l a s p o s s i b l e
i n order t o coincidc with the e x i s t i n g t h e o r e t i c a l s t a b i l i t y analyses.
Design of a new model has begun because t h e e x i s t i n g models do n o t cover
the f u l l range of d e s i r e d i n e r t i a r a t i o s . A pneumatic c a t a p u l t i s being
f a b r i c a t e d , and arrangements f o r photographic coverage of t h e experiment
have been made. The r e s u l t s of a n a n a l y s i s of t h e pneumatic c a t a p u l t
system i n d i c a t e d t h a t t h e d e s i r e d payload could be launched t o a n
a c c e p t a b l e a l t i t u d e w i t h o u t exceeding t h e d e s i g n p r e s s u r e . The diameter
of t h e r e l i e f o r i f i c e f o r c o n t r o l l e d d e c e l e r a t i o n of t h e launching
mcchanism was a l s o determined. The computer program used t o develop
t h e s c r e s u l t s should be u s e f u l when o p e r a t i o n of t h e launching f a c i l i t y
s t a r t s . The p i s t o n and c y l i n d e r assembly, a s w e l l a s c e r t a i n s m a l l e r
i t e m s , has been d e l ivered t o R-TEST, and f a b r i c a t i o n should b e g i n
soon.
(DDS)
2.
ATM
a.
Docking Dynamics
The g e n e r a l ecluations o f motion f o r two r i g i d bodies
w i t h a p o i n t i n common and coupled by a spring-damper system were
d e r i v e d . The e q u a t i o n s i n c l u d e t h e e f f e c t s a t g r a v i t y - g r a d i e n t t o r q u e s ,
s o l a r p r e s s u r e and aerodynamic t o r q u e s , a s w e l l a s c o n t r o l t o r q u e s . The
programming of t h e s e n o n l i n e a r e q u a t i o n s on b o t h t h e d i g i t a l and a n a l o g
computers i s approximately 60 p e r c e n t complete. The programs a r e being
w r i t t e n i n modular form t o a i d i n parameter s t u d i e s of t h e e f f e c t s of
v a r i o u s c o n t r o l laws and parameters. The e q u a t i o n s , s i m p l i f i e d t o two
dimensions, have been programmed t o provide a check of t h e g e n e r a l program.
A n a l y t i c e x t e n s i o n of t h e two body problem t o i n c l u d e any number of bodies
i s about 50 p e r c e n t complete.
A t h e o r e t i c a l s t u d y of t h e e f f e c t s of e l a s t i c i t y on
v c h i c l e motion d u r i n g docking has begun. This v i b r a t i o n s t u d y i s being
pursued i n terms of g e n e r a l i z e d v a r i a b l e mass and s t i f f n e s s m a t r i c e s f o r
s i n g l e v e h i c l e and i s t o be extended l a t e r t o a coupled system.
(DDD)
�b.
ATM P o i n t i n g Accuracy
Equations of motion f o r t h e ATM have been p a r t i a l l y
d e r i v e d u s i n g 2 and 6 hinged-body models. The problem f a l l s i n t o two
main p a r t s :
1.
S h o r t term behavior:
(a)
(b)
2.
.
(1)
Disturbances :
(2)
Control:
crew motion.
j e t s and moment damping.
E l a s t i c body. Two hinged bodies where body #1
i s e l a s t i c and body # 2 i s r i g i d .
Consider
r o t a t i o n around /I1 and /k3 a x i s .
(1)
Disturbances:
(2)
Control:
t h e same a s i n l a .
t h e same a s i n l a .
Long term behavior:
(a)
3.
Rigid body.
R o t a t i o n i n space of 2 and 6
hinged bodies
Rigid and el-ast i c body. Cons i d e r t r a n s l a t i o n a l
and r o t a t i o n a l motion ( s i x degrees of freedom).
(1)
Dis turbances :
aerodynamics.
(2)
Control:
g r a v i t y t o r q u e g r a d i e n t and
same a s i n l a .
(DDD)
OWS
Active Control S t u d i e s
The i n v e s t i g a t i o n of space v e h i c l e c o n t r o l u s i n g c o n t r o l
moment gyros i s being continued. Liapunov's d i r e c t method i s being used
on t h e s e n o n l i n e a r systems t o o b t a i n g l o b a l l y a s y m p t o t i c a l l y s t a b l e cont r o l laws. The c o n t r o l laws chosen a r e l i n e a r combinations of s t a t e
v a r i a b l e s which a r e modified by t r i g o n o m e t r i c f u n c t i o n s of t h e c o n t r o l
a n g l e d e f l e c t i o n s . This method of a t t a c k g i v e s a means of i d e n t i f y i n g
t h e "damping and s p r i n g c o n s t a n t s " i n t h i s r a t h e r complex n o n l i n e a r
system. U n f o r t u n a t e l y , some of t h e s e c o n t r o l laws i n v o l v e s e c a n t and
t a n g e n t f u n c t i o n s which can become i n f i n i t e f o r a n g l e s of 90 d e g r e e s ,
b u t t h e s e a n g l e s can be avoided by proper a c q u i s i t i o n c o n t r o l using
�c o i i t r o l roclicts.
M o d i l i c a t i o n of t h e c o n t r o l laws t o omit some o f t h e
i~ill,or~ntlc,tlI u n c t ions i s b e i n g programmed l o r d i g i t a l s i m u l a t i o n of t h e
s y s r ~'111.
Work i s c o n t i n u i n g on t h e development of a n in-house program t o do a t t i t u d e c o n t r o l s t u d i e s . The dynamic e q u a t i o n s were
d e v e l o p e d and t h e v a r i o u s c o o r d i n a t e systems were d e s c r i b e d by Lockheed.
T h i s work i s now b e i n g reviewed i n d e t a i l . During t h e development and
debugging o f t h e d i g i t a l program, o n l y p a s s i v e c o n t r o l s t u d i e s have
b e e n r u n . A c t i v e c o n t r o l systems a r e b e i n g s t u d i e d and i n c o r p o r a t e d
i n t o the equations of motion.
A d i g i t a l program h a s been developed by Lockheed t o p e r f o r m
a p a r a m e t r i c s t u d y o f a CMG SIXPAC u n l o a d i n g t e c h n i q u e t h a t u s e s t h e
o u t e r g i m b a l s t o a c h i e v e a l l of t h e d e s a t u r a t i o n .
C o n t r o l law s t u d i e s f o r t h e CMG SIXPAC i n c l u d e a d e t a i l e d
s t u d y o f t h e s t a b i l i t y of a c o m p l e t e l y uncoupled n u m e r i c a l c o n t r o l law.
I f t h i s law h a s a c c e p t a b l e s t a b i l i t y c h a r a c t e r i s t i c s , i t s g a i n c h a r a c t e r i s t i c s w i l l b e compared w i t h some of t h e laws s t u d i e d i n t h e p a s t .
Such a comparison s h o u l d i n d i c a t e t h e major s h o r t c o m i n g s of t h e s e
(~~Al~ockheed)
laws.
E.
Other P r o j e c t s
Drop Tower T e s t s
A s e r i e s o f d r o p tower t e s t s i s b e i n g planned which w i l l e x t e n d
t h e knowledge o f l i q u i d p r o p e l l a n t o s c i l l a t i o n a t Bond numbers l e s s t h a n
10. The r e s u l t s o f t h i s e x p e r i m e n t s h o u l d b e v a l u a b l e f o r a c c u r a t e p r e d i c t i o n o f t h e l i q u i d p r o p e l l a n t dynamics i n t h e Voyager s p a c e c r a f t
d u r i n g i n t e r p l a n e t a r y c o a s t . The models t o b e used a r e ( 1 ) 1 - i n c h
d i a m e t e r s p h e r i c a l , ( 2 ) 2-inch d i a m e t e r s p h e r i c a l , and ( 3 ) 2 - i n c h diame t e r by 4 - i n c h t a l l c y l i n d r i c a l .
The d a t a needed a r e f i l m r e c o r d s of i n t e r f a c e f o r m a t i o n i n
model (1) a t 10-ICgo r l e s s and f i l m r e c o r d s and l a t e r a l f o r c e r e c o r d s
of l i q u i d o s c i l l a t i o n s i n models ( 2 ) and ( 3 ) a t t e s t a c c e l e r a t i o n s o f
10-'lg, 1 0 - ' g , and 10-'g.
(DDS)
�VII.
FLIGHT TEST ANALYSIS DIVISION
A.
Special Projects Office
Saturn V
The S a t u r n V F l i g h t T e s t E v a l u a t i o n P l a n , i s s u e d on J u l y 31,
1967, d e f i n e d t h e o r g a n i z a t i o n and e s t a b 1 i s h e d t h e r e s p o n s i b i l i t i e s and
p r o c e d u r e s f o r f l i g h t e v a l u a t i o n o f v e h i c l e s AS-501 t h r o u g h AS-504.
This
document, which w i l l b e s u b j e c t t o r e v i s i o n 30 days b e f o r e e a c h o f t h e
a f f e c t e d f l i g h t s , i s t o b e used a s a g u i d e l i n e by a l l a g e n c i e s c o n t r i b u t ing t o the t o t a l launch v e h i c l e evaluation.
B.
F l i g h t Mechanics Branch
1.
Saturn I B
The 204 o p e r a t i o n a l t r a j e c t o r y document, R-AERO-FM-136-67,
d a t e d May 1 7 , 1967, h a s b e e n d i s t r i b u t e d . An u p d a t e t o t h e document, which
h a s b e e n completed by CCSD and w i l l b e p u b l i s h e d by mid-August, r e f l e c t s
t h e l a t e s t p r o p u l s i o n p r e d i c t i o n s and t h e 270-degree a t t i t u d e f o r t h e
p r o p e l l a n t dump e x p e r i m e n t .
The r a n g e s a f e t y a n a l y s i s f o r t h e 204/LM-1 m i s s i o n i s
documented i n R-AERO-FMR-151-67, d a t e d J u n e 6 , 1967.
The a b o r t and a l t e r n a t e m i s s i o n document h a s now b e e n
completed and w i l l b e d i s t r i b u t e d b y mid-Augus t .
b.
AS- 205 Rendezvous Miss i o n
A t y p i c a l m i s s i o n p r o f i l e f o r t h e 120 x 150 n a u t i c a l
m i l e e l l i p t i c a l o r b i t h a s b e e n g e n e r a t e d , and t h e S-IB s t e e r i n g f u n c t i o n s and second s t a g e IGM p r e s e t t i n g s have b e e n f i n a l i z e d . The t r a j e c t o r y , which r e f l e c t s t h e l a t e s t mass and p r o p u l s i o n p r e d i c t i o n s , w i l l b e
used f o r a l l p r e l i m i n a r y s t u d i e s . The s p a c e c r a f t w e i g h t used was 36,300
pounds. With t h i s w e i g h t , t h e S-IVB s t a g e u s e a b l e p r o p e l l a n t s a t i n s e r t i o n a r e a p p r o x i m a t e l y 1500 pounds.
C .
AS-206 R e s t a r t
As d i r e c t e d by t h e S a t u r n I B Program Off i c e , t h e o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s , and r a n g e s a f e t y a n a l y s i s a r e
being generated t o support the r e s t a r t mission.
�P r e l i m i n a r y s c h e d u l e s f o r s y s tem e n g i n e e r i n g e f f o r t s
have been e s t a b l i s h e d based on the l a t e s t f l i g h t miss i o n assignment
document.
2.
SaturnV
The r e v i s e d o p e r a t i o n a l
t h e FFOT, has been r e c e i v e d from TBC (26
d i s t r i b u t e d soon. Work i s c o n t i n u i n g on
safety.
The four-engine and f i v e - e n g i n e
t h e Range has been s e n t t o KSC.
t r a j e c t o r y , b e t t e r known a s
J u l y 1967) and should be
an update f o r t h e AS-501 range
t u r n i n g r a t e d a t a r e q u e s t e d by
The 501 D i s p e r s i o n Analysis has been r e c e i v e d from TBC.
F i n a l review i s being made t o check t h e c o r r e c t i o n s which were t o be
i n c o r p o r a t e d by TBC. FMT hopes t o make d i s t r i b u t i o n t h i s week of t h e
d i s p e r s i o n a n a l y s i s r e p o r t i f i t i s a c c e p t a b l e . Problems have a r i s e n
w i t h t h e p r e s e n t " c o n s t a n t low t h r u s t v e n t model" i n t h a t t h e r e is n o t
s u f f i c i e n t p r o p e l l a n t r e s e r v e t o cover t h e 30 low performance u s e s , b u t
s t i l l a l l o w s a h i g h confidence ( - 98.3) i n accomplishing t h e m i s s i o n .
The v e n t model misleads t h e v e h i c l e computer i n how much energy i s necess a r y t o achieve the prescribed waiting o r b i t .
I n a n t i c i p a t i o n of a s l i p i n launch s c h e d u l e , a memo
has been w r i t t e n r e q u e s t i n g t h a t t h e p r e v i o u s l y d e r i v e d t i l t program
f o r w i n t e r winds be implemented f o r a November launch. The a p p l i c a b i l i t y
of t h i s ti1 t program has been checked and found a c c e p t a b l e .
The r e v i s e d t i l t program using average J a n u a r y , February,
and March winds has been completed and t r a n s m i t t e d t o t h e R-AERO-FFR f o r
use i n d i s p e r s i o n a n a l y s i s . A p r e s e t t i n g s r e v i s i o n w i l l be made and d i s t r i b u t e d i n e a r l y August. This r e v i s i o n w i l l c o n t a i n t h e S-IC s t a g e
The Abort
t i l t program and t h e a b o r t and a l t e r n a t e m i s s i o n p r e s e t t i n g s .
and A l t e r n a t e Mission Report was r e t u r n e d t o TBC f o r c o r r e c t i o n s and
should be r e s u b m i t t e d by August 1 5 , 1967.
The D i s p e r s i o n Analysis Rough D r a f t was r e c e i v e d and
has been p a r t i a l l y reviewed. Comments on u n s a t i s f a c t o r y a r e a s which
have been noted i n our c r i t i q u e have been forwarded t o TBC f o r incorporat i o n i n t o t h e document b e f o r e i t i s p r i n t e d .
It i s hoped t h a t t h e r e p o r t
w i l l be found a c c e p t a b l e w i t h o u t any changes when i t i s r e c e i v e d on
August 11, 1967.
�Work has begun on the S-IC s t a g e t i l t program and
on the dcvel opmcnt of a f l i g h t s i m u l a t i o n d a t a deck. There i s a
prol,lcm a s s o c i a t e d with t h c new 503 m i s s i o n i n t h a t a l a r g e amount of
r e s itlria l s remain i n e a r t h parking o r b i t . This causes a problem i n
maintaining a propellant control a s well a s v e h i c l e control f o r t h i s
c a s e . S i n c e t h e problem w i l l reappear and i n f a c t was due t o occur
on 503 f o r l a r g e r e s i d u a l s remaining a t second S-IVB c u t o f f , P&VE has
proposed a second burn f o r t h e S-IVB.
A meeting was h e l d on J u l y 1 3 t o d i s c u s s t h e AS-503
m i s s i o n and t h e second s t a r t of t h e S-IVB s t a g e . The conclusions were
a s follows:
There a r e t h r e e o p t i o n s .
(1) The one favored by
R-AERO-FM i s t o s e p a r a t e from t.he s p a c e c r a f t and have a d u a l r e s t a r t of
the S - I n . As t r i o n i c s s t a t e d a t t h i s time t h a t t h e r e was no problem i n
c o n t r o l l i n g w i t h o u t t h e use of t h e s p a c e c r a f t .
( 2 ) Another proposal
was t o r e s t a r t w i t h t h e s p a c e c r a f t a t t a c h e d and burn f o r a t l e a s t
(3) Another a l t e r n a t i v e was t o burn f o r 40 seconds w i t h
10 seconds.
t h e s p a c e c r a f t a t t a c h e d , and burn t o a 45-degree yaw command and then
s e p a r a t e . A problem w i t h a l l proposals is t o g e t t h e proper t r a c k i n g
and t e l e m e t r y f o r t h e S-IVB second burn.
d
.
Lunar Landing Miss i o n
Our e f f o r t on t h e l u n a r landing m i s s i o n has been p r i marily t o g e t a trans lunar i n j e c t i o n targeting capability a v a i l a b l e a s
soon a s p o s s i b l e . Approximately 60 p e r c e n t of t h e s u b - r o u t i n e s a r e
complete and i n our deck. However, we a r e o n l y comparing and no runs
have been made. We a r e hoping t o have our in-house c a p a b i l i t y r e a d y
f o r checkout by e a r l y August.
A s t a t u s on t h e J u l y t a r g e t i n g e x e r c i s e was g i v e n by
Boeing on J u l y 19. The purpose of t h i s e x e r c i s e i s t o check o u t and
demonstrate t h e c a p a b i l i t y of Boeing t o r e t a r g e t launch v e h i c l e s f o r
a l u n a r m i s s i o n i n two weeks. Boeing e s t i m a t e s t h e y a r e t h r e e days t o
one week behind s c h e d u l e . One of t h e problems i s i n e s t a b l i s h i n g a
proper p1 t e s t f o r t h e six-degrees-of-freedom TLI deck. They can,
however, r e a d and w r i t e e a r t h parking o r b i t i n s e r t i o n s t a t e v e c t o r
t a p e s , r e a d the t a r g e t i n g t a p e , and card punch a TLI of t h e v e c t o r t o
t h e 6D deck.
It i s e s t i m a t e d t h a t Boeing i s approximately 35 t o
40 p e r c e n t complete and e f f i c i e n t i n t h i s a r e a . It i s hoped t h a t f o r
t h e September e x e r c i s e ( e x e r c i s e period number two) we w i l l demonstrate
r a p i d r e t a r g e t i n g ; t h a t i s , one month of t a r g e t i n g i n f i v e working days.
�3.
O r b i t a l Debris
Lockheed, under c o n t r a c t NAS8-20369, has submitted a r e p o r t
This document
e n t i t l e d "A Study of AS-501 Debris Risk Hazard Analysis."
has been reviewed and approved. The p r e s e n t Risk Hazard Program i s
being modified t o g e n e r a t e t h e d e b r i s a n a l y s i s f o r t h e AS-502 miss ion.
4.
Voyager
The nominal t r a j e c t o r y has been generated f o r t h e 45" launch
azimuth. The u n r e s t r i c t e d aerodynamic d a t a a r e being p u t i n our 6D deck
t o c a l c u l a t e turning r a t e s .
5.
AAP
A p r e l i m i n a r y range s a f e t y a n a l y s i s has been generated f o r
nose-cone and a CSM "2 1/2 s t a g e " con£ i g u r a t i o n . The nose cone coni g u r a t i o n was i n s e r t e d i n t o a 260 n a u t i c a l m i l e c i r c u l a r o r b i t w i t h
an i n c l i n a t i o n of 50". The CSM " 2 112 stage" con£ i g u r a t i o n was i n s e r t e d
i n t o a n 81 x 120 n a u t i c a l m i l e e l l i p t i c a l o r b i t w i t h a 50' i n c l i n a t i o n .
T r a j e c t o r i e s were generated f o r b o t h n o r t h e r l y and s o u t h e r l y launch
azimuths
.
C.
Tracking and O r b i t a l Analysis Branch
1.
Saturn I B
a . A p r e l i m i n a r y copy of AS-204-LM1 a c q u i s i t i o n and l o s s
timc was g i v e n t o I-MO-R per r e q u e s t .
b. Work w i l l begin t h i s week on t h e AS-205 t r a c k i n g a n a l y s i s
wllicl~w i l l b e done in-house.
c . An a c t i o n item from I-MO has been r e c e i v e d t o a n a l y z e
Bermuda coverage on t h e AS-204/LM1 m i s s i o n f o r v a r i o u s b o o s t phase cont i n g e n c i e s . R-AERO-FM i s p r e p a r i n g t r a j e c t o r y i n f o r m a t i o n n e c e s s a r y t o
R e s u l t s should be a v a i l a b l e soon.
a n a l y z e t h e coverage problem.
2.
Saturn V
a . The t r a c k i n g and c o m u n i c a t i o n s a n a l y s i s document on
t h e SA-504 m i s s i o n prepared by TBC has been r e c e i v e d , reviewed, and
rejected.
TBC has been b r i e f e d on t e c h n i c a l d e f i c i e n c i e s , and o f f i c i a l
n o t i f i c a t i o n of t h e r e j e c t i o n has been submitted t o R-AERO-P.
�ILLS
b.
'Che AS-502 t r a c k i n g ancl t e l e m e t r y coverage document
bccxn tl i s tr i b u t c d unc1c.r Memorandum R-AERO-FT-45-67
.
c . S t u d i e s a r e p r e s e n t l y underway t o a i d i n t h e answer
of t h e F l i g h t Mechanics P a n e l a c t i o n i t e m 2 1 . 5 . 4 r e g a r d i n g AS-~O~/S-IVB
restart possibilities.
S-IVB r e s t a r t t i m e s based on ground p r o f i l e s
a r e b e i n g a n a l y z e d , and recommendations w i l l be made t o answer t h e
following items:
(1) S-IVB r e s t a r t f o r a 10-second b u r n w i t h S/C
a t t a c h e d a b o u t 90 m i n u t e s a f t e r i n s e r t i o n .
(2) Same a s (1) a b o v e , e x c e p t r e s t a r t w i l l o c c u r
a b o u t 180 m i n u t e s a f t e r i n s e r t i o n .
( 3 ) S-IVB r e s t a r t f o r a 30 t o 40-second b u r n , SIC
a t t a c h e d , w i t h a 45' yaw a t t i t u d e , a b o u t 90 m i n u t e s a f t e r o r b i t a l
i n s c r t i o n and a second r e s t a r t a f t e r LV/SC s e p a r a t i o n .
( 4 ) Perform two S-IVB r e s t a r t s a f t e r LV/SC s e p a r a t i o n ,
w i t h a f i r s t b u r n of a b o u t 5 0 s e c o n d s .
I n f o r m a t i o n on f i r s t r e s t a r t c a s e s a b o u t 90 and a b o u t
180 m i n u t e s a f t e r i n s e r t i o n has been s u p p l i e d t o R-AERO-DA.
Informat i o n on second r e s t a r t c a s e s w i l l b e s u p p l i e d a f t e r t r a j e c t o r y informat i o n i s g e n e r a t e d by R-AERO-DA.
3.
Apollo Applications
a . The second meeting of t h e AAP I & C P a n e l was h e l d a t
MSFC on May 24, 1967. The few a c t i o n items t h a t were c o n s i d e r e d were
i n d i c a t i v e of t h e c o n t i n u e d l a c k of d e f i n i t i o n of t h e program.
b. A p r e s e n t a t i o n given a t
F o r c e Meeting h e l d a t MSFC on June 1 and
t h e t r a c k i n g and c o m u n i c a t i o n s coverage
f o r t h e second c l u s t e r m i s s i o n . O r b i t a l
were p r e s e n t e d on b o t h t h e f i r s t c l u s t e r
i n c l i n e d o r b i t and on t h e second c l u s t e r
inclined orbit.
t h e AAP M i s s i o n P l a n n i n g Task
2 i n c l u d e d a b r i e f rundown on
on t h e 50-degree i n c l i n e d o r b i t
decay and l i f e t i m e s t u d i e s
m i s s i o n on t h e 28 112 d e g r e e
m i s s i o n on t h e 50-degree
c . A p r e s e n t a t i o n on t h e C l u s t e r 1 c o n f i g u r a t i o n o r b i t a l
d e c a y and l i f e t i m e was g i v e n t o t h e Guidance, Performance, and Dynamics
Subpanel which met a t MSFC on J u n e 1 5 , 1967. The r e s u l t s p r e s e n t e d
were based on t h e l a t e s t and b e s t i n f o r m a t i o n a v a i l a b l e . These w i l l be
updated a s new i n f o r m a t i o n is o b t a i n e d .
�a. A s tutly was co~npleted by NSL Mission Support t o d e t e r n ~ i n c t h e gimbal r a t e s r e q u i r e d t o o r i e n t t h e ATM s t a r t r a c k e r on Canopus
over a one-year p e r i o d . These r e s u l t s were given t o M r . Snoddy, I-S/AA,
a l o n g w i t h t h e approximate percentage of time t h e ATM s t a r t r a c k e r would
be o c c u l t e d by t h e e a r t h . This i n f o r m a t i o n was r e q u e s t e d t o v e r i f y a
proposed s t a r t r a c k e r gimbal requirement on t h e ATM mission.
b . A meeting was h e l d w i t h I-MO, ASTR, P&VE, and AERO
personnel t o a t t e m p t t o e s t a b l i s h a f i r s t c u t a t t h e Voyager m i s s i o n
sequence of e v e n t s . This information i s being g a t h e r e d t o g e t h e r by
M r . Kurtz of I-MO f o r t h e Mission Operations Working Group.
c. P r e l i m i n a r y a n a l y s i s was made concerning communications
d u r i n g shroud s e p a r a t i o n and DSN pickup. This i n f o r m a t i o n was i n s u p p o r t
of M r . Kurtz, I-MO, a s a panel member of t h e Voyager Mission Operations
Working Group.
d. M r . Lee Gentry, Martin-Marie tta-Denver, was a t MSFC on
June 2 9 , 1967, f o r a n o r i e n t a t i o n meeting on t h e s t u d y "Mars T r a n s f e r
T r a j e c t o r y Determination and E r r o r Analysis."
The i n i t i a l phase of
t h e s t u d y (approximately two months) w i l l be a survey of t h e methods of
i n t e r p l a n e t a r y t r a j e c t o r y determination.
e . A p r e s e n t a t i o n was g i v e n by M r . Pimm, DISC m i s s i o n s u p p o r t ,
a t t h e Voyager T r a j e c t o r i e s , Performance, Navigation and Guidance Working Group meeting a t JPL on J u l y 19, 1967, on a Mars O r b i t e r decay and
lifetime.
5.
O r b i t a l A n a l y s i s and L i f e t i m e
a . M r . R. J . H i l l and M r . R. H. Benson each p r e s e n t e d a
paper a t t h e Environment Induced O r b i t a l Dynamics Seminar on June 6 ,
1967. M r . w ill' s p r e s e n t a t i o n was "Engineering C o n s i d e r a t i o n s i n L i f e time P r e d i c t i o n s ," and M r . enso on' s was "On Obtaining Decay Parameters
from O r b i t Determination."
Writeups of b o t h p r e s e n t a t i o n s have been
completed and copies have been d i s t r i b u t e d t o i n t e r e s t e d personnel.
~~,
t h e SA-101
b . O f f i c e Memorandum R - A E R O - F T - ~ ~ -updating
Pegasus C l i f e t i m e and decay, has been prepared and d i s t r i b u t e d .
c . NSL m i s s i o n s u p p o r t personnel gave a b r i e f i n g on t h e
s t a t u s of a t t i t u d e p r e d i c t i o n work being performed. A 3D s i m u l a t i o n
program has been w r i t t e n and programmed by R-COMP, and is now being
checked o u t . This program w i l l be used t o a n a l y z e t o r q u e magnitudes
and t o v e r i f y averaging techniques which a r e t o be developed. D r . Yu,
who d i s c u s s e d averaging techniques and o p e r a t i o n s , w i l l soon b e g i n working on t h e s p e c i f i c problem of a t t i t u d e p r e d i c t i o n .
�D.
F l i g h t E v a l u a t i o n Branch
1.
General
Computer Programs
The use of Marshall Vehicle Engineering System (MARVES)
i n t h e Modular 6D t r a j e c t o r y program has shown t h a t t h e advantages
o f f e r e d by t h e system could be extended t o computer programs o t h e r t h a n
3 D o r 6D t r a j e c t o r y programs. Other programs, w i t h i n t h e D i v i s i o n ,
w i l l be converted t o MARVES i n a n e v o l u t i o n a r y manner. To a s s i s t i n
t h i s t r a n s i t i o n , t h e following i n f o r m a t i o n has been prepared and w i l l
be k e p t c u r r e n t :
(1)
Index of modules c a t e g o r i z e d by f u n c t i o n .
(2)
Alphabetized notebook of modules ( i n f o r m a t i o n
i n c l u d e s a l l documentation on each module).
(3)
Alphabetized l i s t of nomenclature (and d e f i n i t i o n s )
used i n t h e modules.
(4)
Generalized g u i d e l i n e s f o r p r e p a r a t i o n and docum e n t a t i o n of s u b r o u t i n e s o r modules.
This m a t e r i a l i s being used t o f a m i l i a r i z e t h e D i v i s i o n w i t h MARVES and
t o a i d t h e development of new programs.
2.
Saturn I B
a.
AS-204-LM Wind Limits
The AS-204/IX-1 launch v e h i c l e wind l i m i t s document
has been r e c e i v e d from CCSD. The l i m i t s a r e based upon t h e s t r u c t u r a l
i n t e g r i t y of t h e launch v e h i c l e which i s d e f i n e d a t s e v e r a l Mach numbers
a s f u n c t i o n s of a n g l e of a t t a c k ( a ) , c o n t r o l gimbal d e f l e c t i o n (B), and
dynamic p r e s s u r e ( q ) . R e s u l t s of t h e s t u d y show t h a t , a t t h e most
c r i t i c a l a l t i t u d e (10 km), t h e wind l i m i t s f o r headwind, crosswind,
and t a i l w i n d a r e 50, 48, and 70 m/sec, r e s p e c t i v e l y .
b.
S-IB Cutoff Time and V e l o c i t y Study
A memo e n t i t l e d "Analysis of t h e P r e d i c t e d and Actual
Cutoff Times and V e l o c i t i e s of S-IB s t a g e s and c u t o f f times on S-IVB
s t a g e s of S a t u r n I B v e h i c l e s AS-201, AS-202 and AS-203," w a s approved
and r e l e a s e d .
�3.
Saturn V
a.
EDS-Abort C r i t e r i a
During a meeting on J u l y 19, 1967, between R-AERO,
R-P&m, and TBC EDS groups, s e v e r a l proposals were advanced by TBC
on how t o proceed w i t h t h e a b o r t t e n s i o n breakup problem. The proposal
which r e c e i v e d g r e a t e s t s u p p o r t from R-P&VE was t h a t of s e p a r a t i n g s t a g e s
S-IC/S-I1 upon a b o r t i n i t i a t i o n and s i m u l t a n e o u s l y f i r i n g S-IC r e t r o r o c k e t s t o r e l i e v e t h e bending moment a t t h i s i n t e r f a c e . TBC w i l l conc e n t r a t e more h e a v i l y on t h i s approach and determine i f t h e s t o r e d s t r a i n
energy r e s u l t s i n a s h i f t of breakup t o h i g h e r v e h i c l e s t a t i o n s . They
a r e working t o have a proposed f i x t o t h i s problem by August 1 5 , 1967.
b.
Abort and A l t e r n a t e Mission Analysis
The r e s p o n s i b i l i t y f o r performing a b o r t and a l t e r n a t e
m i s s i o n s a n a l y s e s on S a t u r n V launch v e h i c l e s was switched from AERO-mT
t o AERO-FFR.
R-AERO-FFR w i l l be r e s p o n s i b l e commencing w i t h the AS-503
a n a l y s i s . A new scope of work i.s being n e g o t i a t e d w i t h T ~ C / ~ u n t s v i l l e ,
4.
Apollo A p p l i c a t i o n s
a.
F l i g h t E v a l u a t i o n Working Group-Payload
A FEWG-Payload and AAP f i l e has been e s t a b l i s h e d f o r
AERO-F.
This f i l e c o n t a i n s g e n e r a l i n f o r m a t i o n , memorandums, and agenda
concerning t h e FEWG-Payload o r g a n i z a t i o n ; a l s o l o c a t e d i n t h i s f i l e a r e
MSFC forms No. 422, on each of t h e ATM and OWS experiments. This f i l e i s
t o be used w i t h i n t h e D i v i s i o n f o r i n f o r m a t i o n concerning FEWG and AAP.
During t h e l a t e r p a r t of May s e v e r a l s m a l l meetings were
h e l d among r e s p o n s i b l e persons i n v a r i o u s o f f i c e s and FEWG-Payload s t a f f
concerning t h e t a s k requirements f o r t h e OWS. These v a r i o u s meetings
provided b e n e f i c i a l r e s u l t s i n t h a t t h e complexity of t h e problem of
d e f i n i n g t h e v a r i o u s t a s k requirements was r e a l i z e d .
Dr.
ing
The
the
There w i l l be a s p e c i a l s t a f f and board meeting w i t h
von Braun on August 9 concerning t h e g e n e r a l F l i g h t E v a l u a t i o n WorkGroup (FEWG) o r g a n i z a t i o n w i t h s p e c i a l emphas i s on FEWG-Payload
FEWG-Payload s t a f f and s u p p o r t i n g s t a f f (CCSD) a r e now working on
v a r i o u s c h a r t s t o be p r e s e n t e d a t t h i s meeting.
.
�5.
Contracts
a.
S a t u r n I B Sys tems (CCSD)
C h r y s l e r Corporation Space D i v i s i o n (CCSD) a t Michoud
i s r e s p o n s i b l e f o r e s t a b l i s h i n g t h e i n t e r m e d i a t e (7-day) and f i n a l
(14-day) p o s t - f l i g h t t r a j e c t o r i e s on t h e S a t u r n I B v e h i c l e s . The n e x t
S a t u r n I B t o be launched (AS-204/LM1) i s t h e f i r s t I B v e h i c l e t o use
t h e P r o j e c t Apollo Coordinate System Standards (PACSS). CCSD has
r e d e f i n e d and implemented a l l of t h e changes n e c e s s a r y t o use PACSS.
These changes have been completely documented. MSFC has f u r n i s h e d CCSD
w i t h t h e l a t e s t v e r s i o n of t h e O r b i t a l C o r r e c t i o n Program (OCP) which
can handle o r b i t a l v e n t i n g and the l a t e s t v e r s i o n of t h e powered f l i g h t
t r a j e c t o r y program (GATE). CCSD w i l l a s s i s t us i n conducting s t u d i e s
t o determine t h e c a p a b i l i t i e s and l i m i t a t i o n s of t h e s e programs.
It
appears t h a t CCSD has made e x c e l l e n t p r o g r e s s and can perform t h i s t a s k
w i t h a 1imited amount of s u p e r v i s i o n .
b
.
Miss i o n Support (Nor t h r o p )
Tracking d a t a and telemetered measurements from long
d u r a t i o n space f l i g h t comprise a l a r g e volume of i n f o r m a t i o n t h a t
r e q u i r e s b o t h p r o c e s s i n g and r e d u c t i o n . Some means of compressing
t h e s e d a t a i s needed t o p r e s e r v e a l l t h e s i g n i f i c a n t i n f o r m a t i o n i n t h e
d a t a w h i l e reducing t h e volume.
D r . Hal P u r c e l l (NSL) has been r e s e a r c h ing v a r i o u s compression techniques t o a r r i v e a t a l o g i c a l method.
Emphasis w i l l be on s i m p l i c i t y of technique, minimum computer time, and
minimum d e g r a d a t i o n of d a t a . A f t e r a technique has been s e l e c t e d , a
computer program w i l l be developed f o r AAP f l i g h t d a t a .
An i n f o r m a t i o n a l document compiled f o r t h e ATM and OWS
m i s s i o n s c o n t a i n s g e n e r a l in£ ormation, experiment o b j e c t i v e s , and
i n s t r u m e n t a t i o n d e s c r i p t i o n . The document w i l l be used f o r background
i n f o r m a t i o n and w i l l be updated a s r e q u i r e d .
VIII.
PROJECTS OFFICE
1.
S a t u r n V SE&IS C o n t r a c t
As a r e s u l t of s e v e r a l weeks of c o n c e n t r a t e d e f f o r t , R-AERO-P
has s u c c e s s f u l l y e s t a b l i s h e d coordinated document d e l i v e r y s c h e d u l e s f o r
R-P&VE, R-ASTR, and TBC. This r e s c h e d u l i n g e f f o r t was brought a b o u t by
t h e new S a t u r n V launch schedule (Apollo Program D i r e c t i v e 4G). The
r e s c h e d u l i n g c y c l e a l s o included a complete rework and r e s c h e d u l i n g of
GFD requirements i n s u p p o r t of t h e TBC SE&IS c o n t r a c t .
�2.
F l i g h t Mechanics Panel Meeting
The Twenty-First Meet.ing of t h e FMP was held a t MSFC on
J u l y 12 and 13, 1967. A resumc of some of t h e more important items
from t h e meeting i s a s f o l l o ~ ? s :
( a ) The L/V and S/C program managers a r e b e i n g r e q u e s t e d t o
emphasize t h e f o r m u l a t i o n of checkout procedures, e t c . , t o accommodate
a n on-time (or near-on-time) launch which i s r e q u i r e d f o r t h e pol lo/
S a t u r n rendezvous m i s s i o n .
(b) The FMP w i l l e x p e d i t e s t u d i e s on t h e f o l l o w i n g AS-503
c a n d i d a t e p r o f i l e s and make a recommendation on which one t o implement
f o r t h e miss ion:
(1)
S-IVB r e s t a r t f o r a 10-second burn w i t h SIC
a t t a c h e d a b o u t 90 minutes a f t e r o r b i t a l i n s e r t i o n
( i n t h e e v e n t t h a t SIC checkout r e q u i r e s more than
90 minutes t h e second burn w i l l occur a t a b o u t
180 m i n u t e s ) .
(2)
S-IVB r e s t a r t f o r a 30 t o 40 second b u r n , SIC
a t t a c h e d , w i t h a 45O yaw a t t i t u d e a b o u t 90 minutes
a f t e r o r b i t a l i n s e r t i o n and a second r e s t a r t a f t e r
LV/ SC s e p a r a t i o n .
(3)
Perform two S-IVB r e s t a r t s a f t e r LV/SC s e p a r a t i o n
w i t h a f i r s t : burn of a b o u t 50 seconds.
Due d a t e f o r t h e FMP recommendation i s August 14, 1967.
( c ) The FMP w i l l c o o r d i n a t e a meeting f o r a n o v e r a l l review
of A p o l l o I S a t u r n I B and V ( i . e . , L/V and SIC) one-engine-out and EDS
problems. This w i l l i n c l u d e Crew S a f e t y P a n e l , Mechanical Panel and
o t h e r MSFC & MSC personnel. Date f o r t h e meeting i s Thursday, August 1 0 ,
1967, a t MSFC.
(d) MSC a g r e e s t h a t t h e SIC has no requirement t o reduce t h e
maximum S-IC l o n g i t u d i n a l a c c e l e r a t i o n on AS-502 below a 30 v a l u e of
(The s e r v i c e module a f t bulkhead problem i s being "fixed"
4.840 g ' s .
by MSC.)
( e ) The LVISC i n t e r f a c e s i g n a l s r e l a t i n g t o f l i g h t mechanics
a r e b e i n g reviewed and updated on a l l A p o l l o / S a t u r n I B and V m i s s i o n s .
The minutes of t h e meeting have been d i s t r i b u t e d i n Memo
R-AERO-P-286-67, dated J u l y 13, 1967.
�BIBLIOGRAPHY
1.
Weidner, D. K. and C . L. H a s s e l t i n e , " N a t u r a l Environment Design
C r i t e r i a G u i d e l i n e s f o r MSFC Voyager S p a c e c r a f t f o r Mars 1973
M i s s i o n , " TM X-53616, June 8 , 1967, U n c l a s s i f i e d .
2.
Heybey, W. H . , "On Mixed F.eflection o f S u n l i g h t ,
J u n e 8 , 1967, U n c l a s s i f i e d .
3.
H u f f a k e r , R. M. and M. J . Dash, "A G e n e r a l Program f o r t h e C a l c u l a t i o n o f R a d i a t i o n f o r a n Inhomogeneous, N o n i s o b a r i c , Nonisothermal
Rocket Exhaust Plume," TM X-53622, June 1 9 , 1967, U n c l a s s i f i e d .
4.
F a l l s , Lee W . , "Peak S u r f a c e Wind Exposure P e r i o d S t a t i s t i c s f o r
Cape Kennedy, F l o r i d a , " TM X-53624, J u n e 20, 1967, U n c l a s s i f i e d .
5.
H u f f a k e r , R. M . , "Inhomogeneous R a d i a n t Heat T r a n s f e r from S a t u r n Type Rocket Exhaust Plumes," TM X-53630, J u n e 3 0 , 1967, U n c l a s s i f i e d .
6.
Wheeler, J o h n T . , " A p p l i c a t i o n o f Higher Order Runge-Kutta I n t e g r a t i o n Techniques Developed by Erwin F e h l b e r g t o Low-Thrust T r a j e c t o r i e s , " TM X-53631, June 30, 1967, U n c l a s s i f i e d .
7.
Papadopoulos, J . G . , " A e r o e l a s t i c Load Growth E f f e c t s o n S a t u r n
C o n f i g u r a t i o n s , " TM X-53634, J u l y 1 4 , 1967, U n c l a s s i f i e d .
8.
Lee, R. F . , J. W. Ownbey and F. T. Q u i n l a n , " ~ h u n d e r s t o r m P e r s i s t e n c e
a t Cape Kennedy, F l o r i d a , " TM X-53635, J u l y 1 7 , 1967, U n c l a s s i f i e d .
9.
T o e l l e , R. G . , "A Performance Study f o r t h e A p p l i c a t i o n o f t h e
S a t u r n V t o High Energy M i s s i o n s , " TM X-53639, J u l y 3 1 , 1967,
Unclassified.
10.
S c o g g i n s , James R . , "some P r o p e r t i e s o f Low A l t i t u d e Atmospheric
T u r b u l e n c e a t Cape Kennedy, F l o r i d a , " TM X-53640, J u l y 31, 1967,
Unclassified.
11.
B a l l a n c e , James O . , "An A n a l y s i s o f t h e M o l e c u l a r K i n e t i c s o f t h e
Thermosphere P r o b e , " TM X-53641, J u l y 3 1 , 1967, U n c l a s s i f i e d .
12.
B a l l a n c e , James O . , "Wake and I n t e r r e f l e c t i o n E f f e c t s i n t h e Calcul a t i o n o f F r e e M o l e c u l a r Flow Drag C o e f f i c i e n t s , " TM X-53642,
J u l y 3 1 , 1967, U n c l a s s i f i e d .
It
TM X-53617,
�RIBLIOGRAPlFY (Continued)
13.
P e r r i n e , B. S., "A Method o f S o f t Tether S t a t i o n k e e p i n g , " TM X-53643,
J u l y 31, 1967, U n c l a s s i f i e d .
14.
Bauer, E t h e l H . , "Launch Vehicle T a r g e t i n g Using t h e Hypersurface
Concept," R-AERO-IN-4-67, June 27, 1967, U n c l a s s i f i e d .
15.
Weidner, D. K., "A P r e l i m i n a r y Summary o f t h e MSFC P l a n e t a r y
Atmosphere Computer Program," R-AERO-IN-5-67, June 30, 1967,
Unclassified.
APPROVAL
Deputy D i r e c t o r , Aero-Astrodynamics Laboratory
E. D. Geiss1e.r
D i r e c t o r , Aero-Astrodynamics Laboratory
DISTRIBUTION
R-AERO-DIR
Dr. Geissler
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I-v-P
Harold P r i c e
M r . Jennings
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M r . B u t l e r (4)
Mrs. Hightower
R-AERO-P
R-AERO-D
R-AERO-A
R-AERO-G
R- AERO-Y
R-AERO-F
R-AERO-X
R-DIR
PAO, M r . Kurtz
MS-H, Miss J e r r e l l ( 3 )
(8)
(16)
(20)
(6)
(5)
(8)
(2)
R- AERO- T
Mr.
Mr.
Mr.
Dr.
Mr.
Dr,
Dr.
Mr.
Mr.
Dr.
von Puttkamer
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Heybey
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Liu
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Few
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Sperling
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Saturn V Collection
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000045
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: June - July 1967."
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George C. Marshall Space Flight Center
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1967-08-01
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1960-1969
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Box 23, Folder 33
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AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
October-November 1968
INDEX
Page
.........................
PROJECTS OFFICE ........................................
SCIENTIFIC AND TECHNICAL STAFF
................................
AEROPHYSICS DIVISION ...................................
A . F l u i d Mechanics Research O f f i c e ....................
B . Mechanical Design O f f i c e ...........................
C . Aerodynamic Design Branch ..........................
D . Thermal Environment Branch .........................
E . Experimental Aerophysics Branch ....................
F . Unsteady Gas Dynamics Branch .......................
ADVANCED STUDIES OFFICE
.........................
.........................
.
.....................
...........................
.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION .............
A . Guidance Theory Branch .............................
B . Astrodynamics Branch ...............................
C . O p t i m i z a t i o n Theory Branch .........................
DYNAMICS AND FLIGHT MECHANICS DIVISION .................
V I I.
A . M u l t i - P r o j e c t s .....................................
B., S a t u r n V ...........................................
C . S a t u r n Apollo A p p l i c a t i o n s Program .................
D . General ............................................
V I I I . FLIGHT TEST ANALYSIS DIVISION ..........................
A . S p e c i a l P r o j e c t s O f f i c e and S t a f f ..................
B . F l i g h t E v a l u a t i o n Branch ...........................
C . Tracking and O r b i t a l A n a l y s i s Branch ...............
AEROSPACE ENVIRONMENT DIVISION
A
Atmosphere Dynamics Branch
B
T e r r e s t r i a l Environment Branch
C
Space Environment Branch
.
D
.
F l i g h t Mechanics Branch
............................
�AERO-ASTRODYNAMICS LABORATORY
BIMONTHLY PROGRESS REPORT
October-November 1968
SCIENTIFIC AND TECHNICAL STAFF
J - 2 s Rendezvous and Guidance Study (Few1
-
1. Guidance Analysis
Modified v e r s i o n s of IGM t o more a c c u r a t e l y
c a l c u l a t e range a n g l e s a r e being i n v e s t i g a t e d . IGM flown f o r boostc o a s t - b o o s t has shown t h a t range a n g l e c a l c u l a t i o n s a r e inadequate over
It has been determined t h a t t h e e x i s t t h e d u r a t i o n of t h e c o a s t p e r i o d .
ing IGM f o r m u l a t i o n can be improved by optimizing two miss ion-dependent
c o n s t a n t s which b i a s range a n g l e p r e d i c t i o n s f o r t h e s p e c i f i c p r o f i l e .
However, t h i s i s n o t des i r a b l e from a n o p e r a t i o n a l p o i n t of view,
because t h e s e c o n s t a n t s a r e dependent upon launch window v a r i a t i o n s .
Three methods of p r e d i c t i n g time- to-go a r e being i n v e s t i g a t e d
f o r a v e h i c l e w i t h t h r o t t l i n g i n t h e f i n a l b o o s t phase. Each of t h e s e
methods employ d i f f e r e n t techniques t o s o l v e v e h i c l e range a n g l e and
s a t e l l i t e positions.
One of t h e s e schemes shows promise f o r the nominal
c a s e i n terms of rendezvous e r r o r s and t h r u s t s t a b i l i t y . However, d i s persed cases must s t i l l be e v a l u a t e d . Also, t h r o t t l i n g t h e engine i n
s t e p s r a t h e r than c o n t i n u o u s l y i s being reviewed i n terms of guidance
s t a b i l i t y and rendezvous e r r o r s .
-
P r e l i m i n a r y d a t a from t h r o t t l i n g S - I 1
2. Performance Analysis
and S-IVB t o c i r c u l a r e a r t h o r b i t (100,262 and 500 N.Mi.) i n d i c a t e t h a t
a c o n s i d e r a b l e payload i n c r e a s e i s r e a l i z e d over d i r e c t b o o s t . With
t h r o t t l i n g t o 50,000 l b s / e n g i n e (minimum o p e r a t i o n a l l i m i t ) , a p p r o x i mately 55 p e r c e n t of t h e payload l o s s which r e s u l t s when d i r e c t b o o s t
i s used i n s t e a d of Hohrnann t r a n s f e r (boos t-coas t-boos t ) may be recovered
by u s i n g t h r o t t l i n g . This i s based on o p t i m i z a t i o n of t h e S-IC t i l t
p r o f i l e and t h r o t t l i n g i n t h e S-11; t h e g a i n i s o n l y approximately
40 p e r c e n t .
11.
PROJECTS OFFICE
During October and November, a c o n s i d e r a b l e e f f o r t was d i r e c t e d
toward r e s o l u t i o n of RID'S from t h e ATM and LM-A PDR'S d e a l i n g w i t h
a 1 t e r n a t e m i s s i o n s , c r i t i c a l time l i n e s , and a t t i t u d e time l i n e s .
B r i e f l y , t h e r e s u l t has been t o e l i m i n a t e t h e a l t e r n a t e decoupled
m i s s i o n ( a l t e r n a t e being d e f i n e d a s decided upon a f t e r AAP-4 launch
a s opposed t o backup which i s s e l e c t e d b e f o r e AAP-4 l a u n c h ) . The
�backup m i s s i o n has been c o n s t r a i n e d t o t h e p o i n t t h a t i t w i l l i n p r o f i l e
look much 1 i k e t h e primary m i s s i o n ; t h u s , no new d e s i g n requirements
s l ~ o u l dbe g c n e r a t c d by t h e decoupled mission. The s t r e a m l i n i n g of t h e
M P - 4 m i s s i o n w i l l r e s u l t i n handsome c o s t b e n e f i t s by a l l o w i n g some
r e d u c t i o n s , and c e r t a i n l y n e g o t i a t i n g some proposed i n c r e a s e s i n c o s t
The f i r s t phase of t h i s e f f o r t is scheduled f o r completion on December 15,
1968.
.
111.
ADVANCED STUDIES OFFICE
A.
A s trodynamics and Mission A n a l y s i s Group
1'.
Unmanned P l a n e t a r y
D e t a i l e d miss i o n d e s i g n
S a t u r n passage c o n d i t i o n s ( i n s i d e o r
Uranus and Neptune passage d i s t a n c e s
performed under c o n t r a c t NAS8-20082,
(TM 54130-199).
charts f o r earth-depart energies,
o u t s i d e t h e r i n g s of S a t u r n ) , and
have been completed. The work,
i s documented i n LMSC/HREC A791951
Charts a r e b e i n g prepared t o i n d i c a t e t h e performance p e n a l t y
( i n terms of AV) when r e s t r i c t i o n s a r e placed on passage d i s t a n c e s a t
J u p i t e r and S a t u r n .
P r e l i m i n a r y d a t a have been s e n t t o M r . Guttman, R-ASTR-A,
showing t h e v e l o c i t y requirements n e c e s s a r y t o change t h e impact parame t e r a t t h e s p h e r e of i n f l u e n c e f o r J u p i t e r , S a t u r n , and Uranus. The
d a t a were based on t y p i c a l approach v e l o c i t i e s f o r t h e t r a n d t o u r
miss ions.
2.
S a t u r n V OWS/NPS I n t e g r a t i o n Study
R-ASTR-AG has r e q u e s t e d (1) p r e l i m i n a r y d a t a d e f i n i n g t h e
rendezvous c o r r i d o r s and l o c a t i o n from t h e c e n t e r l i n e of t h e S a t u r n V
o r b i t a l workshop/nuclear e l e c t r i c power system (OWSINPS) c l u s t e r v e r s u s
time f o r l o g i s t i c s s u p p l y v e h i c l e s and remote modules, (2) d a t a necess a r y t o determine t h e number of times t h e CSM might b e used f o r tugging
remote modules t o and from experiment l o c a t i o n s and t h e concomitant
t r a j e c t o r i e s , and (3) d a t a which d e f i n e t h e p r o p u l s i o n requirements and
c r i t e r i a f o r mode s e l e c t i o n f o r r e a c t o r d i s p o s a l ( d e o r b i t f o r ocean d i s p o s a l w i t h impact d i s p e r s i o n r e s u l t i n g from p e r t u r b a t i o n s i n t h r u s t
v e c t o r magnitude and alignment v e r s u s i n j e c t i o n i n t o a l o n g - l i v e d o r b i t ) .
�A l l d a t a excluding t h e impact d i s p e r s i o n have been computed
and a copy d e l i v e r e d t o M r . L. W. B r a n t l e y . The impact d i s p e r s i o n d a t a
a r e being computed, and m o d i f i c a t i o n s of t h e remote module t r a j e c t o r i e s
which r e s u l t i n t h e i n c u r r e n c e of a s m a l l e r r a d i a t i o n dose a r e being
investigated.
3.
Computer Program Development
a.
S p a c e c r a f t Communications and O r i e n t a t i o n
Angles Program
A computer program has been developed t o a n a l y z e spacec r a f t p l a n e t o c e n t r i c passage c o n d i t i o n s f o r t h e Grand Tour m i s s i o n s .
The program c a l c u l a t e s s p a c e c r a f t communication d i s t a n c e s and a n g l e s ,
o r i e n t a t i o n a n g l e s , and o c c u l t a t i o n s w i t h r e s p e c t t o t h e Sun, E a r t h ,
and Canopus. A r i n g model f o r S a t u r n has been i n c o r p o r a t e d t o d e t e r mine t h e r i n g passage c o n d i t i o n s ( i n s i d e o r o u t s i d e of S a t u r n ' s r i n g s ) .
b.
Fly-By O c c u l t a t i o n Program
A computer program i s being developed t o a s s e s s the
These occul t a o c c u l t a t i o n regions f o r planetary fly-by t r a j e c t o r i e s
t i o n r e g i o n s can be viewed i n t h e R-T plane by p a r a m e t e r i z i n g t h e impact
parameter B. A t p r e s e n t , t h e program c o n s i d e r s o c c u l t a t i o n s w i t h r e s p e c t
t o Sun, E a r t h , and Canopus
.
.
B.
F l i g h t Mechanics and Performance Analysis Group
1.
Space S t a t i o n
The j o i n t s t a t e m e n t of work f o r t h e space s t a t i o n has been
prepared. Headquarters has d r a f t e d a combined s t a t e m e n t of work drawing
i n p u t s from MSFC and MSC. For t h e most p a r t , i t was a n MSFC s t a t e m e n t
of work which was submitted t h e previous week. A team of Headquarters,
MSC, LaRC, and MSFC met a l l week t o complete t h i s t a s k ; they reviewed
i t w i t h M r . Mathews on November 22.
I n g e n e r a l , t h e s t u d y w i l l be conducted a l o n g t h e l i n e s d e s i r e d by ASO. One prime concession Headquarters
made, which b o t h MSC and MSFC wanted, was t h a t each c e n t e r w i l l n e g o t i a t e
i t s own c o n t r a c t . S e v e r a l p o i n t s were decided which may be of i n t e r e s t
a s follows:
(a)
b a s e l i n e w i l l b e a 9-man s t a t i o n ,
(b)
LV f o r s t a t i o n w i l l b e S-IC
S-11, S-IC
S-IVB,
S-IVB, o r 1.56" s o l i d + S-IVB,
260" s o l i d
+
+
+
�2.
(c)
LV f o r l o g i s t i c s w i l l be S a t u r n I B , T-IIIM, 260"
s o l i d + S-IVB, o r 156" s o l i d + S-IVB,
(d)
l o g i s t i c s S / C w i l l be e i t h e r e x i s t i n g SIC, mods
e x i s t i n g SIC, o r new SIC (MSC d i d not want t o cons i d e r e x i s t i n g S I C , and
(e)
experiments f o r s t a t i o n w i l l r e c e i v e major emphasis
(MSC d i d n o t want t o denote much e f f o r t i n t h i s a r e a ) .
E a r t h O r b i t a l Experiments
A m i s s i o n a n a l y s i s has been performed i n s u p p o r t of the
hydrogen maser c l o c k experiment t h a t w i l l t e s t t h e t h e o r y of r e l a t i v i t y .
M r . Gregory of A s t r i o n i c s has been our p o i n t of c o n t a c t on t h e s t u d y .
The experiment w i l l be i n s e r t e d i n t o a n i n c l i n e d synchronous o r b i t over
H a w a i i by a T i t a n I I I C launched from ETR. We have g e n e r a t e d t h e performance, and d e f i n e d t h e f l i g h t environment ( a c c e l e r a t i o n s , dynamic
p r e s s u r e , e t c . ) c o a s t i n b o t h parking and Hohmann t r a n s f e r o r b i t , and
burn times.
3.
The Launch Vehicle T r a j e c t o r y Optimization Computer
Program (RFQ No. DCN-1-7-2100027)
A c o n t r a c t has been awarded t o Northrop. Some meetings
have been h e l d w i t h t h e c o n t r a c t o r s , and work has been s t a r t e d . Prel i m i n a r y i n d i c a t i o n s a r e that we can expect a good s t u d y .
4.
Tip Tank
We a r e s u p p o r t i n g t h e ILRV s t u d y and a l s o a t t e m p t i n g t o
f i n d t h e impact on t h e v e h i c l e d e s i g n of r e l a t i v e c o s t d i f f e r e n c e s
between v a r i o u s subsystems; i . e . , "What i s t h e e f f e c t on t h e optimum
v e h i c l e d e s i g n i f t h e c o r e c o s t s twice a s much per pound a s does t h e
t i p tanks"? I n t h i s c a s e t h e minimum l i f t o f f weight i s n o t t h e o p t i mum d e s i g n .
C.
Sys tem A n a l y s i s Group
A $250,000 c o n t r a c t e n t i t l e d "Study of S a t u r n V D e r i v a t i v e
(s-IC/S-IVB) Launch Vehicle System" NAS8-30506 was awarded t o t h e Boeing
Company on a s o l e s o u r c e b a s i s on November 4 . Members of t h i s o f f i c e
p a r t i c i p a t e d i n t h e t e c h n i c a l e v a l u a t i o n of t h e proposal and a r e members
of t h e t e c h n i c a l panel t h a t w i l l d i r e c t t h e s t u d y . McDonnel Douglas
A s t r o n a u t i c s Company and I n t e r n a t i o n a l Bus i n e s s Machines were subcont r a c t e d by TBC f o r s u p p o r t i n t h e a r e a s of S-IVB s t a g e d e s i g n and
�a s t r i o n i c s system d e s i g n , r e s p e c t i v e l y . The o b j e c t of t h e 10-month
(8 t e c h n i c a l , 2 r e p o r t i n g ) s t u d y i s t o provide a d e t a i l e d p r e l i m i n a r y
d e s i g n of t h e S-Ic/S-IVB/IU launch v e h i c l e system. The 8-month t e c h n i c a l
p o r t i o n of t h e c o n t r a c t w i l l c o n s i s t of a t r a d e s t u d y (Phase I ) , a prel i m i n a r y d e s i g n s t u d y (Phase 1 1 ) , and d e f i n i t i o n of a d e s i g n , development, t e s t , and e v a l u a t i o n p l a n (Phase 111). This s t u d y w i l l r e c e i v e
i n p u t s from a launch f a c i l i t i e s s t u d y being done f o r KSC by Boeing and
from t h e J - 2 s i n t e g r a t i o n s t u d y .
�IV.
AEROPHYSICS DIVISION
A.
F l u i d Mechanics Research Off i c e
-
-
(1)
The helium h e a t e r was b e i n g checked o u t .
(2)
From t h e a n a l y s i s of t h e r e s u l t s of p a s t crossed-beam
t e s t s , i t was decided t h a t a thorough c a l i b r a t i o n of
t h e crossed-beam s y s tem was n e c e s s a r y .
Crossed-Beam S t u d i e s
Crossed-beam t e s t s were suspended
TAJF
on October 1 i n t h e MSFC Thermo-Acoustic J e t F a c i l i t y f o r two main
reasons :
On November 26, t h e crossed-beam system frame i n t h e TAJF was
found t o be i n o p e r a b l e and had t o b e modified. These m o d i f i c a t i o n s a r e
i n p r o g r e s s . Three t e s t s i n t h e TAJF a r e planned f o r t h e n e a r f u t u r e .
B.
Mechanical Des i g n Off i c e
1.
Cryo-Panels f o r t h e 1 8 - f o o t Diameter IBFF Vacuum Tank
P r e l i m i n a r y d e s i g n s t u d i e s have begun on cryo-panels f o r
t h e 1 8 - f o o t diameter IBFF vacuum tank. The panels w i l l cover a l l
i n t e r i o r s u r f a c e s and w i l l have removable, non-active s e c t i o n s over t h e
windows and manways. A t e s t panel f o r h e a t t r a n s f e r t e s t s i n t h e Low
D e n s i t y Chamber i s b e i n g f a b r i c a t e d by ME Laboratory. The panel c o n s i s t s
of a n aluminum honeycomb bonded t o a 118" t h i c k aluminum p l a t e w i t h
m e t a l - f i l l e d epoxy. I f t h e s e t e s t s prove t h e e f f e c t i v e n e s s of t h e d e s i g n ,
t h e cryo-panel system w i l l be designed and s e n t t o ME Laboratory f o r
in-house f a b r i c a t i o n .
2.
Model Cover f o r t h e 18-foot Diameter IBFF Vacuum Chamber
Design has been i n i t i a t e d on a model cover f o r t h e 18-foot
diameter IBFF vacuum chamber. This cover w i l l be mounted i n s i d e t h e
vacuum chamber and remotely c o n t r o l l e d t o cover and uncover IBFF models
w i t h a vacuum- t i g h t e n c l o s u r e . This w i l l a l l o w i n s t a l l a t i o n and removal
of models w i t h o u t l o s s of vacuum, thus i n c r e a s i n g t h e number of runs per
day and d e c r e a s i n g pumping c o s t .
3. The f o l l o w i n g i s a p a r t i a l l i s t of p r o j e c t s and t h e i r
current status.
Sonic Nozzle, C. F.D. (AF)
M o d i f i c a t i o n of Model No. 397, C.F.D
(AF)
Design
Des i g n
�P o s i t i o n i n g Equipment L a s e r , 7" WT (AF)
Helium Vent T e s t Equipment, 14" WT (AD)
X-Y-Z P o s i t i o n i n g Devices, L a s e r s , Rm. 215 (AF)
P r e s s u r e Model, IBFF (AE)
M o d i f i c a t i o n of Model No. 422, 14" WT (AE)
E l e c t r o n Beam Gun, L.D.C. (AE)
E l e c t r o n Beam C o l l e c t o r , L.D.C. (AE)
E l e c t r o n Beam O p t i c a l System, L.D.C (AE)
E l e c t r o n Beam P o s i t i o n i n g Device, L.D.C. (AE)
Heated Plenum Chamber, L.D.C. (AE)
F l a t P l a t e Heat T r a n s f e r Model, L.R.C. 4' WT (AT)
5-Component Micro-Force Balance, L.D.C. (AE)
(AE)
P r e s s u r e Model, 2.7" d i a . H.R.N.
(AE)
C a l i b r a t i o n Equipment, H.R.N.
Redesigned Survey Probe, 14" WT (AE)
Model No. 425, Curved C e n t e r l i n e Force Model
14" WT (AD)
Camera Support Equipment, 14" WT (AD)
Laser Beam Support Hardware (AF)
Low Volume Diaphragm C u t t e r , IBFF (AE)
T r a c e r M a t e r i a l System, X-Beam, S.T.S. 14" WT (AF)
C.
Des i g n
Des i g n
Des i g n
Design
Des i g n
Des i g n
Des i g n
Design
Des i g n
Design
Des i g n
Des i g n
Des i g n
Fabrication
Fabrication
Fabrication
Delivered
Delivered
Delivered
Delivered
Aerodynamic Design Branch
1.
Saturn V
a.
Hydrogen Venting Study
P o s s i b l e changes i n t h e S-IVB hydrogen tank v e n t v a l v e
sequencing have g e n e r a t e d a need f o r some i n f o r m a t i o n a b o u t t h e concent r a t i o n l e v e l s of hydrogen surrounding t h e launch v e h i c l e d u r i n g f l i g h t .
T e s t s w i l l b e conducted i n t h e MSFC 14-inch t r i s o n i c
wind t u n n e l t o determine v e l o c i t y and c o n c e n t r a t i o n decay of a helium
j e t e x i t i n g normally from a c i r c u l a r p o r t i n t h e s i d e w a l l . Helium i s
used a s a s i m u l a n t f o r hydrogen s i n c e t h e two a r e c l o s e i n molecular
weight. Combinations of t h e following t e s t parameters w i l l be i n v e s t i 0.9, 1.2, 1.96; r a t i o of j e t mass flow t o
g a t e d : frustum Mach number
0.1, 1.0 and 10.0; j e t Mach number
frustum mass flow ( p e r u n i t a r e a )
0.3, 0.7 and 1.0; measurement l o c a t i o n s
x / d = 15, 45, 100, y / d = 0 t o
20.
-
-
-
-
Hardware i s b e i n g designed and t e s t s w i l l b e g i n a s soon
a s t h e equipment i s a v a i l a b l e . A p r e t e s t r e p o r t which has more d e t a i l s
of t h e t e s t approach i s n e a r l y completed.
�b.
I n t e r s t a g e Optimization Study
A t e s t has been conducted i n t h e MSFC 14-inch TWT t o
determine t h e e f f e c t s t h a t t h e removal of t h e i n t e r s t a g e e x t e r n a l coveri n g s (forward and a f t ) would have on t h e aerodynamic c h a r a c t e r i s t i c s of
t h e S a t u r n V c o n f i g u r a t i o n . A 0.33-percent s c a l e model (No. 383) of t h e
c o n f i g u r a t i o n , b u i l t i n a b u i l d i n g - b l o c k format, was t e s t e d w i t h s e v e r a l
v a r i a t i o n s of t h e i n t e r s t a g e s . Mach number ranges from 0.50 t o 4.96 and
a n g l e of a t t a c k ranges from -2 t o +12 degrees. Five-component f o r c e and
base p r e s s u r e d a t a were o b t a i n e d f o r each c o n f i g u r a t i o n .
A n a l y s i s of t h e t e s t d a t a i n d i c a t e s t h a t t h e z e r o a n g l e
of a t t a c k s t a b i l i t y d e r i v a t i v e s f o r t h e S a t u r n V launch v e h i c l e were not
a f f e c t e d ; however, t h e s t a b i l i t y d e g r a d a t i o n w i t h a l p h a f o r t h e S a t u r n V
was reduced. A d d i t i o n a l t e s t s a r e planned f o r t h e MSFC 14-inch TWT on
r e f i n e d o p e n - i n t e r s t a g e c o n f i g u r a t i o n s f o r t h e S a t u r n V. A r e p o r t documenting t h e s e r e s u l t s w i l l be prepared.
c.
S-IVB O r b i t a l R e s t a r t 5-2 Engine Plume Impingement
Effects
Plans f o r Mission D , p r e s e n t l y scheduled f o r AS-504,
i n c l u d e demonstration of S-IVB r e s t a r t i n o r b i t . This o p e r a t i o n i s t o
b e performed w i t h t h e Command Module s e p a r a t e d and l o c a t e d somewhere a f t
of t h e S-IVB s t a g e . Consequently, t h e Command Module w i l l e x p e r i e n c e
some degree of J - 2 engine plume impingement. The 5-2 engine plume and
c e r t a i n a s p e c t s of i t s impingement a r e d e s c r i b e d i n o f f i c e memorandum
R-AERO-A-68-32, d a t e d October 29, 1968.
2.
AAP
a.
O r b i t a l Aerodynamics
O f f i c e Memorandum, R-AERO-AD-68-64, " O r b i t a l Aerodynamic
Data f o r S i x AAP O r b i t a l C o n f i g u r a t i o n s , " November 25, 1968, c o n t a i n s
o r b i t a l aerodynamic d a t a f o r t h e following s i x con£ i g u r a t ions :
(1)
OWS w i t h t h e CSM a t p o r t f i v e and OWS s o l a r a r r a y s
extended p e r p e n d i c u l a r t o t h e OWS l o n g i t u d i n a l a x i s .
(2)
OWS w i t h s o l a r a r r a y s n o t extended.
(3)
OWS w i t h s o l a r a r r a y s extended p e r p e n d i c u l a r t o
t h e OWS a x i s .
(4)
OWS w i t h s o l a r a r r a y s extended p a r a l l e l t o t h e OWS
longitudinal axis.
�(5)
OWS with docked CSM and LM/ATM (CSM docked a t
p o r t f i v e , OWS s o l a r a r r a y s extended p a r a l l e l t o
the OWS l o n g i t u d i n a l a x i s ) .
(6)
Same a s (5) b u t w i t h the CSM docked a t p o r t f o u r .
A scope of work has been prepared f o r a proposed c o n t r a c t t o develop
methods t o c a l c u l a t e o r b i t a l aerodynamics. The tasks t o be performed
under t h i s c o n t r a c t would be a s follows:
(1) Incorporate the Nocilla molecule r e f l e c t i o n model
i n t o the e x i s t i n g computer program that i s p r e s e n t l y used t o c a l c u l a t e
f r e e molecule aerodynamic c o e f f i c i e n t s . This model has advantages i n
terms of g e n e r a l i t y , accuracy, and t r a c t a b i l i t y . It would provide a
parametric expression f o r the complete v e l o c i t y function of re-emitted
molecules which f o r t u i t o u s l y matches t o a considerable degree such
observed d i s t r i b u t i o n s that a r e now a v a i l a b l e .
(2) Provide w i t h i n the e x i s t i n g computer program the
c a p a b i l i t y t o vary momentum and energy accommodation c o e f f i c i e n t s a s a
f u n c t i o n of s u r f a c e o r i e n t a t i o n , s u r f a c e temperature, and any other
p e r t i n e n t parameters.
(3) Through a l i t e r a t u r e search, summarize a v a i l a b l e
experimental and t h e o r e t i c a l s t u d i e s that have been performed t o d e t e r mine momentum and energy accommodation c o e f f i c i e n t s . Based on t h i s
search, recommend values of t h e momentum and energy accommodation coeff i c i e n t s t h a t would be a p p r o p r i a t e f o r use i n the c a l c u l a t i o n of aerodynamic c o e f f i c i e n t s f o r v e h i c l e s i n e a r t h o r b i t and d e f i n e a r e a s i n
which experimental s t u d i e s a r e needed t o provide a b e t t e r d e f i n i t i o n of
t h e s e c o e f f i c i e n t s f o r conditions t h a t e x i s t on v e h i c l e s i n e a r t h o r b i t .
This c o n t r a c t would be funded by OMSF work u n i t 908-10-10-08-62; the
estimated c o s t is $40,000.
b.
Saturn IB/AAP
I1
-
Solar Panel Shroud Pressure
Tests t o determine load d i s t r i b u t i o n over the s o l a r
panel shroud of the Saturn IB/AAP I1 with the new payload configuration
w i l l be conducted i n the MSFC 14-inch t r i s o n i c wind tunnel f o r Mach
numbers from 0.8 t o 1.96 and r o l l angles of 0 and 90 degrees. Tests
w i l l commence during the week of December 9 , 1968.
c.
AAP Plume Impingement I n v e s t i g a t i o n
Phase I t e s t s a r e continuing i n t h e MSFC base flow
f a c i l i t y i n support of AAP plume impingement s t u d i e s . The Phase I
e f f o r t i s concerned w i t h a p i t o t pressure survey of an H2/02 5-2 engine
�plume. The experimental d a t a w i l l be compared with t h e o r e t i c a l 5-2 motor
plumes derived f o r the proposed t e s t conditions. These comparisons w i l l
d e f i n e the degree of consistency between experimental and a n a l y t i c a l
plume c r i t e r i a . A Phase I1 study, t o begin December 16, 1968, w i l l
determine pressures and h e a t t r a n s f e r r a t e s on a f l a t p l a t e immersed i n
t h e 5-2 plume. The p l a t e angle of a t t a c k , a x i a l and r a d i a l l o c a t i o n i n
the plume w i l l be v a r i e d . The d a t a f o r small d e f l e c t i o n angles w i l l be
used t o confirm empirical modifications t o Newtonian Impact Theory f o r
small d e f l e c t i o n angles. Progress during Phase I has been very slow due
t o limited manpower and our lack of experience i n conducting t e s t s of
t h i s type.
A memorandum documenting the o v e r a l l experimental and
a n a l y t i c a l e f f o r t i n support of AAP plume impingement i s being prepared,
including a n t i c i p a t e d completion d a t e s based on c u r r e n t manpower and
funding l e v e l s .
d.
Saturn I B AAP
Local pressure d i s t r i b u t i o n s f o r the Saturn I B O r b i t a l
Workshop payload shroud were defined a t Mach numbers from 0.8 t o 2.99.
Maximum and minimum pressure c o e f f i c i e n t s were defined a s a function
of l o n g i t u d i n a l s t a t i o n a t each Mach number. The maximum pressure coeff i c i e n t a t angle of a t t a c k occurs on the windward s i d e of the v e h i c l e ,
and the minimum pressure c o e f f i c i e n t occurs on the leeward s i d e of the
v e h i c l e . Maximum and minimum pressures do n o t n e c e s s a r i l y occur on the
c e n t e r l i n e of the v e h i c l e . Maximum pressures a r e usually c l o s e t o the
c e n t e r l i n e , while minimum pressures u s u a l l y occur zero t o 30' from the
c e n t e r l i n e on t h e leeward s i d e of the v e h i c l e . These d a t a , based on
wind tunnel t e s t of a small s c a l e model conducted i n the MSFC 14-inch
t r i s o n i c wind tunnel, a r e published i n o f f i c e memorandum R-AERO-AD-68-58.
3.
General
a.
Saturn Venting
Contract NAS8-20200 w i t h Nortronics-Huntsville has been
concluded. A f i n a l r e p o r t containing an a n a l y s i s of the Ames o r i f i c e
flow c o e f f i c i e n t d a t a i s being published.
Future work i n support of r e f i n i n g Saturn venting design
c r i t e r i a w i l l include t h e determination of v e n t c h a r a c t e r i s t i c s located
i n adverse flow f i e l d s . Undesirable flow f i e l d s may be caused by various
protuberances and frustum-cylinder junctions which could have a b e n e f i c i a l
o r unfavorable e f f e c t on v e n t performance.
�It i s p r e s e n t l y planned t o do a d d i t i o n a l experimental
work which w i l l supplement t h a t of Ames, a s w e l l a s ' t h e a d v e r s e flow
f i e l d s t u d i e s . The m a j o r i t y of t h e s e programs w i l l be c a r r i e d o u t i n
t h e MSFC 14-inch TWT.
b.
Nonlinear L i f t of Bodies of Revolution
The c o n t r a c t o r , CCSD, has n e a r l y completed t h e Phase I
f i n a l r e p o r t . Phase I c o n s i s t e d of o b t a i n i n g a complete p r e s s u r e d i s t r i b u t i o n on o g i v e - c y l i n d e r and o g i v e - c y l i n d e r - f r u s tum-cylinder b o d i e s
i n t h e MSFC 14-inch TWT. Phase 11 i n c l u d e s a p r e s s u r e r a k e s u r v e y of
t h e v o r t e x flow f i e l d behind a n o g i v e - c y l i n d e r - f r u s tum-cyl i n d e r t e s t
model c o n f i g u r a t i o n a t a n g l e of a t t a c k .
Because of t h e d e l a y s encountered d u r i n g t h e Phase I
t e s t i n g due t o t u n n e l s c h e d u l e s l i p p a g e and a low r u n r a t e , Phase I1 .
of t h e c o n t r a c t scope of work cannot be completed w i t h i n t h e o r i g i n a l
p e r i o d of performance and funding. The p e r i o d of performance i s being
extended t o J a n u a r y 15, 1969, t o accomplish a s much work a s p o s s i b l e
w i t h t h e s m a l l amount of funds remaining. A new scope of work i s being
developed which w i l l extend t h e Phase I1 s t u d y t o a s u b s o n i c Mach
number; i t w i l l i n c l u d e a n o g i v e - c y l i n d e r c o n f i g u r a t i o n . Phase I1 i s
t e n t a t i v e l y scheduled i n t h e MSFC 14-inch TWT f o r A p r i l 1969.
c.
Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n
The p r e t e s t conference a t LTV on t h e 4.0-inch diameter
p r e s s u r e model has been postponed due t o a d d i t i o n a l d e l a y s of model
d e s i g n and f a b r i c a t i o n . A scope of work i s being prepared s o l i c i t i n g
b i d s f o r d e s i g n and f a b r i c a t i o n of t h i s model.
The flow v i s u a l i z a t i o n phase of t h e MSFC t e s t s has
been r e s c h e d u l e d f o r December 1968
J a n u a r y 1969, and w i l l be conducted
by MSFC p e r s o n n e l r a t h e r t h a n CCSD.
-
d.
Cone-Cylinder Local Normal Force G r a d i e n t s
During t h i s r e p o r t i n g p e r i o d , a 25-degree cone-cylinder
p r e s s u r e model was t e s t e d i n t h e 14-inch t r i s o n i c wind t u n n e l a t Mach
numbers of 2.99 and 4.00 f o r a n g l e s of a t t a c k from -2 t o -6 d e g r e e s .
These t e s t s were performed t o p r o v i d e d e t a i l e d experimental l o c a l normal
f o r c e g r a d i e n t d i s t r i b u t i o n s f o r comparison w i t h a method-of - c h a r a c t e r Initial
i s t i c s s o l u t i o n b e i n g developed by M r . J o e L. Sims, R-AERO-AF.
e v a l u a t i o n of t h e d a t a has i n d i c a t e d some good r e s u l t s .
�e.
C a l i b r a t i o n of High Reynolds Number Equipment
A c a l i b r a t i o n rake is being designed t o survey the flow
f i e Ld of the High Reynolds Number Equipment. The rake i s of cruciform
c o n f i g u r a t i o n and contains i n each arm s e v e r a l f i v e - p o r t conical pressure
probes, which w i l l measure both the l o c a l Mach number and flow d i r e c t i o n
i n one operation. This method w i l l reduce t h e number of runs necessary
during the c a l i b r a t i o n procedure.
The survey probe t o be used i n t h e rake w i l l be c a l i b r a t e d
and checked f o r dynamic c h a r a c t e r i s t i c s i n the MSFC 14-inch TWT i n e a r l y
1969.
f.
Saturn S-IVB F l i g h t Evaluation
The aerodynamic evaluation of AS-205 was limited s i n c e
only t h r e e aerodynamic pressures were measured and the v e h i c l e angle of
a t t a c k was too small t o allow normal f o r c e and center-of-pressure d e t e r minations. The pressures measured were compared w i t h previous f l i g h t
d a t a and found t o be a s expected. The aerodynamic evaluation f o r AS-205
i s cons idered complete.
D.
Thermal Environment Branch
1.
High Angle of Attack Heating Test
The e v a l u a t i o n of the r e s u l t s of Mach 2.5 and 3.7 phases of
t h e t e s t continues. The Langley time-integrated constant-heat input
method of obtaining h e a t r a t e s from the thermocouple temperature h i s t o r i e s
has been compared w i t h a more e x a c t procedure which assumes a time-varying h e a t input. The r e s u l t s show good agreement a t the e a r l y t e s t times
and then diverge, with the varying-heat input method being lower. The
f i n a l t e s t phase a t Mach 6 has been completed, and the d a t a were r e c e n t l y
received from Langley Research Center.
2.
LRC Protuberance Test
Drafting of the f i n a l drawings of the t e s t p l a t e has begun.
A sample of the t e s t p l a t e has been made t o e v a l u a t e s e v e r a l p o s s i b l e
i n s t a l l a t i o n s of t h e thermocouples. A t e n t a t i v e t e s t d a t e of the f i r s t
two weeks i n May 1969 has been e s t a b l i s h e d w i t h LRC.
3.
E l e c t r o n Density
The c a l c u l a t i o n of t h e e l e c t r o n d e n s i t y d i s t r i b u t i o n i n the
i n v i s c i d plume and the shear l a y e r of the F-1 engine exhaust plume a t
10,000 f e e t a l t i t u d e has been completed. The Aero-Chem I n v i s c i d Streamline
�Program has been modified t o f a c i l i t a t e i t s use by malcing communication
01 d a t a from the flow f i e l d programs d i r e c t and a u t o m a t i c . The c a p a b i l i t y t o r e s t a r t t h e c a l c u l a t i o n a l o n g a s t r e a m l i n e has been added t o prov i d e an a c c u r a t e method t o compute e n t i r e nozzle l e n g t h s w i t h o u t r e q u i r i n g
e x c e s s i v e blocks of computer r u n times.
4.
Vacuum Expans i o n Study
The purpose of t h i s i n v e s t i g a t i o n i s t o develop a mathem a t i c a l technique f o r t h e d e s c r i p t i o n of t h e high a l t i t u d e and space
environment expansion of a n axisymrnetric gaseous j e t . An experimental
program w i l l be conducted t o provide experimental d a t a f o r comparison
with a n a l y t i c a l predictions.
A s e t of p a r t i a l d i f f e r e n t i a l e q u a t i o n s which d e f i n e t h e
v e l o c i t y , d e n s i t y , and s t r e s s t e n s i o n i n the flow f i e l d have been d e r i v e d .
This d e r i v a t i o n was made f o r a s i n g l e component, monatomic g a s , using t h e
B-G-K approximation f o r t h e c o l l i s i o n i n t e g r a l .
M e t h o d - o f - c h a r a c t e r i s t i c s s o l u t i o n s t o t h i s s e t of e q u a t i o n s
have been developed f o r t h e c a s e s of n e g l i g i b l e and n o n - n e g l i g i b l e s h e a r
s t r e s s . These s o l u t i o n s a r e c u r r e n t l y being programmed.
5.
O p t i c a l Measurement of Plumes
A cold flow t e s t was conducted a t AEDC w i t h a l a s e r doppler
v e l o c i t y i n s t r u m e n t ( v e l o c i m e t e r ) t o determine t h e v e l o c i t y f i e l d i n
t h e base and exhaust r e g i o n s of a f o u r n o z z l e model of t h e S a t u r n I1 type.
The t e s t was a f i r s t e f f o r t t o use t h e v e l o c i m e t e r i n a low d e n s i t y s u p e r s o n i c flow. An e q u a l l y important purpose of t h e t e s t was t o e v a l u a t e t h e
v e l o c i m e t e r and v e l o c i m e t e r s u p p o r t systems ( e l e c t r o n i c and contaminant
systems) a s a n i n t e g r a t e d system.
While t h e week of t e s t i n g did n o t produce t h e v e l o c i t y
f i e l d , the s y s tem "shakedown" has provided a n important bas is f o r
instrument changes t h a t should extend t h e i n s t r u m e n t range t o i n c l u d e
flow f i e l d s of t h e type encountered i n t h e t e s t .
6.
Miss i o n Support
a.
Shear Layers
A s t u d y of t h e flow f i e l d c o n d i t i o n s t h a t r e s u l t when
low temperature hydrogen i s vented i n t o a p a r a l l e l high temperature a i r s t r e a m was completed f o r those c o n d i t i o n s p r e s e n t a t 10 km of a S a t u r n V
f l i g h t . The p h y s i c a l p r o p e r t i e s and chemical c o n s t i t u e n t s were evaluated
u s i n g chemistry models of f r o z e n , f i n i t e r a t e and e q u i l i b r i u m . To d e t e r mine a s t a n d a r d s t a r t i n g l i n e f o r F-1 plume c a l c u l a t i o n s , a mixing
�a n a l y s i s of t h e flow through the combustion chamber has been s t a r t e d .
A new e q u i l i b r i u m ducted mixing program i s being a p p l i e d t o d e s c r i b e
t h i s p o r t i o n of t h e nozzle flow.
b.
Nozzle and J e t Wake
A d e t a i l e d s t u d y of t h e flow f i e l d i n t h e R ~ motor
D
i s i n progress f o r two f u e l / o x i d i z e r combinations. The study includes
p r e d i c t i o n of continuum flow f i e l d c h a r a c t e r i s t i c s i n t h e combus t i o n
chamber and nozzle i n a d d i t i o n t o continuum and free-molecular flow
f i e l d c h a r a c t e r i s t i c s i n , t h e plume. The a n a l y s i s of t h e flow f i e l d f o r
t h e Aerozine-50/Nitrogen-tetroxide system has been completed i n t h e
continuum regime including t h e e f f e c t s of O/F g r a d i e n t s and frozen
chemistry. The flow f i e l d i n t h e f r e e molecular regime i s being
predicted .
P r e d i c t i o n of t h e flow f i e l d f o r t h e Monomethyldrazine/
N i t r o g e n - t e t r o x i d e system is i n progress. E f f o r t s a r e c u r r e n t l y being
concentrated on p r e d i c t i n g t h e continuum flow f i e l d c h a r a c t e r i s t i c s i n
t h e combus t i o n chamber and nozzle.
A usable condensation model f o r multi-component vapor
expans i o n i s being e s t a b l i s h e d . The g r e a t e s t amount of experimental
and t h e o r e t i c a l work done on condensation of expanding gases has been
concerned w i t h pure vapors. For r e a l i s t i c a p p l i c a t i o n s , a n engineer
must determine t h e e f f e c t s of condensation i n a m u l t i - s p e c i e s vapor.
Modifications of e x i s t i n g pure vapor t h e o r i e s a r e being i n v e s t i g a t e d
and used t o p r e d i c t t h e e f f e c t s of condensation i n a multi-component
expand ing flow.
7.
Laser Velocimeter S t u d i e s
A l a s e r doppler velocimeter t h a t w i l l measure t h r e e veloci t y components i n a p a r t i c u l a r seeded flow has been developed and made
o p e r a t i o n a l . I t i s c u r r e n t l y being used f o r flow v e l o c i t y and turbulence
measurements i n t h e plume of a subsonic j e t . Future a p p l i c a t i o n s include
s t u d i e s of t h e mixing r e g i o n of a s u p e r s o n i c j e t , flows around high angle
of a t t a c k aerodynamic p r o f i l e s , and base flow i n t e r a c t i o n s .
The f e a s i b i l i t y of using a C 0 2 l a s e r doppler velocimeter t o
measure t h e v e l o c i t y of atmospheric motions has been demonstrated b o t h
a n a l y t i c a l l y and experimentally. The design of a p r a c t i c a l prototype
s y s tem t o measure ground wind v e l o c i t i e s i s complete and t h e s y s tem i s
being f a b r i c a t e d .
P o t e n t i a l a p p l i c a t i o n s t o long range wind v e l o c i t y measurement and c l e a r air turbulence d e t e c t i o n a r e being considered.
�8.
Plume Impingement Heating
Heating r a t e s t o v a r i o u s components on t h e S a t u r n / ~ Pconf i g u r a t i o n due t o plume impingement a r e being c a l c u l a t e d . P r e l i m i n a r y
v a l u e s have a l r e a d y been determined and d e l i v e r e d t o R-P&VE. These
v a l u e s a r e now being r e f i n e d u s i n g more a c c u r a t e plume flow f i e l d
chemistry and h e a t i n g r a t e c a l c u l a t i o n t e c h n i q u e s . S p e c i f i c a r e a s
b e i n g cons i d e r e d a r e :
9.
(1)
Impingement of LM/RCS engine on MDA r a d i a t i o n .
(2)
Impingement of LN/RcS engines on f o l d e d ATM s o l a r
panels
(3)
Impingement of CSM/RCSengines on unfolded ATM
s o l a r panels.
(4)
Impingement of CSM/RCS engines on MDA forward cone.
.
Transonic S o l u t i o n
A new technique t o s o l v e simultaneous p a r t i a l d i f f e r e n t i a l
e q u a t i o n s , d e s i g n a t e d a s a f r e e - e r r o r minimization technique, has been
a p p l i e d t o t h e r e l a t i v e l y simple c a s e of i s e n t r o p i c i n v i s c i d flow of a n
i d e a l gas through a n o z z l e . The minimization technique s o l v e s t h e e n t i r e
flow f i e l d ( s u b s o n i c , t r a n s o n i c , and s u p e r s o n i c ) a s a boundary v a l u e
problem. To d a t e , t h e t r a n s o n i c and s u p e r s o n i c p o r t i o n s of t h e n o z z l e
flow f i e l d a r e v e r y encouraging, a l t h o u g h t h e s u b s o n i c p o r t i o n i s n o t
r e l a x i n g a s expected. The problems of s c a l i n g and i n t e r n a l and e x t e r n a l
communication b e tween t h e t h r o a t r e g i o n and t h e en t r a n c e p l a n e a r e being
explored. The i d e a l gas t r a n s o n i c r e s u l t s would i n d i c a t e t h a t t h i s
method can b e used t o s o l v e much more complex f l u i d mechanics problems.
10.
Continuum Heating and Miss i o n Support
Work has begun on t h e modeling of t h e S a t u r n AS-501 v e h i c l e
f o r t h e purpose of c a l c u l a t i n g clean-body h e a t i n g r a t e s u s i n g t h e
Lockheed SHORE-CATCH computer program. Heating r a t e s w i l l be compared
t o f l i g h t d a t a . I n a r e a s of p r o t u b e r a n c e s , t e s t d a t a w i l l be used t o
a d j u s t t h e clean-body h e a t i n g r a t e s . Recommendations w i l l be made a s t o
which a n a l y t i c a l techniques should b e used t o p r e d i c t aerodynamic h e a t i n g
r a t e s on f u t u r e S a t u r n f l i g h t s .
S i m i l a r o r b i t a l h e a t i n g r a t e s w i l l b e c a l c u l a t e d on t h e
AS-203 v e h i c l e , and t h e r e s u l t s compared t o f l i g h t d a t a t o v e r i f y accuracy
of t h e Heat Rate Program.
�The SHORE-CATCH i s being modified t o add f l e x i b i l i t y i n
i n p u t t i n g p r e s s u r e d a t a , and t o add t h e c a p a b i l i t y of c a l c u l a t i n g h e a t
r a t e s i n t h e s l i p flow regime.
E.
Experimental Aerophysics Branch
1.
Low Density Chamber
Examination of t h e experimental j e t plume (C02) d a t a i n d i c a t e s t h a t t h e n o z z l e w a l l temperature f l u c t u a t i o n s a r e of such magnit u d e a s t o a d v e r s e l y a f f e c t t h e impact p r e s s u r e . Because of t h e long
r u n times p o s s i b l e , a l a r g e amount of h e a t i s b e i n g t r a n s f e r r e d t o t h e
n o z z l e w a l l ; t h e r e f o r e , a n a t t e m p t i s being made t o cool t h e n o z z l e
w a l l ( o r a t l e a s t m a i n t a i n t h e w a l l a t a c o n s t a n t known temperature).
The n o z z l e w a l l temperature i n v e s t i g a t i o n precedes f u r t h e r work w i t h
a l a r g e r nozzle.
A c l o s e r look w i t h t h e S a f e t y O f f i c e i n t o t h e p o s s i b i l i t y
of u s i n g l i q u i d hydrogen i n t h e cryo-panels t o i n c r e a s e t h e c a p a b i l i t y
of t h e Low Density Chamber r e v e a l s no insurmountable problem. An
in-house s t u d y i s b e i n g done w i t h t h e end r e s u l t t o be a g u i d e l i n e
d e s c r i b i n g why, where, and how we a r e going t o u s e t h e LH2 f o r p r e s e n t a t i o n t o t h e S a f e t y Off i c e .
The e l e c t r o n beam work being c a r r i e d on by D r . B e y l i c h has
progressed t o t h e p o i n t of r e c e i v i n g most of t h e ordered equipment and
having t h e e l e c t r o n gun and a s s o c i a t e d hardware i n t h e f i n a l d e s i g n
s t a g e s . This i n s t r u m e n t a t i o n i s t o be used i n t h e gas d e n s i t y d e t e r m i n a t i o n s of t h e p r e s e n t j e t plume work. I f t h e r e e x i s t s t h e p o s s i b i l i t y t o add N2 o r u s e N2 e n t i r e l y i n t h e j e t plume s t u d i e s , t h e n t h e
e l e c t r o n beam measurements w i l l b e extended t o i n c l u d e r o t a t i o n a l
temperature.
2.
Impulse Base Flow F a c i l i t y
The experimental program i n s u p p o r t of t h e S-IVB workshop
plume impingement problems was continued. The e n t i r e analog d a t a r e c o r d ing system of o s c i l l o s c o p e s and cameras has been r e p l a c e d by t h e t h i r t y two-channel d i g i t a l d a t a s y s tem o r i g i n a l l y used f o r t h e shock t u n n e l .
The s y s tem i s now o n - l i n e and working s a t i s f a c t o r i l y . A program f o r
reducing t h e d i g i t a l d a t a a u t o m a t i c a l l y has been w r i t t e n and i s b e i n g
used. This g r e a t l y reduces time and e f f o r t expended i n hand d a t a
reduction a t the f a c i l i t y .
As a segment of t h e c o n t i n u i n g e f f o r t t o i n c r e a s e t h e
f a c i l i t y o u t p u t , a system t o i s o l a t e t h e engine model from t h e vacuum
�t a n k a f t e r a r u n i s being designed. This s y s tem w i l l c o n s i s t of a l a r g e
v a l v e t o b e c l o s e d a s t h e model p r e p a r a t i o n i s being done, t h e r e b y removi n g t h e n e c e s s i t y of v e n t i n g t h e e n t i r e tank a f t e r each r u n . The pacing
i t e m w i l l then become t e c h n i c i a n e f f i c i e n c y r a t h e r than vacuum pumping
c a p a c i t y . This i s expected t o more than double t h e f a c i l i t y o u t p u t .
As a means of extending t h e c a p a b i l i t y of t h i s f a c i l i t y ,
a cryo-panel w i l l be i n s t a l l e d . It i s hoped t h a t t h i s panel w i l l a b s o r b
t h e n o z z l e - s t a r t i n g shock system, a s w e l l a s t h e engine flow, and e f f e c t i v e l y extend t h e r u n time. Furthermore, a d d i t i o n a l a l t i t u d e s i m u l a t i o n
c a p a b i l i t y w i l l be a v a i l a b l e . S t u d i e s a r e now a l m o s t complete f o r a l l
phases. Two m a t e r i a l s have been s e l e c t e d f o r p o s s i b l e use i n f a b r i c a t i n g
t h e cryo-panel:
a bonded aluminum honeycomb and a n extruded f i n n e d
aluminum. The honeycomb m a t e r i a l seems t o have aerodynamic advantages
b u t thermal drawbacks; t h r e e t e s t specimens a r e being prepared by ME
Laboratory f o r e v a l u a t i o n i n t h e Low Density Chamber. Scheduled d e l i v e r y
f o r t h e s e specimens i s December 2, 1968. A t t h e c o n c l u s i o n of t h e s e
e v a l u a t i o n t e s t s , t h e b e t t e r con£ i g u r a t i o n w i l l be s e l e c t e d , and d e t a i l
d e s i g n and procurement on n e c e s s a r y items i n i t i a t e d . A s u r p l u s l i q u i d
n i t r o g e n t a n k has been o b t a i n e d from R-TEST f o r cryogenic s t o r a g e .
3.
High Reynolds Number Equipment
The f i r s t low p r e s s u r e t e s t of t h e High Reynolds Number
T e s t Equipment i s expected around t h e f i r s t of January. A l l t e s t hardware and a s s o c i a t e d equipment i s on hand e x c e p t t h e s u p e r s o n i c t e s t s e c t i o n which w i l l be shipped November 29, 1968.
Welding and c l e a n i n g of t h e supply tube may s l i p t h e above
t e s t d a t e . However, i f work c o n t i n u e s w i t h o u t d e l a y , t h e f i r s t of t h e
y e a r seems r e a s onable.
4.
Thermal A c o u s t i c J e t F a c i l i t y
Two major problems remain i n t h e helium h e a t e r checkout by
t h e c o n t r a c t o r (Fuel Engineering).
The f i r s t , a temperature i n s t a b i l i t y
i n t h e flow, i s being s t u d i e d by t h e c o n t r a c t o r and h i s c o n s u l t a n t , who
a r e now of t h e o p i n i o n t h a t a redesigned s e t t l i n g chamber w i l l cure t h e
i n s t a b i l i t y . The second problem i s that t h e temperature of t h e o u t p u t
flow i s c o n s i d e r a b l y lower t h a n t h e s t o r a g e mass temperature, s u c h a s
o n l y 900 OF f o r a s t o r a g e temperature of 1200 OF. This problem i s s t i l l
unsolved
.
The cold flow d u c t was i n a c t i v e d u r i n g t h i s period b u t i s
b e i n g r e a d i e d f o r f u r t h e r crossed-beam t e s t i n g .
�5.
14 x 14-Inch T r i s o n i c Tunnel
a. An i n v e s t i g a t i o n t o f u r n i s h d a t a f o r quasi-steady
a n a l y s i s i n t h e production of aerodynamic damping of various launch
The t e s t d a t a a r e
v e h i c l e s was conducted by LMSC f o r R-AERO-AUA.
r e q u i r e d f o r c o r r e l a t i o n w i t h t h e a n a l y t i c a l method and f o r e v a l u a t i n g
t h e communication time o r l a g e f f e c t s on t h e flow f i e l d . The t e s t cons i s t e d of both forced and f r e e o s c i l l a t i o n dynamic t e s t i n g . Total runs:
68.
b. An i n v e s t i g a t i o n t o f u r n i s h information on cross-beam
survey of axisymmetric base flows i n t h e s p e c i a l t e s t s e c t i o n of t h e TWT
was conducted by NSL f o r R-AERO-AE.
This t e s t had four o b j e c t i v e s :
(1) To determine t h e c h a r a c t e r i s t i c of a l a s e r crossbeam system when a p p l i e d t o base flow i n the modified s p e c i a l t e s t
section.
(2) To determine t h e adequacy of n a t u r a l t r a c e r s t o
produce s u f f i c i e n t beam modulation o r t h e a r t i f i c i a l t r a c e r concentrat i o n r e q u i r e d f o r t h e s t u d y of t u r b u l e n t f r e e shear l a y e r s .
(3) To determine a p p l i c a b i l i t y of p l e x i g l a s s o u t e r
w a l l e x t e n s i o n f o r suppressing t h e l a r g e c o n t r i b u t i o n s t o t h e cross-beam
s i g n a l s caused by t h e f r e e s h e a r l a y e r s of t h e o u t e r wall.
(4)
To determine t h e e f f e c t s of extraneous n o i s e sources.
S i x t y - e i g h t runs were made.
c. An i n v e s t i g a t i o n was conducted, f o r R-AERO-AD, t o prov i d e experimental l o c a l normal f o r c e d a t a , f o r comparison w i t h a computer
program which c a l c u l a t e d l o c a l normal f o r c e g r a d i e n t on cone-cylinder
bodies i n s u p e r s o n i c f l o w . . T o t a l runs: 3 4 .
d . An i n v e s t i g a t i o n was conducted, f o r R-AERO-AU, t o d e t e r mine t h e boundary l a y e r c h a r a c t e r i s t i c behind a roughened s e c t i o n of an
otherwise smooth w a l l . This i n v e s t i g a t i o n was performed t o analyze a
proposed method by McDonnell-Douglas Corporation p r e p a r a t o r y t o the upcoming
panel f l u t t e r t e s t s i n t h e Ames 2-foot supersonic wind tunnel. T o t a l runs:
49.
e. An i n v e s t i g a t i o n was conducted f o r R-AERO-AD t o e v a l u a t e
t h e e f f e c t s of varying sting-to-model diameters f o r a i d i n analyzing
viscous c r o s s flow d a t a . Some d i f f e r e n c e is apparent i n t h e s t a t i c s t a b i l i t y d a t a . This d i f f e r e n c e can be a t t r i b u t e d t o s e v e r a l a r e a s , such a s
Reynolds number s t i n g v a r i a t i o n blockage, e t c . The t e s t i s s t i l l i n
progress.
�6.
7 x 7-1nch B i s o n i c Wind Tunnel
As a r e s u l t of i n f o r m a t i o n obtained from the cross-beam
t e s t i n t h e s p e c i a l t e s t s e c t i o n of t h e TWT, a n i n v e s t i g a t i o n has been
i n i t i a t e d i n t h e BWT t o develop cross-beam technology a p p l i c a b l e t o wind
t u n n e l flows. The c u r r e n t i n v e s t i g a t i o n i s being conducted by R-AERO-AF
on a n i n d e f i n i t e s c h e d u l e .
7.
Data Reduction
Besides t h e r o u t i n e f a c i l i t y d a t a r e d u c t i o n , t h e f o l l o w i n g
work w a s performed:
( a ) C o n t i n u a t i o n of t h e program f o r D r . Beylich r e g a r d i n g
t h e o r e t i c a l gas dynamics. Problems which were encountered u s i n g t h e high
o r d e r numerical i n t e g r a t i o n procedures of t h e R-COMP MARVESS language
have now been r e s o l v e d .
(b) The Low D e n s i t y Chamber program was f i n i s h e d , i n c l u d i n g
t h e p l o t t i n g r o u t i n e s . S e v e r a l dozen r u n s have been reduced using o n - l i n e
plotting.
( c ) A program t o reduce t h e d i g i t a l d a t a from t h e IBFF was
w r i t t e n and checked. This program a v e r a g e s the many d a t a p o i n t s taken
d u r i n g t h e quas i-s teady c o n d i t i o n s of 5-10 m i l l i s e c o n d s , computes t h e
s t a t i s t i c a l a n a l y s i s of t h e s t e a d i n e s s , and p r i n t s o u t t h e d a t a i n
e n g i n e e r i n g u n i t s . The program a p p e a r s t o work s a t i s f a c t o r i l y f o r t e s t
cases.
8.
I n s trumenta t i o n
a.
High Response Balance
One phase of t h e jet-plume s t u d i e s i n t h e Impulse Base
Flow F a c i l i t y c o n s i s t s of f o r c e measurements on a f l a t p l a t e . The f a c i l i t y run-time of 5-10 m i l l i s e c o n d s r e q u i r e s h i g h r e s p o n s e b a l a n c e s f o r such
measurements. A b a l a n c e l e f t from t h e shock t u n n e l e f f o r t s which appears
t o be s u i t a b l e f o r i n i t i a l work, i s being r e a d i e d f o r t h i s t e s t . The
magnitude of t h e l o a d s , t y p i c a l l y l e s s t h a n one pound, p r e s e n t s unusual
problems. New b a l a n c e s a r e b e i n g designed and f a b r i c a t e d f o r t h i s work.
b
.
Cross ed-Beam Support
The van which was o r i g i n a l l y equipped f o r t h e Colorado
f i e l d t e s t s has been r e t u r n e d t o MSFC. A f t e r r e t u r n , i t was r e f u r b i s h e d
f o r t h e m u l t i - d e t e c t o r f i e l d t e s t s to' be conducted a t MSFC. The d e t e c t o r s
f u r n i s h e d by IITRI have been i n s t a l l e d and a r e b e i n g checked o u t . The
�parking l o t i s being used a s t h e t e s t s i t e f o r the checkout work, w i t h
cons i d e r a t i o n b e i n g g i v e n t o f i e l d t e s t i n g a t t h e R-AERO-Y Atmospheric
Research F a c i l i t y .
F.
Unsteady Gas Dynamics Branch
1.
Ground Winds
Load p r e d i c t i o n s published on August 29, 1968, f o r t h e
AS-503 manned v e h i c l e corresponding t o miss i o n D dynamic c h a r a c t e r is t i c s
have been checked f o r t h e C' m i s s i o n dynamic c h a r a c t e r i s t i c s and a r e cons i d e r e d a p p l i c a b l e . Based upon a v a i l a b l e d a t a , load p r e d i c t i o n s f o r t h e
AS-504 manned v e h i c l e were published on November 27, 1968. For t h e
a v a i l a b l e d a t a , t h e s e p r e d i c t i o n s were made f o r a l l b a s i c on-pad weight
c o n f i g u r a t i o n s w i t h and w i t h o u t t h e MSS and w i t h and w i t h o u t t h e damper
a t t a c h e d (where a p p l i c a b l e ) .
A s t u d y f o r determining t h e second mode e f f e c t s on ground
wind l o a d i n g s f o r t h e S a t u r n V v e h i c l e i s s t i l l i n p r o g r e s s . Also, a
s t u d y i s i n p r o g r e s s t o determine t h e v a r i a t i o n i n bending moment pred i c t i o n s f o r v a r i o u s wind p r o f i l e s .
E f f o r t s a r e underway t o f u l l y reduce a l l a v a i l a b l e S a t u r n V
wind t u n n e l t e s t d a t a us ing t h e Lockheed s t a t i s t i c a l a n a l y s i s program and
a Boeing d a t a a n a l y s i s program f o r r e f i n i n g load p r e d i c t i o n s f o r a l l wind
d i r e c t ions and complex con£ i g u r a t i o n s
.
2.
I n f 1i g h t A c o u s t i c s
a. Data r e d u c t i o n a n a l y s i s has begun on t h e AEDC 4 p e r c e n t
model s u p e r s o n i c d a t a . O v e r a l l l e v e l s s c a l e d t o f u l l s c a l e c o n d i t i o n s
a r e b e i n g computed and p l o t t e d . Cross spectrum a n a l y s i s w i l l begin upon
completion of t h e o v e r a l l a n a l y s i s .
b. Model f a b r i c a t i o n and i n s t r u m e n t a t i o n i n s t a l l a t i o n i s
b e i n g completed f o r t h e shock-turbulence i n t e r a c t i o n experimental s t u d i e s
b e i n g conducted i n t h e 7-inch MSFC s u p e r s o n i c wind t u n n e l by Wyle Labs.
This experiment should r u n a b o u t one week.
c. A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l
I n f l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " has been i n i t i a t e d .
Data from Ames, f o u r - p e r c e n t S a t u r n V, PSTL-1 and PSTL-2 wind t u n n e l
t e s t c o n d i t i o n s , and f l i g h t w i l l b e used, a l o n g w i t h o t h e r d a t a a v a i l a b l e
i n t h e 1i t e r a t u r e . P r e l i m i n a r y d a t a r e d u c t i o n i s being continued
.
�d. A program has been conducted i n t h e AEDC 16-foot t r a n s o n i c tunnel t o provide experimental information t o h e l p d e r i v e methods
by wllicll f l u c t u a t i n g a i r l o a d s i n t h e r e g i o n of protuberances can
a c c u r a t e l y be p r e d i c t e d on launch v e h i c l e s , i n s u p p o r t of a c o n t r a c t with
Wyle L a b o r a t o r i e s , H u n t s v i l l e , A l a b a m a , e n t i t l e d " ~ n v i r o r n n e n tAround Protuberances Submerged i n a Boundary Layer."
The s t a t i c p r e s s u r e d a t a a r e
b e i n g a n a l y z e d , and t h e f l u c t u a t i n g p r e s s u r e d a t a a r e b e i n g reduced.
~
wind t u n n e l t e s t program which
e. A j o i n t M S F C / A ~ Force
c o n s i s t e d of s e v e r a l b i c o n i c nose c o n f i g u r a t i o n s has been conducted.
These con£ i g u r a t i o n s p r o v i d e a bas i s f o r a n a l y z i n g t h e c r o s s c o r r e l a t i o n
c h a r a c t e r i s t i c s ( n e c e s s a r y f o r d e s i g n c r i t e r i a ) of t h e i n £ l i g h t f l u c t u a t i n g p r e s s u r e environment f o r v a r i o u s AAP miss i o n s . C a r e f u l planning i s
r e q u i r e d t o a c h i e v e t h e optimum s e l e c t i o n of d e s i g n i n f o r m a t i o n from t h e
tremendous amount of p o s s i b l e d a t a t o be reduced. The A i r Force, v i a
Lockheed, paid f o r t h e i n i t i a l d a t a r e d u c t i o n c o n s i s t i n g of a few o v e r a l l l e v e l s s p e c t r a . The p r e l i m i n a r y d a t a a r e being analyzed.
f . A t e s t t o a c o u s t i c a l l y c a l i b r a t e t h e MSFC 14-inch wind
t u n n e l was completed September 17 by p e r s o n n e l of t h e C h r y s l e r Corporation.
The primary o b j e c t i v e of t h i s t e s t was t o measure background p r e s s u r e
f l u c t u a t i o n s g e n e r a t e d by t h e t u r b u l e n t boundary l a y e r on t h e t u n n e l
w a l l s and by v a r i o u s o t h e r components of t h e wind t u n n e l . The Mach
number r a n g e s f o r which t h i s t e s t was conducted was 0.4 t o 4.0; o t h e r
v a r i a b l e s were w a l l p o r o s i t y , Reynolds number, and t u n n e l c o n f i g u r a t i o n .
The c a l i b r a t i o n d e v i c e ( o r model) used was a 10-degree-included-angle
cone w i t h two f l a t s u r f a c e s 180 degrees a p a r t f o r flush-mounting dynamic
p r e s s u r e t r a n s d u c e r s . The f l u c t u a t i n g p r e s s u r e d a t a were recorded on
magnetic t a p e . P r e l i m i n a r y d a t a r e d u c t i o n and a n a l y s i s a r e i n p r o g r e s s .
3.
Launch S i t e A c o u s t i c s
a. Papers were p r e s e n t e d by Messrs. Guest and Jones a t t h e
r e c e n t Langley Conference (8-10 October) on t h e "Progress of NASA Research
The proR e l a t i n g t o Noise A l l e v i a t i o n s of Large Subsonic J e t A i r c r a f t . "
ceedings of t h e conference have been published a s a NASA SP-189.
b. A c t i v i t y a t t h e A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t
T e s t Laboratory has slowed down d u r i n g t h e p a s t month. P l a n s a r e now
being i n i t i a t e d t o conduct t h e 20-percent S a t u r n V model r o c k e t n o i s e
experiment, which has been designed t o o b t a i n amplitude and phase i n £ o r mation f o r b o t h t h e l a u n c h and s t a t i c f i r i n g c o n d i t i o n of t h e S a t u r n V
v e h i c l e . S p e c t r a l and s p a t i a l c o r r e l a t i o n c h a r a c t e r i s t i c s w i l l be
obtained f o r t h e v e h i c l e a s w e l l a s t h e immediate launch complex a r e a .
This t e s t i s scheduled t o b e g i n i n January.
�c. The s t u d y of ground a t t e n u a t i o n e f f e c t s on a c o u s t i c
wave p r o p a g a t i o n is b e i n g continued w i t h t h e m e t e o r o l o g i c a l parameters
being analyzed i n more d e t a i l . A model more a p p l i c a b l e i n terms of t h e
p h y s i c a l phenomena i s b e i n g sought f o r p r e d i c t i o n accuracy a p p l i c a t i o n s .
4.
Panel F l u t t e r
a . A p r e - t e s t conference concerning t h e upcoming h i g h amplitude S a t u r n V/S-IVB panel f l u t t e r t e s t (NASA-21250) was held a t Arnes
Research Center on November 1 3 , 1968, w i t h r e p r e s e n t a t i v e s from MSFC, ARC,
and McDonnell-Douglas C o r p o r a t i o n a t t e n d i n g . The following agenda were
discussed:
(1)
Review of Wind Tunnel T e s t Program O b j e c t i v e s .
(2)
I n s t r u m e n t a t i o n and Data A c q u i s i t i o n .
(3)
GFE Requirements
(4)
V i s i t t o Tunnel F a c i l i t y
wind t u n n e l .
(5)
Hardware d e s c r i p t i o n .
(6)
D e t a i l e d t e s t procedure.
- ARC
2 x 2-foot t r a n s o n i c
It was concluded t h a t a l l hardware and equipment should be a t ARC a t
l e a s t one week b e f o r e t h e t u n n e l e n t r y , which has been t e n t a t i v e l y s e t
f o r February 3 , 1969.
b. S t a t u s of t h e government f u r n i s h e d equipment f o r t h e
high-amplitude S-IVB panel f l u t t e r t e s t s is as follows: The RFQ f o r t h e
n o n c o n t a c t i n g displacement meters has been r e l e a s e d . No p r o p o s a l s have
y e t been r e c e i v e d . The boundary l a y e r r a k e d e s i g n , which has been
r e c e i v e d from t h e McDonnell-Douglas C o r p o r a t i o n , i s being f a b r i c a t e d by
the wind t u n n e l (MSFC) machine shop. I n a d d i t i o n , MSFC w i l l s u p p l y seven
s t r a i n gage b r i d g e b a l a n c e u n i t s ; seven h i g h g a i n , low n o i s e "broad band
a m p l i f i e r s " ; and two root-mean-square v o l t m e t e r s . Ames w i l l s u p p l y one
f o u r t e e n - c h a n n e l magnetic t a p e r e c o r d e r , one d i r e c t - w i r i n g o s c i l l o g r a p h
r e c o r d e r , two o s c i l l o s c o p e s , one D.C. v o l t m e t e r , one 16 mm h i g h speed
camera, f i v e p r e s s u r e t r a n s d u c e r s , and a p r e s s u r e c o n t r o l v a l v e f o r
r e g u l a t i n g t h e c a v i t y p r e s s u r e . A l l items a r e a v a i l a b l e w i t h t h e
e x c e p t i o n of t h e noncontacting displacement m e t e r s . This may cause a
s l i g h t slippage i n t h e tunnel e n t r y date.
�c. The roughened s o l i d s i d e w a l l boundary l a y e r p r o f i l e
i n v e s t i g a t i o n conducted i n t h e MSFC 14 x 14-Inch T r i s o n i c Wind Tunnel
was completed November 1 5 , 1968. Made i n s u p p o r t of the upcoming panel
f l u t t e r t e s t mentioned i n ( a ) above, t h i s t e s t was t o determine t h e
boundary l a y e r c h a r a c t e r i s t i c s r e s u l t i n g from roughening a s e c t i o n of
a n o t h e r w i s e smooth w a l l t o i n c r e a s e t h e boundary l a y e r t h i c k n e s s . To
accomplish t h i s , .3125-inch diameter r o l l p i n s were d i s t r i b u t e d over t h e
l e a d i n g 8 inches of t h e smooth w a l l , and t h r e e p i n h e i g h t s ( h e i g h t above
wall:
0, .118 and.250 i n c h e s ) were t e s t e d . Boundary l a y e r p r o f i l e s were
measured a t t h r e e l o c a t i o n s , f o r t h r e e Mach numbers, and f o r two Reynolds
numbers. The d a t a o b t a i n e d looks good, and i s now being analyzed.
5.
Quas i-S teady Analys i s
a. The Shock-Induced S e p a r a t i o n Study program was conducted i n t h e MSFC 14-inch t u n n e l from September 19 through October 7 ,
1968. The f a c i l i t i e s a t t h e MSFC's 14-inch t u n n e l a r e b e i n g used f o r
data reduction.
.
Under c o n t r a c t NAS8- 21459, t h e quas i-s teady techniques
b
a r e b e i n g extended by Lockheed t o provide t h e c a p a b i l i t y t o compute g u s t
p e n e t r a t i o n l o a d s on t h e S a t u r n v e h i c l e s , i n c l u d i n g t h e e f f e c t s of
s e p a r a t e d flow. These techniques a r e b e i n g developed t o determine t h e
aerodynamic damping f o r v a r i o u s s t r u c t u r a l modes by assuming t h a t t h e
v e h i c l e w i l l f l y through a s i n u s o i d a l g u s t of c o n s t a n t amplitude and
wavelength. This c o n t r a c t i s b e i n g extended t o r e f i n e t h e q u a s i - s t e a d y
techniques developed f o r t h e computation of t h e dynamic e f f e c t s of
s e p a r a t e d flow i n c l u d i n g t h e e f f e c t s of g u s t loadings on t h e a e r o e l a s t i c
s t a b i l i t y c h a r a c t e r i s t i c s of t h e S a t u r n launch v e h i c l e s . These a n a l y t i c a l
techniques w i l l b e expanded ( i f f e a s i b l e ) t o i n c l u d e more r e a l i s t i c
i n f l i g h t g u s t environments.
This c o n t r a c t i s a l s o being expanded t o p r e d i c t t h e
a e r o e l a s t i c c h a r a c t e r i s t i c s , by u s e of t h e quas i-s teady techniques
The i n c r e a s e
developed, of t h e S a t u r n V v e h i c l e s AS-505 through AS-508.
i n t h e scope of work w i l l become e f f e c t i v e on February 1, 1969, and t h e
c o n t r a c t ending d a t e extended t o March 31, 1970.
V.
AEROSPACE ENVIRONMENT DIVISION
A.
Atmosphere Dynamics Branch
1.
S u r f a c e Wind Data
S u r f a c e wind speed and d i r e c t i o n d a t a a t t h e KSC Launch Pads
a n d / o r NASA's 150-meter M e t e o r o l o g i c a l Tower F a c i l i t y were provided a s
follows:
�(.I) Memorandum R-AERO-YE-171-68 p r e s e n t e d d a t a recorded
d u r i n g launch o p e r a t i o n s of AS-205 on October 11, 1968, from Launch
Complex 34.
(2) Memorandum R-AERO-YE-173-68 concerned d a t a obtained a t
Launch Complex 39 d u r i n g h u r r i c a n e "Gladys" on October 17-19, 1968, f o r
R-P&VE-SL t o determine maximum v e h i c l e response and s t r a i n guage d r i f t
on a S a t u r n V v e h i c l e .
(3) C u r r e n t d a t a recorded a t t h e m e t e o r o l o g i c a l tower were
s e n t t o t h e Manned S p a c e c r a f t Center f o r Apollo command module
l a n d i n g impact t e s t s s i m u l a t i n g a n off-the-pad a b o r t under v a r i o u s
launch wind c o n d i t i o n s .
( 4 ) Two y e a r s of reduced m e t e o r o l o g i c a l tower d a t a were
provided t h e Boeing Company, S e a t t l e , t o s t u d y g u s t f a c t o r s , s t a b i l i t y
c o n d i t i o n s , e t c . , f o r t h e s u p e r s o n i c t r a n s p o r t program.
2.
Jimsphere Wind Data f o r S p e c i a l S t u d i e s
C o o r d i n a t i o n and p l a n s f o r t h e s u p p o r t of v a r i o u s turbul e n c e programs u s i n g Jimsphere wind p r o f i l e d a t a have been accomplished
by p e r s o n n e l of R-AERO-YE.
Support i s intended f o r t h e f o l l o w i n g
programs :
(1) R-AERO-Y/SRI LIDAR (Light D e t e c t i o n and Ranging) probing program t o d e t e c t t u r b u l e n c e a l o f t a t Half Moon Bay, C a l i f o r n i a , i n
January 1969 under c o n t r a c t NAS8-21117.
(2) LRC/ESSA/AFCRL t u r b u l e n c e a l o f t (CAT) program t o b e
conducted d u r i n g t h e p e r i o d January-March 1969 a t Wallops I s l a n d , V i r g i n i a .
(3) I n s u p p o r t t o LRC/ESSA mountain l e e wave s t u d y a t
Edwards AFB, C a l i f o r n i a d u r i n g t h e period of February-March 1969.
A l l i n f o r m a t i o n a c q u i r e d on t u r b u l e n c e a l o f t , whether s e v e r e , m o d e r a t e , ,
o r l i g h t , w i l l become a v a i l a b l e from t h e s e s t u d i e s f o r updating environmental c r i t e r i a t o d e s i g n and launch l a r g e space v e h i c l e s .
3.
Atmospheric Turbulence Boundary Layer P r o j e c t
a.
Pennsylvania S t a t e U n i v e r s i t y (NASA C o n t r a c t NAS8-21140)
Penn S t a t e has completed a n a l y s e s of t h e v e r t i c a l
coherence f u n c t i o n s of t h e l o n g i t u d i n a l and l a t e r a l components of
These
t u r b u l e n c e , and has t r a n s m i t t e d them t o NASA (R-AERO-YE)
coherence f u n c t i o n s d e s c r i b e t h e c o r r e l a t i o n between t h e F o u r i e r
.
�coin?.jl.t n t s of t h e l o n g i t u d i n a l and l a t e r a l components of t u r b u l e n c e
a s s o c i a t e d w i t h frequency w between two l e v e l s i n t h e v e r t i c a l a t
h e i g h t s zl and z2 ( z l and z2
150 m). These coherence f u n c t i o n s a r e
i n dimensionless form and a r e s c a l e d i n terms of zl, z2, and t h e q u a s i - ,
s t e a d y wind speeds a t l e v e l s zl and z2.
-
b.
C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s (NASA C o n t r a c t
NAS8-21178)
The C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s have completed
t h e i r a n a l y s e s of t h e l a t e r a l spectrum of t u r b u l e n c e and have t r a n s m i t t e d
t h e r e s u l t s t o R-AERO-YE.
The l a t e r a l component of t u r b u l e n c e i s p e r p e n d i c u l a r t o q u a s i - s t e a d y wind speed v e c t o r . This spectrum i s s c a l e d
i n terms of t h e t a n g e n t i a l eddy s t r e s s a t t h e s u r f a c e of t h e e a r t h , t h e
h e i g h t z above t h e s u r f a c e of t h e e a r t h , and t h e q u a s i - s t e a d y wind speed
a t h e i g h t z . Thus, t h e l a t e r a l spectrum is g i v e n i n terms of a dimensionl e s s function.
c
.
In-Hous e Inves t i g a t i o n s
The a n a l y s i s of t h e l o n g i t u d i n a l spectrum of t u r b u l e n c e
has been completed. The l o n g i t u d i n a l component of t u r b u l e n c e i s p a r a l l e l
t o t h e q u a s i - s t e a d y wind v e c t o r . Here a g a i n , t h e l o n g i t u d i n a l spectrum
i s g i v e n by a dimensionless f u n c t i o n i n which t h e eddy s t r e s s a t t h e s u r f a c e of t h e e a r t h , t h e h e i g h t z , t h e q u a s i - s teady wind speed a t h e i g h t z.
appear a s s c a l i n g parameters.
'
d.
Turbulence Model
The Penn S t a t e , C o r n e l l Lab., and our in-house
a n a l y s e s a r e b e i n g combined i n t o a complete and t h e o r e t i c a l l y cons i s t e n t s p e c t r a l t u r b u l e n c e model.
The e n g i n e e r needs o n l y t o pres c r i b e t h e q u a s i - s t e a d y wind p r o f i l e t o o b t a i n t h e l o n g i t u d i n a l and
l a t e r a l s p e c t r a and t h e a s s o c i a t e d coherence f u n c t i o n s (and co- and
q u a d r a t u r e - s p e c t r a ) a s known f u n c t i o n s of h e i g h t z , completely d e f i n e d
f o r t h e f i r s t 150 m e t e r s of t h e atmosphere. The model can be used i n
v e h i c l e development work (low c o s t a s w e l l as r e c o v e r a b l e launch
v e h i c l e s ) and i s i n a form s u i t a b l e f o r performing p a r a m e t r i c a n a l y s e s
of v e h i c l e c a p a b i l i t i e s . These r e s u l t s w i l l appear i n a forthcoming
r e v i s e d C l i m a t i c G u i d e l i n e s Document, NASA TN's, and NASA CR's.
�B.
T e r r e s t r i a l Environment Branch
1.
In-House
a.
AS-503 Wind C o n s t r a i n t s
Considerable e f f o r t has been devoted t o determining
t h e p r o b a b i l i t y of occurrence of wind c o n s t r a i n t s s p e c i f i c a l l y f o r
AS-203 f o r o p e r a t i o n a l planning and m i s s i o n r u l e s . D i s t r i b u t i o n s of
ground winds and wind p r o f i l e i n t e r p r e t a t i o n s have been f u r n i s h e d t o
MSC f o r t h e s p a c e c r a f t l a n d i n g c o n s t r a i n t s .
b.
T e r r e s t r i a l Environment G u i d e l i n e s Document
A r e v i s e d e d i t i o n of t h e T e r r e s t r i a l Environment
( C l i m a t i c ) C r i t e r i a G u i d e l i n e s Document has been completed, e x c e p t f o r
t h e c h a p t e r on wind. Two more months w i l l b e r e q u i r e d t o complete t h e
e x t e n s i v e r e v i s ions t o t h i s important s e c t i o n .
c.
World-Wide Cloud Model
The Monte C a r l o procedures f o r s i m u l a t i n g photographic
coverage of t h e clouded e a r t h from s p a c e were completed. One procedure
p e r m i t s t h e incremental a r e a photographed on each pass t o be determined
by one minus t h e cloud cover encountered on t h a t pass.
I n the other
procedure, t h e a r e a under cons i d e r a t i o n i s d i v i d e d i n t o 100 s q u a r e s ,
w i t h each s q u a r e a s s i g n e d a number. The incremental photographic
coverage i s then determined by s e l e c t i n g t h e number of random numbers
corresponding t o t h e p e r c e n t of c l e a r sky on t h a t p a s s .
Some r e s w l t s w i l l b e published a f t e r t h e two procedures
a r e evaluated.
d.
F a r - F i e l d Sound Propagation
M r . 0. E. Smith p r e s e n t e d a paper, " E f f e c t s of Atmosp h e r i c R e f r a c t i o n on F a r - F i e l d Sound Propagation," a t t h e NASA Acoustic
Conference which was l a t e r published by Langley Research Center i n
NASA SP-189.
I n view of t h e i n t e r e s t generated by t h i s p a p e r , we a r e
p r e p a r i n g our Kaman Nuclear c o n t r a c t r e p o r t on sound p r o p a g a t i o n and
a t m o s p h e r i c v a r i a b i l i t y f o r i s s u e a s a h i g h l e v e l NASA C o n t r a c t o r Report
�2.
Contracts
a.
u n i v e r s i t y of Georgia C o n t r a c t (NAS8-11175)
The agenda items f o r a s e r i e s of seminars a t t e n d e d by
Messrs. Smith, Brown, and F a l l s a t t h e U n i v e r s i t y of Georgia on November 21,
1968, a r e l i s t e d below.
MORNING
9: 30
-
10: 00
A Modified Negative Binomial is t r i b 6 t i o n by W. 0.
W i l l i f o r d , Univers i t y of Georgia.
10:OO
-
10:30
Some Numerical I n v e s t i g a t i o n s of t h e Parameters of
Weibull D i s t r i b u t i o n s by B . J. Williams and F. R. Helm,
U n i v e r s i t y of Georgia.
10:30
-
11:OO
S t r u c t u r e s of Programs and F i l e s i n Computers by Rolf E.
Bargmann, U n i v e r s i t y of Georgia.
11: 00
-
11: 30
The Use of Markov Chains i n Atmospheric S t a t i s t i c s by
A. C. Cohen, U n i v e r s i t y of Georgia.
AFTERNOON
1:30
-
2:OO
Pearson Curves by Lee F a l l s , MSFC.
2: 00
-
2: 30
M e t e o r o l o g i c a l S t a t i s t i c s by S. C l a r k Brown, MSFC.
2:30
-
3: 00
Extreme Value S t a t i s t i c s by 0. E. Smith, MSFC.
3:OO
-
3:30
Summary and E v a l u a t i o n by C a r l F. Kossack, U n i v e r s i t y of
Ge o r g ia
.
b.
Lockheed Support C o n t r a c t (Schedule Order 1, Appendix A-1)
AS-503 launch p r o b a b i l i t y v a l u e s d e r i v e d from a n a n a l y s i s
of t h e n a t u r a l environment were published i n O f f i c e Memorandum R-AERO-YT68-68, dated November 1 8 , 1968. The atmospheric parameters considered
were c e i l i n g and v i s i b i l i t y , ground winds, and unfavorable weather
conditions. .
�Space Environment Branch
C.
1.
Study of E l e c t r o n Cooling i n t h e ~ a r t h ' sUpper Atmosphere
The c o o l i n g of i o n o s p h e r i c e l e c t r o n s through t h e e x c i t a t i o n
of t h e s p i n m u l t i p l e t s of t h e ground s t a t e of atomic oxygen have been
s tudied
This mechanism !seems t o c o n t r i b u t e s i g n i f i c a n t l y t o t h e energy
l o s s t o e l e c t r o n s i n t h e e a r t h ' s upper atmosphere. R e s u l t s have shown
t h a t a n e x p o n e n t i a l c r o s s s e c t i o n f o r t h e r e a c t i o n s seems t o f i t t h e d a t a
b e s t , w h i l e y i e l d i n g a s u b s t a n t i a l energy l o s s i n t h e e l e c t r o n c o o l i n g .
A p r e l i m i n a r y a n a l y s i s of t h i s work i s a v a i l a b l e i n a p r o g r e s s r e p o r t
by t h e Northrop s u p p o r t c o n t r a c t o r .
.
2.
I o n o s p h e r i c Disturbances Caused by t h e I n t e r a c t i o n of t h e
Space Plasma w i t h t h e ~ a r t h ' sMagnetosphere and Upper
Atmosphere
M i s s i s s i p p i S t a t e U n i v e r s i t y w i l l s t u d y t h e i n t e r a c t i o n of
t h e s o l a r plasma w i t h t h e e a r t h ' s magnetosphere and upper atmosphere t o
d e l i n e a t e t h e t y p e s of i o n o s p h e r i c d i s t u r b a n c e s caused . This information
w i l l then be i n c o r p o r a t e d i n t o t h e i o n o s p h e r i c programs now i n p r o g r e s s
t o f u r t h e r d e f i n e t h e t r a t e l i n g i o n o s p h e r i c d i s t u r b a n c e s and t h e i r
c h a r a c t e r is t i c parameters. Of p a r t i c u l a r i n t e r e s t t o t h e U n i v e r s i t y a r e
t h e Alfven waves and H a l l c u r r e n t s produced i n a magnetohydrodynamic
field
.
3.
A c o u s t i c G r a v i t y Wave Study
The f i n a l r e p o r t on t h e f i r s t y e a r ' s work on t h e coupling
of a c o u s t i c energy from t h e troposphere t o t h e thermosphere is due by
December 1 5 , 1968. The follow-on c o n t r a c t f o r t h e c o n t i n u a t i o n of t h i s
work i s being n e g o t i a t e d . During t h e second y e a r , we w i l l a s c e r t a i n
t h e predominant coupling mechanisms, examine t h e e f f e c t s of a v a r y i n g
p r o p a g a t i o n medium, and o b t a i n f u r t h e r experimental d a t a on t h e e f f e c t s
on t h e ionosphere of s t a t i c t e s t f i r i n g s and l o c a l thunderstorms.
4.
I o n o s p h e r i c Plasma I n v e s t i g a t i o n s from a n E a r t h O r b i t a l
Space S t a t i o n
R e s p o n s i b i l i t y f o r t h e d e f i n i t i o n of t h e I o n o s p h e r i c Plasma
I n v e s t i g a t i o n s t o be included i n t h e Experiment Program f o r a n E a r t h
O r b i t a l Space S t a t i o n has been a s s i g n e d t o t h i s D i v i s i o n . The e x p e r i ments t o be included i n t h i s package a r e a plasma wake experiment ( t o
s t u d y t h e i o n o s p h e r i c wake a s s o c i a t e d w i t h l a r g e s p a c e c r a f t ) and a plasma
wave p r o p a g a t i o n experiment which w i l l examine t h e harmonic resonance
a s s o c i a t e d w i t h antennas t r a n s m i t t i n g i n t o t h e magnetoplasma. Even
though t h e s e experiments have NASA Headquarters backing, much more work
needs t o be done on t h e e n g i n e e r i n g d e f i n i t i o n of t h i s program than i s
now b e i n g done.
�5.
Atmospheric Model S t u d i e s
The d e t a i l e d s t u d y program f o r t h e development of an improved
upper atmospheric model i s c o n t i n u i n g . I n s u p p o r t of t h i s program, dragdetermined d e n s i t i e s from 64 s a t e l l i t e s have been compared w i t h d e n s i t i e s
t h a t were c a l c u l a t e d u s i n g t h e MSFC Modified J a c c h i a Model Atmosphere,
1967. The model d e n s i t i e s and drag d e n s i t i e s a r e i n good agreement above
350 km a l t i t u d e ( w i t h i n 15 p e r c e n t ) , b u t d i f f e r e r r a t i c a l l y , by a s much a s
50 p e r c e n t , below t h i s a 1 t i t u d e . P r e l i m i n a r y i n v e s t i g a t i o n s have i n d i c a t e d
t h a t t h e model may be improved by c u r v e - f i t t i n g t h e model e x o s p h e r i c temp e r a t u r e t o t h e drag-determined d e n s i t y a t d i s c r e t e a l t i t u d e s and u s i n g
the r e s u l t i n g expressions t o define the a l t i t u d e density r e l a t i o n s h i p s .
This w i l l provide a n improved mass d e n s i t y model, b u t t h e atmospheric
composition and temperature t h a t a r e a s s o c i a t e d w i t h t h e mass d e n s i t y
must be o b t a i n e d b y some e m p i r i c a l technique. One such technique t h a t
is c u r r e n t l y being i n v e s t i g a t e d e n t a i l s t h e m o d i f i c a t i o n of ~ a c c h i a ' s
e x o s p h e r i c temperature e q u a t i o n s t o f o r c e them t o f i t t h e e x o s p h e r i c
temperatures t h a t have been d e r i v e d from e i g h t MSFC and twelve GSFC
thermosphere probe o b s e r v a t i o n s . S i x of t h e MSFC probes a r e p a r t i c u l a r l y
u s e f u l , s i n c e t h e y were launched a s a s e r i e s on one day and thus provided
v a l u a b l e i n f o r m a t i o n on t h e d i u r n a l v a r i a t i o n i n e x o s p h e r i c temperature.
Once t h e s e m o d i f i c a t i o n s a r e made, t h e boundary c o n d i t i o n s a t 120 km (N2,
02, and 0) w i l l be r e - e s t a b l i s h e d s o t h a t the newly modified J a c c h i a model
w i l l be i n c l o s e agreement w i t h t h e s a t e l l i t e d e n s i t i e s . These r e s u l t s
w i l l p r o v i d e a n improved r e p r e s e n t a t i o n of t h e atmospheric compos i t i o n
and temperature and t h e i r v a r i a t i o n s
.
6.
Environment C r i t e r i a
NASA TM X-53798, "Space Environment G u i d e l i n e s f o r Use i n
Space Vehicle Development, 1968 R e v i s i o n , " has been d i s t r i b u t e d . This
(Copies may be obtained
document i s a r e v i s e d v e r s i o n of NASA TM X-53521.
from R-AERO-YS. ) S p e c i a l i z e d environment c r i t e r i a i n p u t s , n o t g i v e n i n
t h i s document,have been f u r n i s h e d by R-AERO-YS f o r s e v e r a l e n g i n e e r i n g
and s c i e n t i f i c s t u d i e s i n s u p p o r t of t h e OWS/ATM and Future Space S t a t i o n (FSS) Programs. As MSFC becomes more involved i n long l i f e t i m e
o r b i t a l m i s s i o n s , such a s OWSIATM and FSS, t h e r e q u e s t s f o r s p e c i f i c
o r b i t a l environmental c r i t e r i a w i l l become more numerous. A l a r g e percentage of t h e s e r e q u e s t s , however, w i l l be s a t i s f i e d by a n O r b i t a l
Environment C r i t e r i a Document t h a t i s being developed a s a supplement
t o NASA TM X-53798.
7.
Thermosphere Probe Program
A d e t a i l e d a n a l y s i s of s i x MSFC thermosphere probes launched
on January 24, 1967, has r e s u l t e d i n a s c i e n t i f i c paper t h a t w i l l b e subm i t t e d t o one of t h e p r o f e s s i o n a l j o u r n a l s f o r p u b l i c a t i o n .
This paper
�shot\rs t h e MSFC thermosphere probe measurements of N2 number d e n s i t y and
c a l c u l a t e d temperatures t o be i n e x c e l l e n t agreement w i t h o t h e r s i m i l a r
measurements. Atmospheric mass d e n s i t i e s t h a t a r e implied by t h e N2
measurements a r e i n good agreement w i t h t h e MSFC Modified J a ~ c h i aModel
Atmosphere, 1967 above 300 km a l t i t u d e and t h e i n f e r r e d 0 and O2 number
d e n s i t i e s a r e i n d i c a t e d t o be i n good agreement w i t h s e v e r a l mass spectrome t e r measurements of t h e s e q u a n t i t i e s . The paper t e n t a t i v e l y i l l u s t r a t e s
t h a t t h e ornegatron mass s p e c t r o m e t e r , which was flown on a l l of t h e MSFC
thermosphere probes, may be used t o o b t a i n atmospheric i n f o r m a t i o n i n as
much d e t a i l as can be o b t a i n e d from o t h e r mass s p e c t r o m e t e r s t h a t a l s o
measure 0 and O2 c o n c e n t r a t i o n s . Data r e d u c t i o n problems i n t h e O2 and
0 measurements, s u c h a s recombination and accommodation i n s i d e t h e gauge,
however, a r e n o t a p p l i c a b l e t o t h e O2 and 0 c o n c e n t r a t i o n s t h a t a r e c a l c u l a t e d from t h e N2 measurements.
Study e f f o r t - i n t h i s program i s c u r r e n t l y being d i r e c t e d t o
t h e e x t e n s i o n of t h e 20 thermosphere o b s e r v a t i o n s from 140 km down t o
90 km a l t i t u d e . This t a s k , which i s being accomplished u s i n g t h e o r e t i c a l
molecular d i s s o c i a t i o n and eddy d i f f u s i o n c o n s t r a i n t s , w i l l p r o v i d e
i n f o r m a t i o n concerning t h e v a r i a b i l i t y of t h e temperature and atmospheric
c o n s t i t u e n t s n e a r 90 km a l t i t u d e . This i n f o r m a t i o n w i l l be used t o e s t a b l i s h v a r i a b l e boundary c o n d i t i o n s a t 90 km f o r a dynamic model atmosphere
t h a t is being developed from s a t e l l i t e drag-determined d e n s i t y d a t a .
A second s c i e n t i f i c paper, which is i n d r a f t form, w i l l
p r e s e n t t h e a n a l y s i s of t h e two MSFC thermosphere probes launched i n
A p r i l 1967.
Two a d d i t i o n a l probes a r e planned f o r e a r l y 1969, and t h e
RFP f o r f o u r more has been s e n t o u t .
The a n a l y s i ~ ~ oa fl l of t h e MSFC and GSFC thermosphere probes,
i n c o n j u n c t i o n w i t h t h e a n a l y s i s of a l l a v a i l a b l e s a t e l l i t e d r a g - d e t e r mined d e n s i t y d a t a , w i l l provide i n f o r m a t i o n needed f o r t h e development
of a n improved upper atmosphere model t h a t w i l l n o t be l i m i t e d by t h e
c o n s t a n t boundary assumptions i n h e r e n t i n e x i s t i n g model atmospheres.
8.
Solar A c t i v i t y Studies
Lockheed M i s s i l e s and Space Company has computed t h e v a r i o u s
parameters which a r e d e s c r i p t i v e of t h e i n t e r a c t i o n of t h e p l a n e t s w i t h
t h e sun. These parameters a r e :
(1)
P o s i t i o n of t h e s u n r e l a t i v e t o t h e c e n t e r of mass
of t h e s o l a r system.
(2)
V e l o c i t y of t h e s u n r e l a t i v e t o t h e c e n t e r of mass.
�(3)
A c c e l e r a t i o n of t h e sun.
(4)
Angular momentum of t h e sun about t h e c e n t e r of mass.
(5)
Radius of c u r v a t u r e of t h e sun's path.
(6)
Rate of change of angular momentum.
(7)
Rate of change of a c c e l e r a t i o n ( j e r k ) .
These d a t a have been s e n t t o ~ o c k h e e d ' s Palo A l t o Research
F a c i l i t y f o r d e t a i l e d n o n l i n e a r c o r r e l a t i o n study t o determine t h e b e s t
sunspot p r e d i c t o r . R e s u l t s from t h i s c o n t r a c t work should be forthcoming
i n l a t e February.
MIT Experimental Astronomy Laboratory i s conducting a n
a n a l y t i c a l s t u d y t o d i s c i v e r which p l a n e t a r y i n f l u e n c e s a r e most import a n t i n determining s o l a r weather (sunspots and f l a r e s ) . Time g r a d i e n t
components of t h e t e n s o r r e p r e s e n t i n g t h e t o t a l g r a v i t y g r a d i e n t a t t h e
sun due t o t h e p l a n e t s should g i v e an i n s i g h t i n t o t h e underlying s o l a r
physics which cause sunspots and f l a r e s . P r o g r a m i n g t o o b t a i n t h e necessary data i s nearly finished.
Denver Research I n s t i t u t e i s conducting r e s e a r c h t o improve
long-range s o l a r a c t i v i t y p r e d i c t i o n s . The square of t h e v e r t i c a l t i d a l
f o r c e on t h e sun due t o t h e p l a n e t s i s being compared w i t h s o l a r proton
events t o determine whether o r not any c o r r e l a t i o n e x i s t s between t h e s e
parameters. Another e f f o r t under t h e c o n t r a c t i s t h e development of
techniques t o p r e d i c t sunspot numbers f o r periods of one t o two s o l a r
cycles.
The U n i v e r s i t y of Arkansas is a t t e m p t i n g t o develop mathem a t i c a l f u n c t i o n s t o f i t s o l a r cycles. Data from many sources t h a t
e s t i m a t e t h e c y c l e s back s e v e r a l hundred y e a r s have been t a b u l a t e d , and
w i l l be searched f o r hidden p e r i o d i c i t i e s .
A c o n t r a c t i s being negotiated w i t h t h e Solar A c t i v i t y Group
of the ESSA Space Disturbance Laboratory t o s e a r c h f o r p o s s i b l e means of
p r e d i c t i n g sunspot numbers throughout t h e s o l a r c y c l e , t o v e r i f y a l t e r n a t i v e f o r e c a s t s a g a i n s t independent o b s e r v a t i o n s , and t o s e a r c h f o r poss i b l e improved means of r e l a t i n g t h e s o l a r r a d i o f l u x t o t h e sunspot
number o r of p r e d i c t i n g t h e s o l a r r a d i o f l u x d i r e c t l y .
In-house e f f o r t s a r e aimed a t improving s o l a r cycle predict i o n s through t h e a p p l i c a t i o n of Fourier a n a l y s e s , power spectrum techniques, and band pass f i l t e r analyses.
�We p l a n t o sponsor a seminar on S o l a r A c t i v i t y P r e d i c t i o n i n
the s p r i n g of 1969. I n a d d i t i o n t o r e s e a r c h e r s working under MSFC cont r a c t , we hope t o have p a r t i c i p a t i o n by o t h e r l e a d i n g a u t h o r i t i e s i n t h i s
field.
VI.
ASTRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
Guidance Theory Branch
1.
Support Contract S t u d i e s
a.
Lunar Targeting Analysis Using QUOTA
Terminal conditions f o r the t a r g e t i n g problem have been
s e l e c t e d a s r a d i u s of c l o s e s t approach, s p e c i f i c energy, and azimuth a t
periselenum. The a s s o c i a t e d t r a n s v e r s a l i t y conditions have been developed
and incorporated i n t o t h e QUOTA program. Several t e s t s have been run,
and a s expected, t h e r e s u l t s i n d i c a t e d two problem a r e a s : t h e s e n s i t i v i t y a s s o c i a t e d w i t h t h e i s o l a t i o n of a n optimum s o l u t i o n , and t h e
accuracy of t h e two-body s o l u t i o n over t h e c o a s t a r c s . The problem
a r e a s a r e being i n v e s t i g a t e d .
b.
~ u a s i - o p t i m a lGuidance Study
Rendezvous s t u d i e s a r e now being conducted w i t h QUOTA.
Two d i f f e r e n t problems a r e being s t u d i e d :
(1) rendezvous w i t h a n S-IVB,
i n i t i a l time 151 seconds ( f i r s t burn s u b - o r b i t a l ) , and a t a r g e t v e h i c l e
i n a 225 n.m. o r b i t , and (2) rendezvous w i t h i n t e r c e p t o r and t a r g e t i n
c i r c u l a r o r b i t w i t h varying r e l a t i v e i n c l i n a t i o n s
.
c.
O r b i t Trim Systems E r r o r Analysis
D i f f i c u l t i e s a r e s till being encountered i n transforming t h e n a v i g a t i o n accuracy d a t a , generated by the Bissett-Berman program
a s a covariance m a t r i x i n l o c a l C a r t e s i a n coordinates, i n t o a covariance
m a t r i x i n o r b i t a l elements. An a n a l y t i c a l method of transforming t h e
l o c a l C a r t e s i a n coordinate covariance m a t r i x d i r e c t l y i n t o a n o r b i t a l
element covariance m a t r i x has been p a r t i a l l y developed. This a n a l y t i c a l
method , a f i r s t - o r d e r p e r t u r b a t i o n a n a l ys i s , assumes zero means.
d.
Optimal Guidance Study
Some progress has been made i n understanding t h e
behavior of t h e switching f u n c t i o n and how t h i s a f f e c t s t h e formulation
of m u l t i p l e l u n a r a r c o p t i m i z a t i o n t r a j e c t o r i e s . Also, a g e n e r a l t h r e e dimensional computer program f o r m u l t i p l e burn a r c t r a j e c t o r i e s w i t h
v a r i o u s terminal s u r f a c e s i s being assembled.
�2.
Contracts
a.
-
IBM
A p p l i c a t i o n of Numerical Methods t o Extend
C a p a b i l i t i e s f o r Optimal Rocket Guidance
During t h i s r e p o r t i n g p e r i o d , improvements t o t h e comp u t a t i o n of p a r t i a l d e r i v a t i v e t r a n s i t i o n m a t r i c e s have been i n c o r p o r a t e d
i n t o t h e computer program f o r determining optimal t h r u s t - c o a s t - t h r u s t
t r a j e c t o r i e s . The computer program i s s t i l l being checked o u t . A l s o ,
a n IBM t e c h n i c a l n o t e c o n t a i n i n g t h e d e r i v a t i o n of t h e improvements t o
t h e computation of t h e c o a s t a r c t r a n s i t i o n m a t r i c e s was published.
b.
Lockheed
-
Rendezvous Guidance
The method of f i r s t - o r d e r p e r t u r b a t i o n s i s being a p p l i e d
t o t h e powered f l i g h t phases of t h e rendezvous m i s s i o n which has now been
r e g u l a r i z e d a c c o r d i n g t o Levi-Civita.
D i g i t a l programming of t h e r e s u l t i n g c o n t r o l l a w s i s underway.
3.
In-House S t u d i e s
Work i s i n p r o g r e s s t o f i n d a COV s o l u t i o n t o an AAP type of
rendezvous miss i o n . An optimal burn-coas t - b u r n , w i t h a s h o r t c o a s t
( l e s s than 90 m i n u t e s ) , s o l u t i o n t o t h e problem has been o b t a i n e d .
However, s i n c e t h e s h o r t c o a s t time v i o l a t e s the r e s t a r t c a p a b i l i t i e s
of t h e S-IVB, a s e a r c h f o r a l o n g e r c o a s t s o l u t i o n i s b e i n g made. It
i s planned t o develop optimal rendezvous t r a j e c t o r i e s f o r t h e e n t i r e
launch window. The r e s u l t s of t h i s s t u d y w i l l be compared, i n terms of
payload and launch window d u r a t i o n , w i t h t h e p r e s e n t l y d e f i n e d AAP mission p r o f i l e s
.
,
A patched c o n i c s o l u t i o n of ~ a m b e r t ' s problem has been
numerically o b t a i n e d w i t h a technique i n v o l v i n g t h e use of p a r t i a l
d e r i v a t i v e t r a n s i t i o n m a t r i c e s . The motion of t h e probe i s approximated by two c l a s s i c a l two-body segments which a r e pieced t o g e t h e r .
This r e s u l t s i n a patched c o n i c s o l u t i o n f o r t h e l u n a r problem. Such
a s o l u t i o n makes p o s s i b l e a new approach t o t h e l u n a r t a r g e t i n g problem
A paper concerning optimal c o - a l t i t u d e rendezvous has been
prepared and i s b e i n g submitted f o r c o n s i d e r a t i o n a s a t e c h n i c a l n o t e i n
t h e ALClA j o u r n a l .
The c a p a b i l i t y t o t r a n s f e r o r rendezvous between a r b i t r a r i l y
o r i e n t e d e l l i p t i c o r b i t s has been added t o t h e CDC-3200 COV program. The
r e f e r e n c e c o o r d i n a t e s y s tem i s t h e same a s used by North American A v i a t i o n .
One t e s t case has been solved and a number of o t h e r s w i l l be attempted t o
compare w i t h some of NAA' s r e s u l t s using quas i-1i n e a r i z a t ion.
'
�B.
As trodynamics Branch
1.
Broken-Plane T r a j e c t o r i e s (Lockheed)
The f i r s t d r a f t of t h e u s e r ' s manual f o r t h e Lockheed
Broken-Plane Computer Program has been completed and i s now being
e d i t e d f o r p u b l i c a t i o n . Work was begun on t h e development of a comp l e t e l y g e n e r a l broken- lane program that w i l l e l i m i n a t e t h e r e s t r i c t i o n s on t h e e x i s t i n g program w i t h r e g a r d t o h e l i o c e n t r i c t r a n s f e r a n g l e .
2.
Miss i o n Design C h a r t s
A paper i s being prepared i l l u s t r a t i n g a n e f f e c t i v e means
of communicating a s t r o d y n a m i c a l l y based miss i o n a n a l y s i s m a t e r i a l between
t h e a s trodynamicis t and t h e s y s tems e n g i n e e r . The r e p o r t w i l l emphasize
b o t h t h e type of m a t e r i a l t o b e p r e s e n t e d and t h e method of i t s p r e s e n t a t ion.
3.
I n t e r p l a n e t a r y N-Body Programs
a.
Program Development (Lockheed)
Work was begun on t h e checkout of t h e N-Body I n t e r p l a n e t a r y T r a j e c t o r y Program o b t a i n e d from ~ o c k h e e d / ~ u n n y v a l e .The program i s
coded i n F o r t r a n I1 and FAP and t h e r e f o r e must be converted t o F o r t r a n I V
f o r u s e on t h e IBM 7094 corYlputer system. The program, which i s extremely
v e r s a t i l e , has e l e v e n d i f f e r e n t o p t i o n s .
b
.
I s o l a t i o n Routines (Nor t h r o p )
The f i n a l d r a f t of a summary r e p o r t on t h e i s o l a t i o n
s t u d i e s was completed. Work continued w i t h checkout of t h e computer
program which t e s t s i s o l a t i o n schemes.
c.
T a r g e t i n g S t u d i e s (Northrop)
S t u d i e s were made t o determine a n e x p o n e n t i a l v a l u e t o
c o r r e c t l y v a r y t h e displacement of a probe. A method that worked w e l l
t o c o r r e c t t h e e r r o r was t o change t h e a c c e l e r a t i o n a t a d e c r e a s i n g r a t e .
The r e s u l t a n t displacement showed a n improvement over two-body t h e o r y ,
a s w e l l a s i n t h e c o n s t a n t s t e p method, i n a l l t r a j e c t o r i e s considered
f o r p e r i o d s of l e s s than one hundred days of f l i g h t .
The "Average A c c e l e r a t i o n Vector" method was a l s o
i n v e s t i g a t e d . This method a l t e r s t h e two-body t r a j e c t o r y by t h e average
a c c e l e r a t i o n v e c t o r s of each p l a n e t . Each v e c t o r was used t o c a l c u l a t e
t h e displacement of t h e probe due t o t h e p a r t i c u l a r p l a n e t , and t h e s e
�displacements were added t o t h e Kepler s o l u t i o n t o o b t a i n more accuracy.
Tlle method i s very a c c u r a t e f o r reasonable periods of c o a s t .
4.
O r b i t a l Transfer (Lockheed)
Work was continued t o extend t h e c a p a b i l i t i e s of Lockheed's
Medium Accuracy O r b i t a l Transfer Program (MOAT) t o compute t h e h e l i o c e n t r i c p o s i t i o n and v e l o c i t y h i s t o r y of a n i n t e r p l a n e t a r y s p a c e c r a f t
a t equal time increments along t h e h e l i o c e n t r i c t r a j e c t o r y . The program
i s a l s o being modified t o c a l c u l a t e the communications angles and d i s tances a t equal time increments along t h e t r a j e c t o r y . Automatic p l o t
r o u t i n e s a r e being added t o t h e program t o g r a p h i c a l l y d i s p l a y t h e d a t a
a s a f u n c t i o n of time along t h e t r a j e c t o r y .
Swingby Miss i o n Analysis (Lockheed)
5.
F i n a l e d i t i n g of t h e "Mars Capture Miss ions v i a Venus
Swingby" r e p o r t has been completed, and copies of the f i n a l r e p o r t w i l l
be d e l i v e r e d t o R-AERO-GA w i t h i n t h e next week.
6.
O r b i t s i n Non-Central F i e l d s
Work continues i n a n e f f o r t t o f i n d a simple c h a r a c t e r i z a t i o n of those transforms which g i v e no cross products i n momenta when
t h e Hamiltonian of a given mechamical system i s r e w r i t t e n i n t h e new
coordinates
.
7.
Abort and A l t e r n a t e Missions (Boeing)
Phase I and Phase I1 of t h e study of f i r s t - s t a g e engineo u t problems, which began September 3 , have been completed. An i n t e r i m
r e p o r t covering t h e s e two phases was received November 11, 1968. The
purpose of Phase I was t o show t h e e f f e c t s of v e h i c l e and t r a j e c t o r y
changes on c r i t i c a l t r a j e c t o r y parameters f o r t h e AS-502 v e h i c l e . The
r e s u l t s were t h a t t h e c e n t e r engine c u t o f f (CECO) on a f i x e d time r a t h e r
than on p r o p e l l a n t d e p l e t i o n i s d e t r i m e n t a l t o engine o u t s t a g i n g cond i t i o n s , and t h e AS-502 v e h i c l e w i t h t h e updated c o n f i g u r a t i o n of modif i e d t i l t a r r e s t , outboard engine c a n t , and CECO a t 125 seconds would
s t i l l have a n engine-out s t a g i n g problem.
Phase I1 c o n s i s t e d of a d e t a i l e d e v a l u a t i o n of AS-504
s i n g l e engine-out c a p a b i l i t y . The b a s e l i n e v e h i c l e and t r a j e c t o r y
included t h e r e v i s e d t i l t a r r e s t , c a n t , and e a r l y CECO a t 135 seconds.
The r e s u l t s show t h a t i n i t s p r e s e n t c o n f i g u r a t i o n the AS-504 v e h i c l e
has an engine-out s t a g i n g problem using t h e AS-503 c h i - f r e e z e schedule.
This problem w i l l be examined more c l o s e l y and p o s s i b l y a r e v i s e d chif r e e z e schedule recommended through a p p r o p r i a t e channels.
�Phase I11 i s now almost complete and a s a r e s u l t w i l l recomm
mend (1) a s p e c i f i c f i x f o r t h e AS-504 v e h i c l e , and ( 2 ) a g e n e r a l engineo u t guidance method a p p l i c a b l e t o a l l v e h i c l e s . A f i n a l r e p o r t on t h i s
should be o u t around December 1, 1968.
8.
O c c u l t a t i o n S t u d i e s (Lockheed)
A r e p o r t p r e s e n t i n g t h e r e s u l t s of a p a r a m e t r i c a n a l y s i s of
t h e e f f e c t s of v a r i o u s s a t e l l i t e o r b i t parameters on t h e o c c u l t a t i o n
c h a r a c t e r i s t i c s of Mars o r b i t e r was d e l i v e r e d t o R-AERO-GA, "Mars O r b i t e r
O c c u l t a t i o n A n a l y s i s w i t h P a r a m e t r i c Data f o r t h e 1973 through 1979 Type I
Mars Capture M i s s i o n s , " by T. C. Davis, LMSC/HREC
A791860, October 1968,
C.
O p t i m i z a t i o n Theory Branch
1.
Parameter O p t i m i z a t i o n Study f o r ATM
Schedule Order E-64
-
Lockheed
-
The s o u r c e of t h e problem w i t h s t a b i l i t y of t h e l i n e a r i z e d
analog s i m u l a t i o n used i n t h e hybrid o p t i m i z a t i o n technique has been
i s o l a t e d ; i t i s due s o l e l y t o n o i s e and s c a l i n g problems a t a c r i t i c a l
p o i n t i n analog s i m u l a t i o n s . S e v e r a l d i f f e r e n t analog r e p r e s e n t a t i o n s
show cons i s t e n t r e s u l t s , w h i l e d i g i t a l s i m u l a t i o n s do n o t show any s t a b i l i t y problems. This problem has been d i s c u s s e d w i t h A s t r i o n i c s . A l o g i c
change t h a t A s t r i o n i c s has introduced i n t o t h e CMG command s i g n a l t o
smooth t h e s i g n a l appears l i k e l y t o c o r r e c t t h e s i m u l a t i o n problem a l s o .
This i s c u r r e n t l y being checked o u t . The d i g i t a l l o g i c has been checked
o u t , and o p e r a t i o n a l hybrid runs a r e expected when t h e analog problem i s
corrected.
2.
Launch Vehicle F l i g h t Control
a.
S a t u r n V/Apollo Load R e l i e f S t u d i e s
Schedule Order E-60
- Northrop
The b a s i c r i g i d a n a l y s i s has been completed. The load
r e l i e f c o n t r o l l e r developed through r i g i d body s t u d i e s i s being analyzed
on a high-speed analog s i m u l a t i o n which i n c l u d e s f l e x i b l e body e f f e c t s .
A s e t of 500 measured winds w i l l provide t h e d i s t u r b a n c e t o t h e system.
Supplemental i n v e s t i g a t i o n s continue on t h e u t i l i t y of
parameter
s e n s i t i v i t y technique t o d e s i g n a load r e l i e f cqnTomovicl s
t r o l l e r f o r the Saturn ~ I A p o l l o .
�b.
. S t a t i s t i c a l Wind Model
-
Hayes (NAS8-21444)
Objective: C o n s t r u c t i o n of a wind model f o r u s e i n
s t a t i s t i c a l a n a l y s i s of launch v e h i c l e performance.
A meeting w a s h e l d w i t h t h e c o n t r a c t o r on November 22
t o d i s c u s s t h e s t a t u s and f u t u r e d i r e c t i o n of t h e s t u d y . Data r e d u c t i o n
has r e q u i r e d more e f f o r t and expense t h a n was expected, and t h e c o n t r a c t o r has s t a t e d t h a t t h e scope of work cannot be completed w i t h i n t h e fund
a l l o c a t i o n u n l e s s some r e l i e f on t h e computation e f f o r t i s provided. No
a d d i t i o n a l funds a r e c u r r e n t l y a v a i l a b l e .
Attempts a r e being made t o reduce a l a r g e segment of
t h e d a t a on MSFC computers. I f s a t i s f a c t o r y arrangements cannot be made,
i t w i l l be n e c e s s a r y t o reduce t h e scope of work.
It does appear p o s s i b l e
t o reduce t h e scope of work i n such a manner a s t o r e t a i n s i g n i f i c a n c e of
t h e reduced f i n a l ( p a r t i a l ) r e s u l t s ; t h e a d d i t i o n a l work n e c e s s a r y t o
complete t h e o r i g i n a l scope of work could be completed inhouse u s i n g t h e
programs and techniques developed by t h e c o n t r a c t o r .
3.
Trajectory Optimization
-
Northrop (Schedule Order E-59)
F i n a l copies of t h e r e p o r t on n e c e s s a r y c o n d i t i o n s f o r
optimal c o n t r o l w i t h i n e q u a l i t y c o n s t r a i n t s on t h e time r a t e of change
of t h e c o n t r o l v a r i a b l e s have been r e c e i v e d and d i s t r i b u t e d . The d r a f t
copy of t h e r e p o r t on Runge-Kutta formulas f o r reducing t h e amount of
computation needed i n t h e s o l u t i o n of optimal t r a j e c t o r i e s has been
s t u d i e d and approved; f i n a l copies w i l l soon b e d e l i v e r e d . The cont r a c t o r i s i n v e s t i g a t i n g methods f o r o b t a i n i n g expans i o n s of Lagrange
m u l t i p l i e r s i n terms of a n impulsive s o l u t i o n and methods f o r "updating"
d e r i v a t i v e s of Lagrange m u l t i p l i e r s a t a g i v e n time w i t h r e s p e c t t o t h e
s t a t e v a r i a b l e s a t t h e same time.
4.
Minimax Control
-
General ~ y n a m i c s / ~ o n v a i(NAS8-21454)
r
Objective:
(1) t o extend t h e C-minimax t h e o r y t o determine
C-minimax performance i n t h e presence of incompletely s p e c i f i e d d i s t u r b a n c e s ; (2) t o determine i f a n a n a l y t i c s o l u t i o n e x i s t s f o r C-minimax performance f o r l i n e a r dynamical s y s tems w i t h bounded c o n t r o l ; and (3) t o
i n v e s t i g a t e t h e computational problems d i s c o v e r e d t o e x i s t w i t h t h e c u r r e n t computational a l g o r i t h m .
�The c o n t r a c t o r has continued t o s e a r c h f o r computationally
a t t r a c t i v e methods of computing C-minimax c o n t r o l s f o r h i g h o r d e r systems.
Methods a d d i t i o n a l t o t h o s e c i t e d p r e v i o u s l y have been o b t a i n e d , b u t
each seems t o have i t s own computational d i s a d v a n t a g e . I n e s s e n c e , a
p l e t h o r a of methods have been o b t a i n e d which y i e l d s t h e optimal c o n t r o l
f o r g i v e n i n i t i a l c o n d i t i o n s , a l b e i t a t some computational expense.
None of t h e methods y i e l d i n s i g h t i n t o t h e g e n e r a l p r o p e r t i e s of t h e
s o l u t i o n , however, a s t h e c u r r e n t computational a l g o r i t h m does f o r
second o r d e r systems. S t u d i e s of l i n e a r systems w i l l c o n t i n u e , and
some cons i d e r a t i o n w i l l be g i v e n t o approximating problems y i e l d i n g
general solutions.
5.
Lunar Roving Vehicle
I n v e s t i g a t i o n s have been i n i t i a t e d t o determine i f t h e r e
e x i s t any s e r i o u s m o b i l i t y or n a v i g a t i o n problems f o r t h e c u r r e n t l y
planned l u n a r r o v i n g v e h i c l e , which i s t o b e c o n t r o l l e d from e a r t h i n
t h e unmanned mode of o p e r a t i o n . E f f o r t s t o d a t e have c o n s i s t e d of
o b t a i n i n g and s tudying background m a t e r i a l on t h e l u n a r s u r f a c e environment and on t h e c o n t r o l and n a v i g a t i o n s t u d i e s made f o r p r e v i o u s l y proposed l u n a r r a v i n g v e h i c l e s .
Progress has been impeded by t h e long time
n e c e s s a r y t o o b t a i n some of t h e r e l e v a n t documents.
�V I I . DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Multi-Projects
Dynamics and Control
1.
Vehicle Response t o D e t a i l e d Winds (Ref. ~ e c / ~ a n1968
.
P* 49)
The S a t u r n V v e h i c l e has been s i m u l a t e d b o t h a s a r i g i d
and a s a n e l a s t i c v e h i c l e f o r f l i g h t through 975 d e t a i l e d Jimsphere
winds, b o t h s c a l a r and d i r e c t i o n a l . R e s u l t s i n d i c a t e d t h a t f l y i n g a
r i g i d v e h i c l e through t h e f i l e t e r e d winds (Rawinsonde e q u i v a l e n t ) and
adding t h e r e s p o n s e obtained from a g e n e r a l i z e d harmonic a n a l y s i s
approach, u s i n g a spectrum f o r t h e t u r b u l e n c e , c l o s e l y d u p l i c a t e s t h e
r e s u l t s o b t a i n e d using t h e d e t a i l e d p r o f i l e s . I f t h e s e t e n t a t i v e conc l u s i o n s h o l d , a b e t t e r a n a l y s i s approach could b e developed s i n c e t h e
r i g i d v e h i c l e s i m u l a t i o n w i t h f i l t e r e d winds can b e e f f i c i e n t l y s o l v e d
on computers. R-AERO-DD
2.
Six-Dimens i o n a l E l a s t i c Body Hybrid S i m u l a t i o n (New)
A s ix-dimensional e l a s t i c body s i m u l a t i o n has been g i v e n
t o t h e Computation Laboratory f o r p r o g r a m i n g on t h e hybrid computer.
The approach i s t o a p p l y t h e same technique as used on t h e h i g h speed
a n a l o g , u s i n g many winds, t o a 6-D s i m u l a t i o n . The h i g h speed simulaComputation Laboratory people b e l i e v e t h e y can run a t o t a l
t i o n i s 2-D.
t r a j e c t o r y w i t h a r e a l wind i n 1/100 of r e a l time. S i n c e a l l s t a t i s t i c s
can be handled i n t h e d i g i t a l p o s i t i o n of t h e computer, o n l y one pass
w i l l be needed through t h e wind ensemble t o o b t a i n a l l v e h i c l e responses
i n a s t a t i s t i c a l manner. R-AERO-DD
3.
Prelaunch Wind Monitoring (Ref. F e b . / ~ a r c h 1968, p. 3 7 )
The a t t e m p t t o develop an approach t o p r e d i c t , T hours
b e f o r e launch, t h e v e h i c l e response t o expected winds a t launch is prog r e s s i n g . The wind s t a t i s t i c s have been obtained from R-AERO-Y, and
b a s i c computer programs w i t h which t o u s e t h e wind s t a t i s t i c s have been
w r i t t e n . The s t a t i c a e r o e l a s t i c p o r t i o n has been checked o u t , a l o n g
w i t h t h e b a s i c v e h i c l e dynamics and c o n t r o l , i n c l u d i n g t r a j e c t o r y . The
e v a l u a t i o n of t h e s e n s i t i v i t y of t h e v e h i c l e response t o t h e changing
wind c h a r a c t e r i s t i c s has begun. D D D / M ~t i~ n
�I).
SaturnV
1.
Dynamics and Control
~ o n g i t u d i n a l l ~ a t e r aCoupling
l
(Ref. Aug./Sept. 1968, p. 35):
The l a t e r a l / l o n g i t u d i n a l coupling i n v e s t i g a t i o n of t h e 503 v e h i c l e has
been completed w i t h no evfdence of a problem. AS-504 i s being analyzed
by Boeing under a new t a s k f o r b o t h s t a b i l i t y and response. A paper on
t h e AS-502 r e s u l t s , t o be p r e s e n t e d a t t h e AIAA meeting i n J a n u a r y , w i l l
b e completed w i t h i n 2 weeks. A f i n a l r e p o r t of a l l inhouse work should
be completed i n December. R-AERO-DD
2.
P r o j e c t Information A p p l i c a b l e t o Many Vehicles
D i r e c t Ascent Lunar Launch Window Study (Ref. March 1966,
p. 35): Performed a t a low l e v e l of e f f o r t , a n a n a l y s i s of t h e d i r e c t a s c e n t l u n a r launch window has been completed. This a n a l y s i s d e f i n e d
t h e payload and azimuth v a r i a t i o n s a s s o c i a t e d w i t h a d i r e c t - a s c e n t launch
p r o f i l e t o e n e r g i e s corresponding t o f l i g h t times of 62, 6 7 , and 7 2 hours.
A c o n s t r a i n t imposed on t h e f l i g h t p r o f i l e w a s t h a t the minimum d i p a l t i tude d u r i n g S-IVB burn be g r e a t e r than o r e q u a l t o 80 km. Coast times
between t h e S - I 1 and t h e S-IVB s t a g e s were i n v e s t i g a t e d a s a method of
i n c r e a s i n g t h e launch window d u r a t i o n . For e a r l y launches t h i s i s
a p p r o p r i a t e , b u t i s n o t a p p l i c a b l e t o l a t e launches.
(R-AERO-DAP/NSL)
3.
P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles
a.
Dynamics Data f o r AS-503 Third F l i g h t S t a g e (Mission C")
~ p r i l / ~ a1968,
y
p. 38 and August/September 1968, p. 37
A v i b r a t i o n a n a l y s i s which r e f l e c t s t h e payload change
has been made of t h e t h i r d f l i g h t s t a g e S a t u r n V/AS-503 (Mission C' w i t h
LES a t t a c h e d ) . A document which c o n t a i n s t h e dynamic d a t a f o r AS-503
S-IVB f l i g h t s t a g e (Mission c ' ) has been prepared f o r b o t h t h e manned
t r a n s l u n a r miss i o n and t h e e a r t h o r b i t CSM o p e r a t i o n s w i t h command r e s t a r t
m i s s i o n . This document was d i s t r i b u t e d under cover memorandum R-AERODD-138-68.
R-AERO-DDS/BO~~~~
b.
On-Pad Dynamics C h a r a c t e r i s t i c s f o r AS-504 (New)
An on-pad v i b r a t i o n a n a l y s i s has been made of AS-504
f o r s e v e r a l d i f f e r e n t f u e l i n g c o n d i t i o n s . A payload of 100,000 l b s was
assumed f o r t h e a n a l y s i s . These d a t a a r e soon t o be d i s t r i b u t e d a s
e n c l o s u r e s t o memorandum R-AERO-DD-141-68.
R-AERO-DDS
�C.
S a t u r n Apollo A p p l i c a t i o n s Program
1.
Cluster
a.
Mission P r o f i l e
(1)
AAP-1, 2, 3A, 3, and 4 F l i g h t P r o f i l e and Launch
Window A n a l y s i s (Ref. Aug./Sept. 1968, p. 38 and 41)
The documentation of t h e p r e l i m i n a r y f l i g h t p r o f i l e
and launch window a n a l y s i s f o r t h e AAP C l u s t e r missions t o a n AAP-2
b r b i t a l a l t i t u d e of 220 NM has been completed.
The AAP c l u s t e r m i s s i o n p r e l i m i n a r y £1 i g h t p r o f i l e
and launch window a n a l y s i s i s being r e p e a t e d t o r e f l e c t r e c e n t a n d / o r
a n t i c i p a t e d b a s e l i n e changes. Under t h e new p l a n , t h e OWS ( U P - 2 ) w i l l
i n s e r t , a f t e r p a s s i v a t i o n , near p e r i g e e of a 185 x 210 NM o r b i t . The
o r b i t a l i n c l i n a t i o n of t h e OWS w i l l be approximately 35 d e g r e e s , chosen
s u c h that t h e AAP-2 launch w i l l be optimum (maximum payload) and a n AAP-1
optimum in-phase s o u t h e r l y launch o p p o r t u n i t y w i l l be a v a i l a b l e approxim a t e l y 2 112 s t a g e s t o o r b i t . On AAP-1, t h e CSM w i l l i n s e r t i n t o a n
8 1 x 120 NM o r b i t and c i r c u l a r i z e a t apogee. The c o e l l i p t i c rendezvous
method w i l l t h e n be followed, w i t h t h e h e i g h t ad j u s t maneuver being performed s o a s t o r a i s e apogee t o 10 NM below t h e p e r i g e e of t h e workshop
o r b i t . This p r o f i l e w i l l provide t h e maximum amount of phasing v a r i a t i o n .
Af t e r rendezvous i s complete, t h e CSM w i l l c i r c u l a r i z e t h e OWS/CSM c l u s t e r
i n t o a 210 x 210 NM o r b i t . Then AAP-3A and AAP-3 w i l l be launched s o u t h e r l y
approximately 90 and 180 days a f t e r t h e AAP-1 launch, r e s p e c t i v e l y . AAP-4
i s t o be launched s e v e r a l days a f t e r AAP-3 and w i l l perform a n unmanned
rendezvous w i t h t h e c l u s t e r
.
The s i m u l a t i o n of t h e AAP c l u s t e r m i s s i o n has proceeded t o t h e c i r c u l a r i z a t i o n of t h e OWS/CSM (AAP-2/AAP-1) c l u s t e r . The
OWS o r b i t a l i n c l i n a t i o n s a t i s f y i n g t h e U P - 1 and 2 optimum launch r e q u i r e ments i s 35.747 d e g r e e s . The OWS w i l l be launched a t 17:OO @lT on day
z e r o and AAP-1 w i l l be launched a t 21:24 GMT on day 2. R-AERO-DAO/DAP/
Nor t h r o p
(2)
Mechanization of t h e C l u s t e r Mission P r o f i l e and
Launch Window Analysis (Ref. Aug./Sept. 1968, p. 40)
The l o g i c flow f o r t h e d r i v e r o r e x e c u t i v e program
n e c e s s a r y f o r t h i s mechanization has been developed. The O r b i t a l P r e d i c t i o n Program, used f o r c o a s t s and launch o p p o r t u n i t y c a l c u l a t i o n s , and
t h e Quick-Look Program, used f o r p r e l iminary m i s s i o n s imulat i o n s , have
been converted and l i n k e d on t h e UNIVAC 1108 computer. P r e s e n t l y , t h e
CDC 3200 v e r s i o n s o f t h e s e programs a r e being used t o develop and check
�o u t t h e m o d i f i c a t i o n s n e c e s s a r y f o r t h e s e programs t o perform t h e operat i o n s which have p r e v i o u s l y been done by hand. Also, they a r e being used
t o develop some of t h e l o g i c which w i l l l a t e r be placed i n t h e d r i v e r .
R-AERO-DAO/NO~~~~O~
(3)
LM/ATM Unmanned Rendezvous (Ref. J u n e / ~ u l y1968,
P. 41)
The p r a c t i c a l i t y of using t h e workshop a t t i t u d e
c o n t r o l system (WACS) a s a k i c k s t a g e t o do a p o r t i o n of t h e maneuvers
i n t h e AAP-4 rendezvous p r o f i l e i s now under i n v e s t i g a t i o n .
It i s
assumed t h a t t h e S-IVB s t a g e i n s e r t s i n t o a n o r b i t w i t h a p e r i g e e somewhat below t h e f i n a l d e s i r e d o r b i t and apogee above i t . The ,WACS (modif i e d w i t h a f t f i r i n g t h r u s t e r s ) performs a c i r c u l a r i z a t i o n maneuver a f t e r
p a s s i n g through apogee t h e second time. By v a r y i n g t h e r a d i u s of apogee
(and p e r i o d ) a launch window can be o b t a i n e d , and i t i s p o s s i b l e t o comp e n s a t e f o r t h e down-range, i n s e r t i o n d i s p e r s i o n s . Trade-offs a r e being
determined between i n s e r t i o n a l t i t u d e , payload, WACS p r o p e l l a n t r e q u i r e d ,
LM RCS p r o p e l l a n t r e q u i r e d , launch window widths and number of phasing
o r b i t s . R-AERO-DAO
( 4 ) Design Reference Miss i o n Document (DRMD) AAP-112
(Ref. April/May 1968, p. 42)
Volume V of t h e DRMD i s being r e v i s e d . Revision A
i s f o r t h e purpose of i n c o r p o r a t i n g changes t o t h e m i s s i o n r e s u l t i n g from
change 1 t o Program D i r e c t i v e 3C, F l i g h t Mission D i r e c t i v e f o r AAP-112,
dated May 1 4 , 1968, and t h e F i n a l Report of t h e AAO C l u s t e r AD Hoc A t t i tude Control Working Group, dated May 24, 1968. Revision B i s issued a s
Appendix A t o i n c o r p o r a t e p r e l i m i n a r y r e s o u r c e usage d a t a . Revision A
has been i s s u e d under cover memorandum R-AERO-DAM-36-68 and Revis i o n B
under cover memorandum R-AERO-DAM-40- 68. R-AERO-DAM/M~~t i n
(5)
AAP Experiments Data Bank (Ref. April/May 1968,
P. 42)
( a ) Two more i s s u e s of t h e d a t a bank have been
p u b l i s h e d . These i s s u e s (October 1968, and November 1968) i n c o r p o r a t e
changes t o v a r i o u s experiments which have a d i r e c t e f f e c t on t h e payload
f o r t h e AAP.
(b) The AAP experiment d a t a bank i s being r e v i s e d
t o i n c o r p o r a t e v a r i o u s s u g g e s t i o n s and comments t o make i t more meaningf u l . C o o r d i n a t i o n between -DAM, I-S/AA, and M a r t i d M a r i e t t a C o r p o r a t i o n
i s b e i n g maintained t o i n s u r e that t h e r e v i s e d d a t a bank i s u s e f u l f o r
a l l purposes. R-AERO- artin in
�(6)
Experiment C o m p a t i b i l i t y (New)
R-AERO-DAM, i n c o n j u n c t i o n w i t h R-AERO-P, I-S/AA,
and ~ a r t i n / M a r i tet a C o r p o r a t i o n , i s answering a n a c t i o n item s e n t from
Luskin r e l a t i v e t o Experiment/Mission C o m p a t i b i l i t y A n a l y s i s . The scope
of t h e endeavor is f o r a more comprehensive assessment t o i n c l u d e e v a l u a t i o n of s e v e r a l a l t e r n a t i v e experiment combinations. R-AERO-DAM
(7)
AAP Hardware U t i l i z a t i o n (New)
E f f o r t s a r e being made t o complete a flow c h a r t
showing hardware u t i l i z a t i o n i n t h e AAP f o r contingency and backup miss i o n planning.
I n a d d i t i o n , a second phase ( t h a t of p r o b a b i l i t y d e t e r mination) is b e i n g worked, a l t h o u g h t h i s phase i s p r o g r e s s i n g s l o w l y
because some of t h e i n f o r m a t i o n i s n o t a v a i l a b l e .
(8)
.
AAP LM/ATM Unmanned Rendezvous (Ref. Aug /Sep t .
1968, p. 44)
The t a s k of e s t a b l i s h i n g f e a s i b i l i t y of a n S-IVB/
LM-ATM rendezvous w i t h t h e o r b i t a l assembly u s i n g t h e S-IVB mainstage
p r o p u l s i o n s y s tem i n a r e i g n i t i o n mode and t h e a u x i l i a r y p r o p u l s i o n
s y s tem l o n g i t u d i n a l type t h r u s t e r c o n t i n u e s . The a r e a s under s tudy a r e
(1) second S-IVB 5-2 t h r u s t i n g i n t o a n i n t e r m e d i a t e w a i t i n g o r b i t , (2)
h e i g h t a d j u s t m e n t maneuver f o r proper phase r e l a t i o n s h i p w i t h t h e t a r g e t ,
(3) p l a n e change maneuver a t t h e l i n e of nodes between t h e S-IVB/LM-ATM
and t h e workshop o r b i t , ( 4 ) t k r m i n a l rendezvous t r a n s f e r maneuvers,
(5) midcours e c o r r e c t i o n maneuver, and (6) t h e f i n a l v e l o c i t y matching
maneuver a t t h e s t a t i o n k e e p i n g pos i t i o n . The a n a l y s i s i n d i c a t e d that
a l l maneuvers can be performed w i t h t h e low a c c e l e r a t i o n p r o f i l e provided
c a r e i s t a k e n t o e s t a b l i s h compatible geometry s o t h a t d e l t a v e l o c i t y
requirements a r e cons is t e n t w i t h t h e a v a i l a b l e t h r u s t l e v e l . R-AERO-DGG/
Nor t h r o p
b.
Guidance
T r a j e c t o r y Shaping Payload Improvements (Ref. Aug./Sept.
1968, p. 42): The payload t r a d e - o f f s w i t h S-IB v e h i c l e l o a d s u s i n g t h e
S-IBIS-IVB/LM-ATM c o n f i g u r a t i o n has been e s t a b l i s h e d f o r two d i f f e r e n t
o r b i t s u s i n g S-IB t r a j e c t o r y shaping t e c h n i q u e s . Approximately 450 pounds
of payload can b e gained w i t h a n i n c r e a s e i n v e h i c l e l o a d s of 3 p e r c e n t
and 580 pounds f o r 5 p e r c e n t f o r a n o r b i t of 80 x 260 n a u t i c a l m i l e s .
Approximately 450 pounds payload i n c r e a s e f o r 3 p e r c e n t l o a d s i n c r e a s e
and 560 pounds payload i n c r e a s e f o r 5 p e r c e n t i n c r e a s e i n v e h i c l e loads
can be achieved f o r a d i r e c t i n s e r t i o n i n t o a 220 n a u t i c a l m i l e c i r c u l a r
R-AERO-DGG
orbi t
.
�c.
Dynamics and Control
(1)
ATM S t a b i l i t y and P o i n t i n g S t u d i e s (Ref. Aug./Sept.
1968, p. 43)
Work being conducted f o r t h e ATM m i s s i o n , C l u s t e r I ,
i s divided i n t o f i v e b a s i c areas:
(1) s t a b i l i t y of e l a s t i c body c l u s t e r
and bending f i l t e r d e t e r m i n a t i o n , (2) p o i n t i n g a c c u r a c i e s of t h e ATM t o
d i s t u r b a n c e s such a s man motion, (3) momentum management, (4) s t e e r i n g
laws, and (5) program development. This work i s being done in-house,
w i t h t h e m i s s i o n s u p p o r t c o n t r a c t o r s , and i n t e g r a t i o n c o n t r a c t o r and i s
p r o g r e s s i n g a s follows:
-
A n a l y s i s has been made
(a) S t a b i l i t y Analysis
of t h e g e n e r a l s t a b i l i t y c h a r a c t e r i s t i c s of t h e c l u s t e r u s i n g CMG'S by
1i n e a r i z i n g t h e d e s c r i b i n g d i f f e r e n t i a l e q u a t i o n s . I f t h e s y s tem were
i d e a l (no l a g s ) , no bending f i l t e r s would be needed s i n c e c o n t r o l s e n s o r s
and t o r q u e s a r e l o c a t e d a t t h e same v e h i c l e s t a t i o n ; however, t h e i n h e r e n t
l a g s i n t h e s y s tem r e q u i r e networks. These networks a r e f a i r l y s i m p l e ,
u s u a l l y a f o u r t h o r d e r . S t u d i e s thus f a r i n d i c a t e a n a c c e p t a b l e s t a b i l i t y margin u s i n g t h e s e networks, w i t h v e r y l i t t l e d e t e r i o r a t i o n of t h e
pointing accuracy. R - A E R O - D D D I M ~ ~ ~ ~ ~
To b e t t e r a s s e s s coupling and n o n l i n e a r i t i e s
e l i m i n a t e d through t h e l i n e a r i z a t i o n assumed i n t h e above s t u d i e s , t h e
t o t a l 3-D system of e q u a t i o n s has been formulated, expanded a b o u t t h e
s i n g u l a r p o i n t s (CMG gimbal a n g l e s ) , and t h e n l i n e a r i z e d a b o u t t h e s e
p o i n t s f o r s t a b i l i t y . This e f f o r t i s i n f i n a l check-out on t h e computer;
r e s u l t s a r e expected soon. ~ - A E R 0 - ~ ~ ~ / N o r t h r o p
-
(b) P o i n t i n g Accuracy
The p o i n t i n g a c c u r a c y
f o r t h e ATM has been approached i n two ways: o b t a i n i n g t h e response of
the t e l e s c o p e and v e r n i e r c o n t r o l system by d r i v i n g t h e t e l e s c o p e base
a t t h e maximum expected bending mode amplitude f o r each bending mode
frequency; and o b t a i n i n g t h e response of t h e t o t a l e l a s t i c system t o
v a r i o u s man motions and d i s t u r b a n c e i n p u t s . R e s u l t s of t h e s e a n a l y s e s
i n d i c a t e t h a t t h e p o i n t i n g a c c u r a c y of t h e s y s tem can be met f o r a l l
c a s e s s t u d i e d which included i n i t i a l a t t i t u d e e r r o r s of 0.02" on each
a x i s . Some 25 d i f f e r e n t gimbal a n g l e o r i e n t a t i o n s were i n v e s t i g a t e d
on t h e hybrid computer. R - ~ ~ ~ ~ - D ~ / ~ a r t i n / N o r t h r o p
-
( c ) Momentum Management
S t u d i e s have been made
comparing v a r i o u s s t e e r ing laws and d i s t r i b u t i o n laws t o determine cont r o l l a b i l i t y of t h e c l u s t e r . This was done by observing t h e system
r e s p o n s e t o a sequence of 50 n-m torque commands, u s i n g CMG1s and Che
4-vector c o n t r o l w i t h no gimbal c o n t r o l , ~ e n n e l ' s r o t a t i o n and d i s t r i b u t i o n , l i n e a r gimbal a n g l e feedback, and q u a d r a t i c feedback. The H-vector
�was changed t o H-vector c o n t r o l and t h e s t u d y r e p e a t e d f o r lLnear gimbal
feedback. I n i t i a l i n d i c a t i o n s show t h e l i n e a r o r q u a d r a t i c feedback
s u p e r i o r t o t h e i s o g o n a l d i s t r i b u t i o n l a w i n t h e c a p a b i l i t y of each
s y s tem f o r p r e v e n t i n g a n t i p a r a l 1 , e li s m . R-AERO-DD/Nor t h r o p
-
The work done u s i n g a CMG con(d) S t e e r i n g Laws
t r o l l a w based on t h e concept t h a t t h e momentum v e c t o r s always form a
maximum volume i s being documented. Although t h e law i s c o n c e p t u a l l y
v e r y s i m p l e , t h e a c t u a l p h y s i c a l implementation of t h e law a p p e a r s t o
b e more complex t h a n t h e c o n t r o l laws c u r r e n t l y i n o p e r a t i o n . R-AERO-DDD
-
Development of a s e t of
( e ) Program Development
d i g i t a l computer modules f o r t h e v a r i o u s phases of C l u s t e r I m i s s i o n i s
c o n t i n u i n g . Modules have been programmed f o r a l l c o n t r o l systems (LNG,
v e r n i e r , r e a c t i o n j e t ) , r i g i d body dynamics, o r b i t dynamics, and g r a v i t y
g r a d i e n t . Four of t h e modules, r i g i d body dynamics, o r b i t dynamics
CMG'S, and g r a v i t y g r a d i e n t have been r u n t o g e t h e r on t h e 1108 computer
and good r e s u l t s o b t a i n e d . The major d i f f i c u l t y thus f a r i s computer r u n
time. Unless a major breakthrough is obtained i n speed on d i g i t a l comp u t e r s , most o r b i t a l dynamic s t u d i e s w i l l have t o be made on h y b r i d o r
a n a l o g computer. ~ ~ / ~ o r t h r o p .
(2)
P a s s i v e A t t i t u d e C o n t r o l (Ref. Aug./Sept.
P. 4 5 )
1968,
The f l e x i b i l i t y of t h e g e n e r a l purpose a t t i t u d e
c o n t r o l program (ACP) f o r l a r g e e a r t h o r b i t i n g s p a c e c r a f t has been subs t a n t i a l l y enhanced by adding a s e l f - c o n t a i n e d s u b r o u t i n e f o r d e n s i t y
computation based on ~ a c c h i a ' s d e n s i t y model. The program has been
s u c c e s s f u l l y checked o u t .
A computer program e s p e c i a l l y e f f i c i e n t f o r s imul a t i n g p a s s i v e s a t e l l i t e motion over long time p e r i o d s s u c h a s 10 o r
more o r b i t s has a l s o been s u c c e s s f u l l y checked o u t . The i n t e g r a t i o n
r o u t i n e s a r e b e i n g r e f i n e d f o r f u r t h e r r e d u c t i o n s i n t h e computing time.
The program i s b e i n g documented.
E x c e l l e n t r e s u l t s have been o b t a i n e d i n f i r s t comp u t e r s i m u l a t i o n s where t h e s o l a r panels of a p a s s i v e s a t e l l i t e a r e used
a s aerodynamic dampers. T o r s i o n a l s p r i n g s and dampers provide t h e necess a r y phasing between s p a c e c r a f t and panel o s c i l l a t i o n s f o r maximum dampi n g . An e f f o r t i s underway t o reduce t h e computing time of t h e d i g i t a l
s imula t i o n program. R-AERO-DCA
�d.
P r o j e c t Information Applicable t o I n d i v i d u a l Vehicles
AAP-2 Rigid Body Control Responses *(Ref. Aug./sept.
1968, p. 43)
Rigid body c o n t r o l responses f o r t h e AAP-2 v e h i c l e have
been completed f o r two time p o i n t s (max q a , max q ) and published i n
R-AERO-DCC-11-68.
Because of t h e l a r g e responses and near l o s s of cont r o l f o r t h e RSS c a s e when e x c i t e d by a 95 p e r c e n t i l e n o n d i r e c t i o n a l
d e s i g n wind, time responses f o r t h e 90 p e r c e n t i l e n o n d i r e c t i o n a l s y n t h e t i c
wind were a l s o included. Responses f o r t h e Mach 1 time p o i n t and j u s t
b e f o r e inboard engine c u t o f f w i l l be published l a t e r . The l a r g e responses
o b t a i n e d f o r t h i s v e h i c l e r e s u l t from a forward s h i f t i n t h e c e n t e r of
p r e s s u r e and a n i n c r e a s e i n t h e normal f o r c e c o e f f i c i e n t i n t h e c r i t i c a l
h i g h dynamic p r e s s u r e r e g i o n caused by t h e con£ i g u r a t i o n (AS-203 nose
cone w i t h c y l i n d r i c a l e x t e n s i o n , and s o l a r panel c o n d u i t s ) . R-AERO-DC
2.
OWS
a.
OWS Control Impulse S t u d i e s (Aug./Sept.
1968, p. 4 4 , 45)
The p r e s e n t m i s s i o n t i m e l i n e f o r AAP-1-2, 3A, 3 - 4 r e q u i r e s
t h e OWS c o n t r o l system t o handle t h e c l u s t e r c o n t r o l f o r s e v e r a l types of
o r b i t s , v e h i c l e o r i e n t a t i o n , and maneuvers. S t u d i e s i n each of t h e s e
a r e a s a r e being conducted a s w e l l a s s e n s i t i v i t y of impulse requirement
These s t u d y a r e a s a r e "tugboat"
t o v a r i o u s s y s tem parameter v a r i a t i o n s
s t a b i l i t y c h a r a c t e r i s t i c s , s e n s i t i v i t y t o mass parameters, s e n s i t i v i t y
t o c o n t r o l systems deadbands, and e f f e c t of o r b i t i n c l i n a t i o n . A t t h e
p r e s e n t time, t h e OWS impulse c a p a b i l i t y meets t h e r e q u i r e m e n t s . R-AERO-DDD
.
-
-
"Tugboat" c o n f i g u r a t i o n
Computer runs have
(1) OWS
i n d i c a t e d t h a t t h e second bending- mode of t h e " tugboat"
configuration i s
unstable.
S i n c e t h i s was unexpected, a c l o s e r checkout of t h e e q u a t i o n s
and program was i n i t i a t e d . I t has been decided t h a t a TR-48 analog
s i m u l a t i o n might be more f l e x i b l e than a l i n e a r i z e d s t a b i l i t y a n a l y s i s
f o r parameter s t u d i e s . This analog s i m u l a t i o n i s now being implemented.
R-AERO-DDD
-
( 2 ) OWS
Mass Parameter S e n s i t i v i t y - R-P&VE has
r e q u e s t e d t h a t a l i s t i n g be made of mass parameters which a f f e c t WACS
p r o p e l l a n t b u d g e t s . Computer runs a r e now being made t o show t h e e f f e c t
of i n e r t i a l and c . g . v a r i a t i o n s upon t h e WACS impulse per o r b i t . These
r e s u l t s w i l l be published by memo w i t h i n t h e n e x t r e p o r t i n g p e r i o d . This
i n f o r m a t i o n i s needed by P&VE t o h e l p them p l a n a b e t t e r c o n t r o l of
important mass c h a r a c t e r i s t i c s . R-AERO-DDD
�(3) OWS Control Impulse S e n s i t i v i t y t o Control System
An OWS c o n t r o l a t t i t u d e parameter s t u d y has been made (R-AERODeadband
DDD-137-68 )
The o p e r a t i o n a l mode of the OWS i s X-POP (x-axis perpendicu l a r t o o r b i t a l p l a n e ) . From g r a p h s , we can determine t h e impulse per
o r b i t f o r v a r i o u s combinations of deadband, average d e n s i t i e s , and deviat i o n s from X-POP.
R-AERO-DDD
-
( 4 ) E f f e c t of 35" O r b i t I n c l i n a t i o n on Impulse RequireA c l u s t e r contingency s t u d y f o r t h e OWS u s i n g a 35-degree
ments (New)
i n c l i n a t i o n w i l l be completed b e f o r e t h e end of t h e month. I n t h e e v e n t
of a m i s s i o n a b o r t , t h e OWS w i l l decay i n o r b i t , and a t t h e s t a r t of
a n o t h e r m i s s i o n t h e CSM w i l l b o o s t t h e OWS i n t o a h i g h e r o r b i t . Circul a r and e l l i p t i c a l o r b i t s a r e considered. The impulse per o r b i t f o r the
c i r c u l a r o r b i t s can be obtained from graphs i n R-AERO-DDD-137-68.
R-AERO-DDD
-
b.
A c t i v e Control (Ref. Aug./Sept.
1968, p. 44)
X-POP-type missions a r e being simulated f o r t h e OWS/ATM
c l u s t e r , where t h e e f f e c t s of time l a g s on f u e l consumption of t h e React i o n C o n t r o l Sys tem a r e under s t u d y . The o r b i t considered i s a 230 n.mi.
c i r c u l a r o r b i t . The s t u d y of t h e e f f e c t s of i n t e g r a t i o n s t e p s i z e on
t h e a c c u r a c y of t h e computed f u e l e x p e n d i t u r e s r e q u i r e s some a d d i t i o n a l
work. A program t o s i m u l a t e g r a v i t y - g r a d i e n t momentum dumping and a
program f o r a c c u r a t e e v a l u a t i o n and comparison of v a r i o u s CMG momentum
d i s t r i b u t i o n techniques a r e being checked o u t . R-AERO-DC
3.
ATM
- Mission
Profile
Vis i b i l i t y of t h e Earth-Moon L i b r a t i o n P o i n t s from ATM
(Ref. A u g . / ~ e p t . 1968, p. 46 and .June/.July 1968, p. 46)
A l l p r e s e n t l y planned development work on t h i s problem has
been completed and i s being documented. F u t u r e p r o d u c t i o n runs w i l l
probably occur a t i r r e g u l a r i n t e r v a l s a s more d e t a i l s on t h e ATM m i s s i o n
become a v a i l a b l e .
During t h e course of t h i s work, a n e r r o r was discovered i n
a n e x i s t i n g program a t t h e Computation Laboratory. The program was one
used t o c o n v e r t t h e ephemeris from a "mean e q u a t o r and equinox of 1950.0"
c o o r d i n a t e system t o a "mean e q u a t o r and equinox of date" c o o r d i n a t e
system. This program had a time e r r o r of 110.8 minutes which produced
a n e r r o r i n t h e a n g u l a r p o s i t i o n of t h e sun of a b o u t one t e n t h of one
d e g r e e , and a n e r r o r i n t h e a n g u l a r p o s i t i o n of t h e moon of about one
degree.
(An e r r o r i n t h e a n g u l a r p o s i t i o n of t h e moon of one degree i s
e q u a l t o two l u n a r d i a m e t e r s . )
The s e a r c h f o r t h i s e r r o r consumed more
than one week and, what i s more s e r i o u s , someone i n t h e p a s t may have
used t h i s program w i t h t h e e r r o r unknowingly.
�D.
General
1.
Response of F l e x i b l e Space Vehicles t o Docking fmpact
The e f f o r t thus f a r has been d i r e c t e d a t completion of t h e
phase wherein t h e chase and t a r g e t v e h i c l e s a r e assumed t o be r i g i d b o d i e s .
The programming and f o r m u l a t i o n corresponding t o t h i s phase of t h e t a s k
i s complete. The d i g i t a l program i s being e x e r c i s e d w i t h a s e t of nominal
parameters t h a t c h a r a c t e r i z e a t y p i c a l AAP con£ i g u r a t i o n , i n c l u d ing t h e
docking mechanism parameters
.
The c a l c u l a t i o n s f o r response based on r i g i d chase and t a r g e t
v e h i c l e s w i l l , i n a l l p r o b a b i l i t y , i n f l u e n c e t h e modeling and f o r m u l a t i o n
corresponding t o t h e e l a s t i c chase and t a r g e t v e h i c l e s phase of t h e s t u d y .
It i s expected t h a t c e r t a i n s i m p l i f y i n g assumptions can be made based on
t h e r e s u l t s of t h e i n i t i a l phase of t h e s t u d y . R - A E R O - D D I M ~ ~ ~ ~ ~
2.
S t r u c t u r a l Damping P r e d i c t i o n s (Aug. / S e p t .
1968, p. 47)
The m a t e r i a l damping program w a s completed and p a r t i a l l y
checked o u t d u r i n g October. This program n u m e r i c a l l y i n t e g r a t e s elemental
m a t e r i a l damping over t h e volume of each s t r u c t u r a l element. I t then sums
t h e energy d i s s i p a t e d and t h e s t r a i n energy f o r each element over the
e n t i r e s t r u c t u r e . The s o l a r a r r a y s of t h e Apollo Telescope Mount a r e
being used f o r checkout. R-AERO- lockheed heed
3.
Study of Use of S c a l e Models t o Determine t h e S t r u c t u r a l
Dynamics C h a r a c t e r is t i c s of Space Vehicles (New)
The f o l l o w i n g p r o g r e s s has been made i n t h i s study:
(a) V i b r a t i o n a n a l y s i s of t h e f u l l - s c a l e a n t e n n a c o n f i g u r a t i o n was completed, t o p r o v i d e bas i s f o r comparison w i t h v a r i o u s models.
(b) A s i m p l i f i e d e q u i v a l e n t beam-type model c o n f i g u r a t i o n
was a n a l y z e d . V i b r a t i o n a n a l y s i s was completed and the method of cons t r u c t i o n was found u n s a t i s f a c t o r y . A s t u d y of b e t t e r beam-type r e p r e s e n t a t i o n of t h e s t r u c t u r e i s underway.
( c ) A g e n e r a l approach f o r s t i f f n e s s s i m u l a t i o n f o r v a r i o u s
methods of antenna model c o n s t r u c t i o n was o u t l i n e d . Design c a l c u l a t i o n s
f o r t h e model s h e l l s of t h e S a t u r n V second s t a g e t a n k , s k i r t , and a d a p t e r
have been made f o r two types of models.
(d)
evaluated.
V i b r a t i o n modes f o r t h e AAP c l u s t e r were r e c e i v e d and
�( e ) A s t u d y of a l t e r n a t e approaches t o the c o n s t r u c t i o n of
each of t h e main s e c t i o n s of t h e c l u s t e r was continued. Study of l i q u i d
mass s i m u l a t i o n was begun. R-AERO- artin in
4.
System P r o b a b i l i t y Module (Ref. ~ u n e / J u l y 1968, p. 4 8 )
During t h i s performance p e r i o d , t h e methods devised f o r
u s i n g t h e Markov Chain Theory f o r c a l c u l a t i n g p r o b a b i l i t i e s a r e i n t h e
f i r s t s t a g e s of programming. The programming should be completed d u r i n g
t h e n e x t one o r two r e p o r t i n g p e r i o d s . ~ - A ~ ~ o - ~ A ~ / L o c k h e e d
VIII
.
A.
FLIGHT TEST ANALYSIS DIVISION
S p e c i a l P r o j e c t s O f f i c e and S t a f f
1.
F l i g h t ~ v a l u a t i b nPanel (FEP)
a.
Meeting
The s i x t e e n t h meeting of t h e F l i g h t E v a l u a t i o n Panel
was h e l d a t MSC on October 8 , 1968. M r . Don D. Arabian, Chief of t h e
T e s t D i v i s i o n i n t h e Apollo S p a c e c r a f t Program O f f i c e , i s t h e new MSC
co- chairman.
Major agenda d i s c u s s i o n s concerned i n t e r - c e n t e r anomaly
i n v e s t i g a t i o n procedures, subpanels r e p o r t s , and manned f l i g h t i n t e r center i t e r f a c e plans.
It was a l s o agreed t h a t t h e FEP w i l l g e n e r a t e a
proposed r e w r i t e of Apollo Program D i r e c t i v e 19 f o r submission t o
Headquarters.
A f t e r t h e FEP meeting on October 8 , 1968 a t MSC,
M r . Arabian s t a t e d t h a t t h e l a t e s t f i n d i n g s of t h e AS-502 133-seconds
anomaly a b s o l v e t h e launch v e h i c l e f o r t h e s p a c e c r a f t f a i l u r e . These
f i n d i n g s d e r i v e d from microdens i t o m e t e r (photogrammetric) a n a l y s e s of
s e l e c t e d frames of t h e ALOTS f i l m n e a r 133-seconds combined w i t h t e s t s
on honeycomb s t r u c t u r e l e a d them t o t h e c o n c l u s i o n t h a t honeycomb
debonding p e r m i t t e d i n t e r f a c e s h e e t f a i l u r e followed by t h e o u t e r f a c e
s h e e t f a i l u r e . M r . Arabian was t o b r i e f M r . Low on t h e s t a t u s t h a t
a f t e r n o o n and w a s recommending t h a t t h e Apollo 6 anomaly r e p o r t be
i s s u e d d e l e t i n g t h e a n a l y s i s on t h e S-IVB and I U . M r . E r n e s t Nathan
a g r e e d , i f a c r e d i t remark f o r MSFC s u p p o r t i n t h e i n v e s t i g a t i o n i s
included. MSFC w i l l b e a b l e t o review t h e anomaly d r a f t of t h e r e p o r t
b e f o r e p u b l i c a t i o n . M r . Arabian was most complimentary t o MSFC f o r i t s
support during the i n v e s t i g a t i o n .
�b.
Activities
(1) An MSFC t e c h n i c a l c o n t i n g e n t a t t e n d e d the Apollo 7
(128-205) F l i g h t Crew Systems Debriefing ( C o n f i d e n t i a l ) a t MSC on October 31
and November 1, 1968. The group headed by M r . E r n e s t B. Nathan, MSFC
Co-Chairman of t h e Apollo F l i g h t E v a l u a t i o n Panel (FEP) , cons i s ted o f :
James S i s s o n (I-IB-E) - S a t u r n I B Program
F l i g h t Dynamics and Mechanics
Robert Jackson (R-AERO-P)
As
t
r
i o n i c s Sys tems
Glen R i t t e r (R-ASTR-S)
Robert Hunt (R-P&VE-S) Propuls i o n and S t r u c t u r e s
D r . James Dozier (R-SSL-P) - A s t r o p h y s i c s .
-
-
-
Attendance was p r i m a r i l y f o r t h e launch v e h i c l e p o r t i o n of t h e d e b r i e f i n g , e x c e p t f o r M r . Nathan, who was t h e r e b o t h days, and M r . Dozier, who
a l s o a t t e n d e d t h e Crew Observations p o r t i o n . The FEP a l s o arranged f o r
i n t e r m i t t e n t a t t e n d a n c e of M r . J e f f e r y H a m i l t o n , t h e MSFC AAP l i a i s o n
r e p r e s e n t a t i v e a t MSC.
(2) Air-to-ground v o i c e t r a n s c r i p t s through T f 30
(cSM-S-IVBIIUISLA
rendezvous) were condensed t o a launch v e h i c l e
hours
o r i e n t e d c o n t e n t and d i s t r i b u t e d t o MSFC management, s e l e c t e d FEP and
FEWG members, AAP, and o t h e r i n t e r e s t e d t e c h n i c a l elements.
(3) Two c l a s s i f i e d volumes of the F l i g h t Crew Technical
D e b r i e f i n g t r a n s c r i p t s were d i s t r i b u t e d t o MSFC personnel on a need-toknow bas i s .
(4) MSFC i n p u t s t o t h e Apollo 8 ( A S - ~ O ~ / C S M - ~FOl i~g)h t
Crew D e b r i e f i n g Guide were compiled f o r t r a n s m i t t a l t o MSC.
2.
Apollo A p p l i c a t i o n s
-
FEWG
-
Payload
The group membership i s being r e c o n s t r u c t e d because of t h e
cons i d e r a b l e changes that. have been made i n t h e MSFC r e s p o n s i b i l i t i e s
d u r i n g t h e p a s t y e a r . New e v a l u a t i o n r e s p o n s i b i l i t i e s have been added,
and concepts have been r e v i s e d , a s the many new a s p e c t s of manned payloads have been a n a l y z e d . The d a t a flow i n t e r f a c e has been under study
and i s now b e i n g worked w i t h t h e newly formed i n t e r - c e n t e r panel.
A p r e l i m i n a r y d r a f t of t h e updated programmatic p l a n f o r
AAP Payload E v a l u a t i o n has been d i s t r i b u t e d t o t h e membership f o r review
and comment. A g e n e r a l p r e s e n t a t i o n and review meeting of t h e group i s
planned f o r e a r l y n e x t y e a r t o up-date t h e developments f o r t h o s e prev i o u s l y involved and t o o r i e n t t h e new elements, i n c l u d i n g t h e new module
contractors.
�Very meager a s s i s t a n c e has been a v a i l a b l e from t h e i n t e g r a t i o n c o n t r a c t o r , who i s t o supply s t a f f s u p p o r t t o t h e group. It i s
expected t h a t t h i s s u p p o r t w i l l be s u f f i c i e n t t o be,meaningful e a r l y n e x t
y e a r . The e a r l y d r a f t s of t h e m i s s i o n p l a n s a r e being delayed a s a r e s u l t .
3.
Mission E v a l u a t i o n Panel
The f i r s t meeting of t h e AAP Mission E v a l u a t i o n Panel was
h e l d a t MSFC on November 7 t h . R e p r e s e n t a t i v e s fromMSFC, MSC, KSC, GSFC,
and Headquarters a t t e n d e d . H i g h l i g h t s of t h e p r i m a r i l y o r g a n i z a t i o n a l
meeting were membership review, s t a t e m e n t of MEP p o l i c i e s , proposed
c h a r t e r review and AAP d a t a p l a n s t a t u s . One of t h e f i r s t a r e a s of
a c t i v i t y of t h e panel w i l l be i n p o s t - f l i g h t d a t a flow handling.
B.
F l i g h t E v a l u a t i o n Branch
1.
Saturn I B
a.
AS-205 P o s t f l i g h t T r a j e c t o r y
The a c t u a l f l i g h t t r a j e c t o r y of t h e AS-205 v e h i c l e
launched on October 11, was v e r y c l o s e t o nominal. The t o t a l spacef i x e d v e l o c i t y a t S-IVB c u t o f f was 0.4 m/s lower than nominal. A t
S-IVB c u t o f f , t h e a l t i t u d e and s u r f a c e range were 0.2 km h i g h e r than
nominal and 1.1 km g r e a t e r than nominal, r e s p e c t i v e l y .
The powered-flight t r a j e c t o r y , based e n t i r e l y on C-band
r a d a r t r a c k i n g d a t a , was determined by CCSD a t Michoud. The MSFCdeveloped GATE program w a s t h e method used, and f o r t h e f i r s t time, a
f i n a l t r a j e c t o r y was e s t a b l i s h e d w i t h o u t using any h i g h p r e c i s i o n t r a c k ing d a t a .
The o r b i t a l t r a j e c t o r y was obtained w i t h t h e OCP program
u s i n g C-band r a d a r d a t a from s e v e r a l s t a t i o n s . An e s t i m a t e of t h e v e n t i n g f o r c e s was obtained from t h e telemetered guidance d a t a . The o r b i t a l
and powered f l i g h t t r a j e c t o r i e s were c o n s i s t e n t , and were merged t o form
a smooth continuous t r a j e c t o r y from guidance r e f e r e n c e r e l e a s e t o S-IVBISC
separation.
The n a v i g a t i o n update was accomplished w i t h a c c e p t a b l e
a c c u r a c y , and t h e LOX s a f i n g experiment was a b o u t a s expected. One a r e a
of i n t e r e s t i s t h e more-rapid-than-predicted decay of t h e S-IVB o r b i t .
MSC i s i n t e r e s t e d because t h e s p a c e c r a f t had t o make a n unplanned 5 f t / s e c
maneuver t o accomplish rendezvous. A t t h i s time, no c o n c r e t e evidence
has been found p o i n t i n g t o a cause, b u t t h e i n v e s t i g a t i o n i s c o n t i n u i n g .
MSC agreed t o a c c e p t our r e s u l t s on t h e o r b i t a l recons t r u c t i o n and w i l l use t h e MSFC g e n e r a t e d ephemeris up t o S-IVB/SC
separation.
�b.
AS-205 P o s t f l i g h t Guidance Analysis
The AS-205 guidance a n a l y s i s was e s s e n t i a l l y completed
and g i v e n t o t h e F l i g h t E v a l u a t i o n Working Group (FEWG) as a p a r t of
t h e i r r e p o r t . The a n a l y s i s i n d i c a t e s t h a t t h e hardware e r r o r s were v e r y
s m a l l and t h a t t h e pos t f 1i g h t e s t a b 1 ished t r a j e c t o r y was good.
The n a v i g a t i o n update of t h e s t a t e v e c t o r on AS-205 was
s u c c e s s f u l i n t h e s e n s e t h a t t h e update was accepted by t h e system.
2.
Saturn V
a.
AS-503 Abort and A 1 t e r n a t e Miss i o n Ana1ys.i~.
The d e l i v e r y s c h e d u l e f o r t h e AS-503C' Abort and
A 1 t e r n a t e Mission Document is as follows:
Item
-
Due Date
I
I1
111
Final
Status
Received
Received
Received
Expected
on
on
on
on
time
time
time
time
Item I i s t h e m a l f u n c t i o n a n a l y s i s from l i f t o f f t o e a r t h parking o r b i t .
Item I1 is t h e m a l f u n c t i o n a n a l y s i s from parking o r b i t t o TLI w i t h t h e
s p a c e c r a f t (primary m i s s i o n ) . Item I11 i s t h e a n a l y s i s from parking
o r b i t t o TLI w i t h o u t t h e s p a c e c r a f t ( a l t e r n a t e m i s s i o n ) . The f i n a l
item w i l l be a summation of t h e t h r e e d e l i v e r i e s i n c o r p o r a t i n g c o r r e c tions
-
.
I n a d d i t i o n t o t h i s AAM document, MSC has been f u r n i s h e d
p r e l i m i n a r y i n f o r m a t i o n concerning l i m i t l i n e s f o r v e l o c i t y (V) and p a t h
a n g l e (y) p l o t s i n d i c a t i n g c o n d i t i o n s from which e a r l y s t a g i n g t o t h e
S-IVB can be accomplished. This r e s u l t s i n burning t h e S-IVB t o d e p l e t i o n t o a c h i e v e a 75 nm minimum o r b i t .
An a n a l y s i s has a l s o been performed t o determine when
i t i s n e c e s s a r y t o s t a g e t o t h e S-IVB (assuming a previous m a l f u n c t i o n )
t o avoid extended S - I 1 burn such t h a t t h e c h i f r e e z e would p r e v e n t t h e
S-IVB from o b t a i n i n g proper end c o n d i t i o n s due t o h i g h a l t i t u d e s .
b.
been i n i t i a t e d .
AS-504 Abort and A l t e r n a t e Mission Analys5s
The AS-504 D Abort and A l t e r n a t e Miss i o n Analysis has
A l l of t h e GFD requirements have been s a t i s f i e d , and
�the p r c l iminary f l i g h t program p r e - s e t t i n g s have been d e r i v e d . Since t h e
PLJ s y s t c r n w i l l bc "closcd loop" on t h e S - I 1 s t a g e , a f a i l u r c a n a l y s i s w i l l
I>c pcrformcd
.
c.
AS-503 Dynamic A n a l y s i s and Wind Limits
The AS-503 D Mission Dynamics Analysis was published t o
s e r v e a s a p r e l i m i n a r y AS-504 Dynamics A n a l y s i s . This document i s b e i n g
updated f o r t h e C' m i s s i o n . S t a b i l i t y margins w i l l be contained i n a n
appendix of t h e updated document i n t h e form of r o o t l o c i of t h e l e a s t
s t a b l e v e h i c l e c h a r a c t e r i s t i c r o o t s . R-P&VE-S has i n d i c a t e d t h a t t h e
f i n a l AS-503 A-B s t r u c t u r a l l i m i t s a r e n o t expected t o change s i g n i f ic a n t l y . T h e r e f o r e , the e x i s t i n g i n f l i g h t wind l i m i t s a r e not expected
t o be updated.
d.
AS-504 Dynamics Analysis and Wind L i m i t s
TBC p l a n s t o b e g i n work on t h e AS-504 Dynamics Analysis
Document soon i n o r d e r t o meet t h e i r scheduled d e l i v e r y d a t e of January 20,
1969. However, t h e l i f t o f f and tower c l e a r a n c e s e c t i o n s t u d i e s w i l l be
delayed u n t i l t h e s o f t r e l e a s e c o n f i g u r a t i o n , t h e S-IC engine alignment
d a t a , and t h e ground winds a r e d e f i n e d .
e.
AS-503 Emergency D e t e c t i o n System Analysis
Documentation of t h e EDS a n a l y s i s f o r t h e C' m i s s i o n i s
now a v a i l a b l e .
The t h r e e r e p o r t s which c o n s t i t u t e t h i s e f f o r t a r e t h e
AS-503 D M i s s i o n Document and t h e two l e t t e r r e p o r t s updating t h e a n a l y s i s
t o t h e C' m i s s i o n . As-503 Emergency D e t e c t i o n System and F l i g h t L i m i t s
Report should be d i s t r i b u t e d soon.
3.
General
a.
Unified S-Band Tracking Data U t i l i z a t i o n
The c a p a b i l i t y t o c o n v e r t Unified S-Band from i t s
r e c e i v e d format t o one compatible w i t h o t h e r program requirements has
been completed. The AS-502 USB d a t a have been converted and w i l l be used
t o check o u t o t h e r decks p r e p a r a t o r y t o t h e AS-503 e v a l u a t i o n .
b.
Two Body S e p a r a t i o n S i m u l a t i o n Program
Nortronics-Northrop has prepared a r e p o r t TR-796-8-395,
under Schedule Order 43 documenting a six-degrees-of-freedom s i m u l a t i o n
of t h e s e p a r a t i o n of two v e h i c l e s . The program i s w r i t t e n i n D S L / ~ O ,and
IBM 7090194 s y s tem language f o r t h e s i m u l a t i o n of continuous sys tem
dynamics. The document d i s c u s s e s t h e e q u a t i o n s which a r e programmed,
c o n t a i n s a u s e r ' s manual, and i n c l u d e s a program l i s t i n g and flow c h a r t
�and a sample problem w i t h the r e s u l t s . This program was w r i t t e n t o s t u d y
r e l a t i v e motion between s t a g e s f o r a malfunctioned v e h i c l e such a s a
retro-rocket failure.
C.
Tracking and O r b i t a l A n a l y s i s Branch
1.
Saturn I B
-
AS-205
Real-time s u p p o r t provided t o t h e Mission Operations O f f i c e
d u r i n g t h e AS-205 f 1i g h t included making t r a n s f o r m a t i o n s of the MSC
v e c t o r s and e s t i m a t i n g t h e S-IVB s t a g e o r b i t a l l i f e t i m e .
Based on t h e Antigua v e c t o r a t 18:35 U.T. (end of t h e second
r e v o l u t i o n ) , t h e o r b i t a l l i f e t i m e of t h e S-IVB s t a g e was e s t i m a t e d a t
8 . 9 days (nominal p r e d i c t i o n ) and 5.6 t o 12.9 days f o r t h e i20 p r e d i c t i o n s . This compares w i t h 9 , 6.8, and 12.3 days f o r t h e p r e f l i g h t
nominal and i 20 p r e d i c t i o n s . The a c t u a l l i f e t i m e was 6 . 8 days. Since
t h e p r e d i c t i o n s were n o t a s a c c u r a t e a s p a s t p r e d i c t i o n s , we a r e examining t h e p o s s i b i l i t y of some r e t r o v e l o c i t y being a t t a i n e d a f t e r t h e
second r e v o l u t i o n due t o v e n t i n g . We have r e c e i v e d t r a c k i n g d a t a up
t o t h e 2 1 s t r e v o l u t i o n and w i l l s o l v e f o r a n o r b i t a l v e c t o r a f t e r a l l
v e n t i n g was completed, and t h e s t a g e was i n a random tumble.
2.
Saturn V
- AS-503
C'
V i r t u a l l y a l l of t h e t r a c k i n g and communications coverage
a n a l y s i s has been completed on t h e AS-503 C' m i s s i o n f o r b o t h t h e December
and January launch o p p o r t u n i t i e s . R e s u l t s have been published i n t h e
f o l l o w i n g memoranda:
(1) AS-503 C' Mission Launch Vehicle Tracking and Communicat i o n s a n a l y s i s f o r TLI Phase f o r December 21, 1968, R-AERO-FT-40-68,
October 1, 1968.
(2) AS-503 C' Option 1 Mission Launch Vehicle Tracking and
Communications A n a l y s i s f o r December Launch Opportunity, R-AERO-FT-42-68,
October 1 5 , 1968.
(3) AS-503 C' Option 1 Mission Launch Vehicle Tracking and
Communications Analysis f o r December 20-27, 1968, and January 18-24, 1969,
Launch Opportunity, R-AERO-FT-44-68, November 8 , 1968.
(4) AS-503 C' Launch Vehicle A c q u i s i t i o n and Loss Data f o r
Extended E a r t h O r b i t (No S-IVB TLI Burn), R-AERO-FT-45-68, November 12,
1968.
�(5) Tracking and Communications Analysis on t h e AS-503 C '
Launch Vehicle O p e r a t i o n a l T r a j e c t o r y
B a s i c Mission, R-AERO-FT-46-68,
November 20, 1968.
-
AS-503 C' s h i p a n a l y s i s d a t a and t r a c k i n g and communications d a t a on t h e
AS-503 a b o r t and a l t e r n a t e missions were p r e s e n t e d a t the G&P Subpanel
meeting a t MSC.
3.
AAP
a . Look-angle i n f o r m a t i o n on t h e LN/ATM f o r f i v e o r b i t s
a t 210 n.mi. a l t i t u d e f o r 28.9" i n c l i n a t i o n r e q u e s t e d by R-ASTR was
delivered.
b. P r e s e n t a t i o n s on t h e f e a s i b i l i t y of c o n t r o l l e d r e e n t r y
of t h e S-IVB s t a g e on AAP-4 and t h e OWS were g i v e n t o t h e Mission Requirements Panel meetings on October 2 4 t h a t MSFC and on November 2 1 s t a t MSC.
The p r e s e n t a t i o n on October 2 4 t h was a s t a t u s r e p o r t , and t h e November
2 1 s t p r e s e n t a t i o n was t h e f i n a l r e s u l t s of o u r s t u d i e s .
c. A contingency mode of o p e r a t i o n f o r t h e C l u s t e r m i s s i o n
was analyzed w i t h r e s p e c t t o o r b i t a l decay and l i f e t i m e . R e s u l t s of
t h i s a n a l y s i s a r e documented i n O f f i c e Memorandum R-AERO-FT-47-68,
November 20, 1968.
d. R e s u l t s of a launch phase t r a c k i n g and communications
a n a l y s i s f o r some t y p i c a l AAP S a t u r n I B low a l t i t u d e t r a j e c t o r i e s on
v a r i o u s launch azimuths a r e p r e s e n t e d i n O f f i c e Memorandum R-AERO-FT41-68, October 3, 1968.
4.
General
Arrangements have been made t o comply w i t h a r e q u e s t by
t h e C I A i n Washington (made through NASA Headquarters) f o r a copy of
our E a r t h O r b i t a l L i f e t i m e Program.
D.
F l i g h t Mechanics Branch
Saturn V
a.
.,
AS-503 C' Mission
A l l m i l e s t o n e s were a t t a i n e d f o r the January launch window
as p r e v i o u s l y r e p o r t e d f o r t h e December window. S i n c e t h i s w i l l be t h e
f i r s t manned f l i g h t of a S a t u r n V launch v e h i c l e and w i l l a l s o e n t a i l a
v a r i a b l e launch azimuth w i t h l u n a r t a r g e t i n g , c o n s i d e r a b l e e f f o r t has
been expended i n s i m u l a t i o n and v e r i f i c a t i o n procedures.
�Guidance p r e s e t t i n g s , d i s p e r s i o n a n a l y s e s , and range s a f e t y
d a t a , which have included numerous launch azimuths and engine-out simul a t i o n s , have been f u r n i s h e d a s r e q u i r e d . The f i n a l o p e r a t i o n a l t r a j e c t o r y document combining t h e December and January launch windows w i l l be
d i s t r i b u t e d i n e a r l y December.
b.
AS-504 (D Miss i o n )
A s h i f t from Launch Pad B t o Launch Pad A on t h i s f l i g h t ,
subsequent t o t h e AS-503 launch, w i l l n o t r e q u i r e a rework of o p e r a t i o n a l
t r a j e c t o r y , e t c . , a s long a s t h e i n i t i a l i z a t i o n parameters can be updated
i n t h e LVDC.
( A s t r i o n i c s Laboratory i n d i c a t e s t h i s w i l l n o t b e d i f f i c u l t
t o accomplish. )
The p r e l i m i n a r y b o o s t t o parking o r b i t o p e r a t i o n a l t r a j e c t o r y and guidance p r e s e t t i n g s have been r e c e i v e d from Boeing. A thorough
a n a l y s i s and checking of t h e p r e s e t t i n g s w i l l be made t o avoid format
d e f i n i t i o n problems, a s encountered p r e v i o u s l y f o r a v a r i a b l e launch
azimuth. The complete o p e r a t i o n a l t r a j e c t o r y document w i l l be d e l i v e r e d
i n e a r l y December. A new S - I 1 s t a g e p r o p u l s i o n p r e d i c t i o n w i l l soon be
a v a i l a b l e . This new p r e d i c t i o n has a d i f f e r e n t l o a d i n g v a l u e and a n
approximate 3-second d i f f e r e n c e i n PU s h i f t time t h a n t h a t p r e s e n t l y
being simulated.
c.
Quick Response T a r g e t i n g Program (QRTP)
Conversion of t h e QRTP from t h e Boeing computer system t o
t h e UNIVAC 1108 computer system i s now e n t e r i n g t h e d e t a i l e d checkout
phase. Data, compiled i n g e n e r a t i o n of t h e l a s t day of January 1969
t a r g e t i n g f o r t h e AS-503 C' m i s s i o n , has been s u p p l i e d f o r use a s a
b a s e l i n e f o r comparison. Miles tones of deck c o m p i l a t i o n , e x e c u t i o n ,
and ephemeris t a p e i n t e r r o g a t i o n have been a t t a i n e d . Once t h i s program
becomes o p e r a t i o n a l , i t may permit us (in-house) t o reduce t h e impact of
s u p p o r t i n g t h e numerous launch days c u r r e n t l y r e q u i r e d f o r C' and F type
miss i o n s .
d.
I n f l i g h t T r a j e c t o r y Support
The c a p a b i l i t y t o a s s e s s the S a t u r n S-IVB 2nd burn performance margin i n r e a l time i s n e a r i n g completion. The computer program i s
b a s i c a l l y t h e Marves-SPED 6D o p e r a t i o n a l t r a j e c t o r y program. Modificat i o n s t o permit i n p u t of I U and t r a c k i n g s t a t e v e c t o r s , a s w e l l a s t h e
r e f o r m a t t e d t a r g e t i n g and r e i g n i t i o n e q u a t i o n s , have been implemented.
The program, however, h a s , n o t y e t been converted from t h e IBM 7094 t o
t h e UNIVAC 1108 computer system. While t h i s conversion i s n o t mandatory
f o r t h e AS-503 C' m i s s i o n , removal of t h e 7094 computers j u s t a f t e r t h e
m i s s i o n i s flown w i l l n e c e s s i t a t e t h e s e conversions i f any in-house
o p e r a t i o n a l t r a j e c t o r y c a p a b i l i t y i s t o be maintained.
�I n t e r n a l s i m u l a t i o n s of t h e r e a l - t i m e s u p p o r t a c t i v i t i e s were
perEormed i n c o n j u n c t i o n w i t h HOSC/MCCHo p e r a t i o n s on 22 November and 3
December i n o r d e r t o confirm t i m e l i n e s . The f i r s t s u c c e s s f u l runs were
made on t h e 3 December s i m u l a t i o n .
This program i s now being completely checked o u t . It i s
f e l t t h a t v i r t u a l d u p l i c a t i o n of previous o p e r a t i o n a l t r a j e c t o r y d a t a
i s r e q u i r e d b e f o r e confidence i n a go/no-go d e c i s i o n can be e s t a b l i s h e d .
Although t h i s r e q u i r e s c o n s i d e r a b l e e f f o r t , no s i g n i f i c a n t problems a r e
a n t i c i p a t e d . This has been a coordinated e f f o r t between members of
R-AERO-FF, R-AERO-FM, Computer Sciences Corporation, and Northrop Space
Laboratories
.
e.
Document Schedules
A meeting was h e l d on October 29 w i t h R-P&VE-PPE t o e s t a b l i s h p r o p u l s i o n requirements f o r AS-505 and AS-506.
It was agreed t h a t
t h e p r e d i c t i o n s would b e f i n a l . The f o l l o w i n g s c h e d u l e was o u t l i n e d :
AS-505 nominal p r e d i c t i o n on Nov. 25, 1968
mass d a t a 2-3 days l a t e r .
-
AS-505 d i s p e r s i o n p r e d i c t i o n on Dec. 2, 1968
mass d a t a 5 days l a t e r .
AS-505 engine o u t p r e d i c t i o n on Dec. 9 , 1968
mass d a t a 5 days l a t e r .
AS-506 nominal p r e d i c t i o n on Dec. 23, 1968
mass d a t a 2-3 days l a t e r .
-
-
AS-506 d i s p e r s i o n p r e d i c t i o n on J a n . 23, 1969
mass d a t a 5 days l a t e r .
-
AS-506 engine o u t p r e d i c t i o n on Jan. 30, 1969
mass d a t a 5 days l a t e r .
-
It was agreed t o r e - s c h e d u l e t h e p r e l i m i n a r y p r o p u l s i o n
d a t a f o r AS-507 f o r February 26, 1969 ( i . e . , nominal and d i s p e r s i o n )
and engine-out d a t a f o r March 1 2 , 1969.
Based upon t h e above d a t a d e l i v e r y , t h e following document
d e l i v e r y s c h e d u l e was d e r i v e d :
�D e l i v e r y Date
Document
AS-505
AS-506
I n i t i a l Operational Trajectory
2-4-69
3-27-69
EPO and Guidance P r e s e t t i n g s
1-2-69
2-7-69
Dispersion Analysis
2-26-69
4-22-69
The F i n a l O p e r a t i o n a l T r a j e c t o r y documents have been d e l e t e d .
BIBLIOGRAPHY
1.
"Research Achievements Review, Vol. 111, Report No. 2," NASA TM
X-53777, October 1968.
2.
Smith, R. E. and D. K. Weidner, e d . , "Space Environment C r i t e r i a
G u i d e l i n e s f o r Use i n Space Vehicle Development (1968 ~ e v i s i o n ) , "
NASA TM X-53798, October 31, 1968.
3.
S p e r l i n g , Hans J . , "On t h e Real S i n g u l a r i t i e s of t h e N-Body Problem
IN-AERO-68-6, October 1 5 , 1968.
"
�APPROVAL
rodynamics Laboratory
E. D. G e i s s l e r
D i r e c t o r , Aero-Astrodynamics Laboratory
DISTRIBUTION
.R-AERO-DIR
Dr. G e i s s l e r
M r . Jean
Mr. B u t l e r
R-DIR, M r . W e i d n e r
MS-H, M i s s J e r r e l l (3)
I-V-P,
R-AERO-R
Mr. B e a n ( 4 )
Mrs. Hightower
R- AERO- T
Mr. M u r p h r e e
Mr. Cummings
Dr. Heybey
Mr. J a n d e b e u r
Dr. K r a u s e
Mr. N a t h a n
Mr. Few
M r . von P u t t k a m e r
R-AERO-P
R-AERO-D
R-AERO-A
R-AERO-G
R-AERO-Y
R-AERO-F
R-AERO-X
(8)
(16)
(16 )
(6)
(8)
(8)
(4)
PAO, M r . K u r t z
Mr. P r i c e
�
Dublin Core
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Title
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Saturn V Collection
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000046
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: October - November 1968."
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George C. Marshall Space Flight Center
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1968-12-01
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1960-1969
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Saturn Project (U.S.)
NASA space programs
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Progress reports
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Saturn V Collection
Box 29, Folder 27
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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en
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AERO-AS TRODYNAMICS LABORATORY
MONTHLY PROGRESS REPORT
October 11. 1966
INDEX
Page
.........................
ENGINEERING STAFF ......................................
PROJECTS OFFICE ........................................
AERODYNAMICS DIVISION ..................................
A. Mechanical Design O f f i c e ...........................
B . F a c i l i t i e s Branch ..................................
C . V e h i c l e D e s i g n Branch ..............................
D . Thermal Environment Branch .........................
E . Unsteady Aerodynamics Branch .......................
AEROSPACE ENVIRONMENT DIVISION .........................
ASTRODYNAMICS AND GUIDANCE TmORY DIVISION .............
A . O f f i c e o f t h e C h i e f ................................
B. Astrodynamics Branch ...............................
C . Guidance Theory Branch .............................
D . O p t i m i z a t i o n Theory Branch .........................
V I I . DYNAMICS AND FLIGHT MECHANICS DIVISION .................
A . M u l t i - P r o j e c t s .....................................
B . S a t u r n V ...........................................
C . S a t u r n IB ..........................................
D . U P ................................................
E . G e n e r a l ............................................
V I I I . FLIGHT TEST ANALYSIS DIVISION ..........................
A . S p e c i a l P r o j e c t s O f f i c e ............................
B . F l i g h t E v a l u a t i o n Branch ...........................
C . F l i g h t Mechanics Branch ............................
D . T r a c k i n g and O r b i t a l A n a l y s i s Branch ...............
ADVANCED STUDIES OFFICE ................................
A. F l i g h t Nechanics and Performance Anal y s i s Group ....
B . Systems A n a l y s i s Group .............................
C . As modynamics and M i s s i o n A n a l y s i s Group ...........
TECHNICAL AND SCIENTIFIC STAFF
�AERO-ASTRODYNAMICS LABORATORY
MONTHLY PROGRESS REPORT
October. 11, 1966
I.
TECHNICAL AND SCIENTIFIC STAFF
1.
Advanced Launch Vehicle T r a j e c t o r y Research (Northrop
C o n t r a c t S.O. 1 5 )
a.
HTO A i r b r e a t h e r Model
Work i s p r o g r e s s i n g on t h e computer model of a i r b r e a t h i n g
( l i f t i n g ) launch v e h i c l e s . The ground r u n , l i f t o f f and minimum-fuelp u l l - u p phases of t h e f l i g h t have been programmed. T r i a l runs of t h i s
p o r t i o n of t h e program showed t h e d e s i r a b i l i t y of two a d d i t i o n a l cont r o l modes d u r i n g t h e p u l l - u p .
These modes, which a l l o w a quick l i f t o f f
and a n e a r l y l e v e l f l i g h t d u r i n g sound b a r r i e r p e n e t r a t i o n , have been
i n c o r p o r a t e d i n t o t h e program.
I n a d d i t i o n , a n i t e r a t i v e loop t o cont r o l t h e v a l u e of t h e d e r i v a t i v e of v e l o c i t y w i t h r e s p e c t t o a l t i t u d e
a t t h e end of t h e p u l l - u p phase has been programmed and checked o u t .
b.
HTO/VTO Rocket Models
Both the HTO-only and t h e VTO-only decks were checked o u t
and found o p e r a t i o n a l . Northrop i s modifying t h e VTO-only deck f o r
s i m u l a t i o n of a 4 - s t a g e a s c e n t i n t h e Mars atmosphere, i n s u p p o r t of
a n o t h e r Schedule Order.
(von Puttkamer)
2.
Advanced Systems and Mission S t u d i e s
a.
S3 L a r - E l e c t r i c P r o p u l s i o n Miss ions
Aero-As trodynamics Laboratory i s s u p p o r t i n g Research
P r o j e c t s Laboratory i n s t u d i e s concerned w i t h miss ions i n v o l v i n g s o l a r e l e c t r i c propulsion.
I n an i n i t i a l "kick-off" meeting between M r . von
Pdttkamer f o r AERO and D r . S t u h l i n g e r , D r . S h e l t o n , D r . Hale, M r . Wood
and M r . D a i l e y f o r RP, t h e g o a l s and t h e modus o p e r a n d i of t h e mutual
e f f o r t s were e s t a b l i s h e d . It was decided t o undertake t h e i n v e s t i g a t i o n
of a photographic Mars m i s s i o n w i t h s o l a r - e l e c t r i c p r o p u l s i o n , involving
a n unmanned P e g a s u s - l i k e s p a c e c r a f t and sun-synchronous o r b i t s around
Mars w i t h s h i f t i n g a l t i t u d e s .
Subsequent meetings between RP and AERO personnel on
September 1 5 t h and 23rd served t o e s t a b l i s h t h e program p l a n . AERO's
c o n t r i b u t i o n w i l l be i n t r a j e c t o r y computation, m i s s i o n o p t i m i z a t i o n ,
�c o n t r o l and g u i d a n c e , o r b i t a l mechanics, and r i g i d body dynamics, t o
b e performed by AERO-G and AERO-X, w i t h t h e l a t t e r b e i n g s u p p o r t e d by
Nor t h r o p
.
Two-dimensional a n a l y s e s and p r e p a r a t i o n s f o r more s o p h i s t i c a t e d t h r e e - d i m e n s i o n a l t r a j e c t o r y s t u d i e s a r e underway. A f i r s t
r e p o r t o f p r e l i m i n a r y r e s u l t s i s s c h e d u l e d f o r e a r l y November. P a r t i c i p a t i n g AERO p e r s o n n e l i n c l u d e A. Schwaniger, Causey, R. Duncan, B. L i s l e ,
AERO c o n t a c t
Galloway, H. Ingram of AERO-G and A r c h i e Young o f AERO-X.
i s J. v. Puttkamer
.
b.
J u p i t e r Flyby Missions
C o n t a c t h a s b e e n e s t a b l i s h e d w i t h p e r s o n n e l of GDIForth
Worth i n c o n n e c t i o n w i t h i n t e r p l a n e t a r y p r o b e s t u d i e s . A GD/FW team
u n d e r D r . L. E. Hove h a s conducted a n e x t e n s i v e s t u d y o f J u p i t e r f l y b y
m i s s i o n s i n v o l v i n g S a t u r n l a u n c h v e h i c l e s f o r JPL.
A p r e s e n t a t i o n t o AERO p e r s o n n e l on October 11 of p e r t i n e n t
r e s u l t s and r e l a t e d e f f o r t s i n t h e Advanced P l a n e t a r y Probe s e c t o r i s
being prepared.
c.
L i f t i n g Body AAP Experiment
N o r t h r o p has s u b m i t t e d a p r o p o s a l o f a l i f t i n g body r e e n t r y
e x p e r i m e n t as a p o s s i b l e advanced S a t u r n I AAP m i s s i o n t o M a r s h a l l .
10's S a t u r n / A p o l l o A p p l i c a t i o n s O f f i c e i s e v a l u a t i n g t h e p r o p o s a l and
h a s a s k e d AERO f o r i n p u t s .
The p r o p o s a l h a s b e e n e v a l u a t e d and M r . J a c k Waite of t h e
S/AAP O f f i c e was informed o f AERO'S p o s i t i o n on October 4.
In general,
as a l a r g e - s c a l e t e s t o f aerodynamics of LID = 1 . 0 b o d i e s i n s u p p o r t
o f Langley/Ames a e r o n a u t i c a l work, t h e LBV e x p e r i m e n t a p p e a r s d e f i n i t e l y
d e s i r a b l e , i t b e i n g a l s o backed by r e c e n t r e s u l t s o f MSFC's RAPT s t u d y .
On t h e o t h e r hand, t e c h n i c a l 1 y and f i n a n c i a l l y , t h e e x p e r i m e n t would
have some s h o r t c o m i n g s , and t h a t , p o l i t i c a l l y , t h e r e would b e n o t h i n g
i n i t f o r AERO ( b e s i d e s p a s s i v e w a t c h i n g ) and l i t t l e f o r MSFC.
d.
T e c h n i c a l Review o f H y p e r s o n i c A i r c r a f t Technology
Aero-As trodynamics L a b o r a t o r y was r e p r e s e n t e d a t t h e 1966
t e c h n i c a l r e v i e w m e e t i n g of t h e NASAIUSAF Ad Hoc Working Group f o r
H y p e r s o n i c A i r c r a f t Technology, o r g a n i z e d by NASA a t t h e Langley R e s e a r c h
C e n t e r on September 21 and 22.
�The o b j e c t i v e of t h e conference was t o d i s c u s s t h e key
problems, t h e r e c e n t accomplishments and t h e f u t u r e plans i n t h e a r e a
of h y p e r s o n i c f l i g h t r e s e a r c h . S p e c i f i c a l l y , progress made i n t h e f i e l d
s i n c e t h e 1964165 r e p o r t of t h e USAF Ad Hoc Task Force on SCRAMJET was
t o be p r e s e n t e d .
I n 28 t e c h n i c a l p a p e r s , r e p r e s e n t a t i v e s of A i r Force and
NASA a t t e m p t e d t o p r e s e n t a d e t a i l e d survey of t h e c u r r e n t s t a t e - o f - t h e a r t of p r o p u l s i o n , aerodynamics, s t r u c t u r e s , and a p p l i c a t i o n s t u d i e s of
h y p e r s o n i c a i r c r a f t . It i s f e l t t h a t t h e meeting, under t h e chairmans h i p of John V. Becker (Langley) and Robert E . Supp (AF-APL, USAF) was
h i g h l y s u c c e s s f u l i n i t s b a s i c o b j e c t i v e of e s t a b l i s h i n g a new m i l e s t o n e
i n h y p e r s o n i c technology development.
A detailed t r i p r e p o r t ( c l a s s i f i e d Confidential) i s a v a i l a b l e from J. v . Puttkamer on r e q u e s t .
e.
AIAA Aerodynamic D e c e l e r a t i o n Sys tems Conference,
September 7-9, Houston, Texas
Besides some papers p e r t a i n i n g t o b o o s t e r r e c o v e r y , a
p r e s e n t a t i o n on e a r t h - b a s e d t e s t i n g of Voyager/Mars parachutes was of
interest.
I n t h i s paper, J. C. McFall and H. N. Murrow of NASA-Langley
r e p o r t e d on t h e NASA P l a n e t a r y Entry Parachute (PEP) Program which uses
r o c k e t s and b a l l o o n s t o conduct r e c o v e r y of Voyager-like payloads under
deployment c o n d i t i o n s envisioned f o r Mars e n t r y , i. e . , h i g h Mach numbers
(M r 1 . 2 ) and low d e n s i t i e s ( e a r t h a l t i t u d e s between 30 and 90 km).
"Quick look" d a t a of the f i r s t t e s t (of s i x planned), s u c c e s s f u l l y conducted on August 30 a t Walker AFB, were p r e s e n t e d . The 1600 l b Voyager
c a p s u l e was launched i n a n upward d i r e c t i o n by 12 s o l i d r o c k e t s from a
( r e c o r d - s i z e ) 2 6 - m i l l i o n - c u - f t b a l l o o n f l o a t i n g a t 39 km a l t i t u d e . A t
M a c h l . 2 , a n 8 4 - f o o t r i n g s a i l parachute was deployed and t h e c o n i c a l
aero-shell jettisoned.
The recovered payload of 200 l b s (plus 325 l b s
b a l l a s t ) included s u c c e s s f u l l y o p e r a t i n g onboard cameras.
(von Puttkamer)
3. Five magnetic t a p e s c o n t a i n i n g analog d a t a from 90 experimental
r u n s made by D r . F i s c h e r , I I T , have been r e c e i v e d .
D e t a i l e d computer
i n p u t parameters and o p e r a t i n g i n s t r u c t i o n s , t o g e t h e r w i t h t h e analogt o - d i g i t a l c o n v e r s i o n requirements have been agreed upon and provided
t o R-COMP by our Northrop Mission Support personnel w i t h a r e q u e s t t o
process through t h e new piecewise c o r r e l a t i o n program P a r t I. Very
l i t t l e p r o g r e s s has been made on t h e r e q u i r e d computational d a t a process i n g of t h e s e 90 runs because of a change i n personnel and because of
i n t e r f e r e n c e of o t h e r heavy workload demands on R-COME'.
The e v e n t u a l
e f f e c t of t h e s e d e l a y s on D r . F i s c h e r ' s c o n t r a c t has n o t been determined
as yet.
�The t e s t c a s e s which were m u t u a l l y agreed upon by I I T , Northrop,
R-COMP-PRV, R-AERO-AM, and R-AERO-T a s n e c e s s a r y and s u f f i c i e n t t o
e x p e r i m e n t a l l y determine t h e accuracy, e f f i c i e n c y , and l i m i t a t i o n s of
a p p l i c a b i l i t y of t h e c o n c e p t s , approximations and assumptions contained
i n t h e computer program p r e v i o u s l y prepared by R-COMP-PRV and R-AERO-AM
f o r p i e c e w i s e e s t i m a t i o n of c o r r e l a t i o n f u n c t i o n s , P a r t I, have been
o n l y p a r t i a l l y completed. R e s u l t s of t h e remaining r e q u e s t e d runs a r e
being awaited s i n c e t h e y a r e needed t o f i n i s h t h e e v a l u a t i o n and t o
document t h e s e new techniques and t h e i r r e l a t i v e performance a s compared
t o more c o n v e n t i o n a l t e c h n i q u e s .
Considerable p r o g r e s s was made t h i s month i n a t t e m p t s t o unders t a n d t h e a p p a r e n t b u t s u r p r i s i n g l y inadequate performance of t h e numerical
i a t e g r a t i o n technique t h a t had o r i g i n a l l y been a p p l ied t o t h e computation
of t h e band-averaged s p e c t r a l d e n s i t y of t h e random processes a s s o c i a t e d
w i t h t h e crossed-beam experiments. I n a n e f f o r t t o p r e v e n t scrapping
more of t h e s i g n i f i c a n t o r i g i n a l c o n t r i b u t i o n s t o t h i s sens i t i v e and
c o m p u t a t i o n a l l y d i f f i c u l t problem, some f u r t h e r e f f o r t w i l l be expended
in this pursuit.
The g e o m e t r i c c o n s i d e r a t i o n s a s r e p o r t e d l a s t month a r e cont i n u i n g b u t w i t h a lower p r i o r i t y t h a n t h e above work.
(Cumings)
11.
ENGINEERING STAFF
ODYSSEY I (Multisphere S a t e l l i t e Experiment):
The f i r s t p r o j e c t
d e f i n i t i o n s t u d y meeting was h e l d on September 8 , 1966. A l l p a r t i c i p a t i n g
l a b o r a t o r i e s have submitted a Phase "B" s t u d y p l a n except R-P&VE. Their
p l a n i s expected by October 14, 1966. The requirement f o r a u x i l i a r y prop u l s i o n i s e s s e n t i a l l y a c e r t a i n t y t o modify e x i s t i n g f l i g h t o r b i t s t o an
a c c e p t a b l e experiment o r b i t . R-AERO-F i s w e l l underway i n d e f i n i n g a c c e p t a b l e ensemble o r b i t s w i t h r e s p e c t t o s p h e r e s e p a r a t i o n and l i f e t i m e , which
a r e t h e parameters t h a t p r i m a r i l y c o n t r o l t h e experimental d a t a .
111.
PROJECTS OFFICE
1.
Incentive Contract
-
TBC S%IS
Formal n e g o t i a t i o n s on Task 8.0, " F l i g h t Systems Analysis ,"
were begun September 15, 1966. An agreement was reached between MSFC
and TBC t o a c c e p t t h e &DO i n c e n t i v e document l i s t i n g and i n c e n t i v e p o i n t
d i s t r i b u t i o n . Most of t h e c o n t r a c t wording r e l a t i n g t o t h e implementation
of Task 8.0 has been agreed upon. However, a t t h e p r e s e n t time, n e g o t i a t i o n s a r e deadlocked on t h e schedule i n c e n t i v e f o r t h e R&DO i n c e n t i v e document l i s t i n g . Every e f f o r t i s being made t o develop a n e g o t i a b l e plan.
�2.
S a t u r n I B L o g i s t i c s Vehicle Study
This s t u d y has e s s e n t i a l l y been d i s c o n t i n u e d because (1) the
a c t u a l hardware c o s t r e p r e s e n t s o n l y a s m a l l p o r t i o n of t h e t o t a l program
c o s t , (2) e l i m i n a t i o n of t h e p r e s e n t I U hardware and u s i n g a n a u t o p i l o t
system would reduce t h e c a p a b i l i t y of t h e S a t u r n I B t o a l e v e l n o t comp e t i t i v e w i t h o t h e r launch v e h i c l e systems, and (3) a l i m i t e d c o s t
r e d u c t i o n was p o s s i b l e , a l t h o u g h t h i s r e d u c t i o n would i n t h e long run
p e n a l i z e t h e S a t u r n I B launch v e h i c l e program.
3.
CCSD Performance I n c e n t i v e f o r SA-203
The a c t u a l end cond i t i o n s of f l i g h t (s-IB/ S-IVB s e p a r a t i o n
s i g n a l ) achieved d u r i n g t h e S-IB-3 f l i g h t d e v i a t e d from t h e published
nominal v a l u e s a s f o l l o w s :
V e l o c i t y (m/sec)
Actual D e v i a t i o n
23.5
Allowed D e v i a t i o n
t32.1
F l i g h t P a t h Angle (deg)
Range (km)
A l t i t u d e (km)
Cross Range (km)
A l l parameters e x c e p t t h e a l t i t u d e were w i t h i n t h e t o l e r a n c e s agreed t o
b e f o r e f l i g h t . There were two primary causes of t h e d e v i a t i o n s of t h e
S-IB-3 f l i g h t . The f i r s t was a n a l t i t u d e e f f e c t on t h e i n d i v i d u a l
engine performance which was n o t obtained from t h e engine o r s t a g e
a c c e p t a n c e f i r i n g t e s t s . The second cause, which was a l s o a d d i t i v e t o
t h e f i r s t , was a n a d d i t i o n a l i n c r e a s e i n performance caused by a n
a p p a r e n t i n f l u e n c e of t h e s t a g e on t h e c l u s t e r e d engine t h r u s t .
The performance i n c e n t i v e of t h e S-IB s t a g e c o n t r a c t s t i p u l a t e s
that t h e government and the c o n t r a c t o r w i l l a g r e e b e f o r e f l i g h t on t h e
a c c e p t a b l e t o l e r a n c e s a b o u t t h e nominal t r a j e c t o r y . I f any of t h e s e
parameters a r e o u t of t o l e r a n c e , t h e c o n t r a c t o r cannot a c h i e v e f u l l
i n c e n t i v e bonus. However, a f t e r i n v e s t i g a t i n g t h e problem, i t t u r n s
o u t t h a t t h e i n p u t d a t a s p e c i f i e d by MSFC were i n e r r o r . Based on t h e
i n p u t d a t a f u r n i s h e d t o CCSD, i t appears t h a t t h e t r a j e c t o r y d a t a s u p p l i e d
by CCSD were c o r r e c t . T h e r e f o r e , i t was recommended t h a t CCSD n o t be
p e n a l i z e d , i n t h i s p a r t i c u l a r c a s e , f o r being o u t of t o l e r a n c e i n a l t i tude.
�IV.
AERODYNAMICS DIVISION
A.
Mechanical Design Off i c e
1. R-ME f a b r i c a t i o n s u p p o r t has been d r a s t i c a l l y reduced during
t h i s r e p o r t i n g period.
I n s u f f i c i e n t funds has f o r a l l p r a c t i c a l purposes
e l i m i n a t e d t h e u s e of R-ME'S s i n g l e s u p p o r t c o n t r a c t o r , Hayes I n t e r n a t i o n a l
(and s u b s e q u e n t l y M i c r o c r a f t , A s t r o Space, e t c . ) , except f o r t h e f a b r i c a t i o n of approved S a t u r n I B and S a t u r n V mainstream programs. This l e a v e s
R-ME'S in-house shops and t h e A.E.C. shops a t Oak Ridge, Tennessee, a s
our o n l y r e 1 i a b l e f a b r i c a t i o n s o u r c e s . A 1 though n e g o t i a t i o n s a r e underway i n a n a t t e m p t t o o b t a i n a d d i t i o n a l funds f o r R-ME'S s i n g l e s u p p o r t
c o n t r a c t o r , t h e s h o r t a g e of f a b r i c a t i o n c a p a b i l i t y should be considered
i n t h e planning of f u t u r e p r o j e c t s .
2.
F a b r i c a t i o n of a l l items f o r t h e base flow t e s t c e l l ,
model and s u r v e y assembly f o r Tunnel "E", V.K.F. AEDC, i s complete and
t h e s u r v e y assembly i s being checked o u t . Shipment t o AEDC w i l l be made
d u r i n g t h e f i r s t week i n October.
3 . The probe c a r t assembly and survey r a k e s f o r t h e cold flow
d u c t have been d e l i v e r e d . These a r e t h e f i n a l mechanical components
r e q u i r e d f o r cold flow cross-beam c o r r e l a t i o n t e s t i n g .
4. The f l a t p l a t e model assembly i s undergoing f u n c t i o n a l
checkout a t t h e f a b r i c a t i o n s i t e a t A.E.C. (Oak Ridge, Tenn.) b e f o r e
shipment t o Ames f o r t e s t i n g .
5 . The f o l l o w i n g i s a l i s t of a d d i t i o n a l p r o j e c t s and t h e i r
current status :
Status
Description
Viscous Cross Flow Force Model and Balance
-
14" W.T.
Fabrication
Updated S a t u r n V Force Model- 14" W.T.
F i n and Asymmetric Body and Balances
-
14" W.T.
Sidewall-Mounted I n n e r s t a g e Ring Model and
14" W.T.
Balance
Updated S a t u r n TB Tank
Balance - 14" W.T.
Drafting
Loads Force Model and
Design
Design
Design
Balance Cal i b r a t i o n Stand
Design
8' O.D.
Drafting
Vacuum Exhaust Plenum
M o d i f i c a t i o n of Nozzle f o r S.T.S.
-
14" W.T.
Fabrication
�5.
(Continued)
Description
Status
P e r f o r a t e d F l o o r and C e i l i n g Assembly, T.T.S.
14" W. T.
P l e x i g l a s s Models f o r Cross Bean i n S.T.S.
14" W.T.
-
P r e s s u r e Models f o r Cross Beam i n S.T.S.
S a t u r n I B Thin Skin Heat T r a n s f e r Model
-
-
Fabrication
-
Fabrication
14" W.T.
Fabrication
JPL
Design
Base Heating Model f o r IBFF
Drafting
High Reynolds No. F a c i l i t y Development
Design
B.
F a c i l i t i e s Branch
1.
Impulse Base Flow F a c i l i t y
A l l systems a s s o c i a t e d w i t h t h e m o d i f i c a t i o n t o extend t h e
p r e s s u r e and vacuum c a p a b i l i t i e s of t h e f a c i l i t y have been checked o u t .
The North American A v i a t i o n , Dual Plane S e p a r a t i o n T e s t
f o r R-AERO-AT has begun w i t h some f i f t y runs being completed.
R e s u l t s from t h e cold flow phase (using N 2 g a s ) of t h e
above t e s t a r e i n r e a s o n a b l e agreement w i t h d a t a obtained a t t h e Langley
Research C e n t e r . The l i m i t e d d a t a obtained thus f a r from t h e *how flow
phase, u s i n g HZ and O2 combustion, a r e i n good agreement w i t h cold flow
d a t a when t h e i n t e r s t a g e i s 120 inches o r more a f t of t h e s e p a r a t i o n
p o i n t ; however, d a t a obtained t h u s f a r w i t h t h e i n t e r s t a g e between t h e
s e p a r a t i o n p o i n t and 120 inches a f t i n d i c a t e a s i g n i f i c a n t i n c r e a s e i n
l o a d s . S i n c e o n l y a v e r y few runs have been made, no conclusions can be
drawn u n t i l f u r t h e r d a t a a r e a v a i l a b l e .
P r e s e n t plans c a l l f o r a t e s t program t o i n v e s t i g a t e p o s s i b l e
dimensional s c a l i n g e f f e c t s on t h e s t a r t i n g time of a h i g h Reynolds
Number f a c i l i t y a t t h e c o n c l u s i o n of t h e c u r r e n t t e s t .
2.
Hot and Cold Flow T e s t F a c i l i t i e s
T e s t s a r e pending f o r b o t h t h e Cold Flow F a c i l i t y and t h e
Hot Flow T e s t F a c i l i t y . Based on t h e r e l a t i v e p r i o r i t i e s , t h e a v a i l a b l e
manpower has been s h i f t e d t o o t h e r t e s t a r e a s . The shadowgraph s t u d i e s
of Mach wave r a d i a t i o n a s a n o i s e s o u r c e i n j e t exhausts should be
�resumed d u r i n g October. The nozzle plume s t u d y i s dependent on i n s t r u m e n t a t i o n c u r r e n t l y being used on o t h e r t e s t s .
It i s expected t h a t
equipment and manpower demands w i l l s l a c k e n during October, and t h e s e
t e s t s can be completed.
3.
7 x 7-Inch Bis o n i c Wind Tunnel
The i n v e s t i g a t i o n by R-AERO-AT i n t o t h e use of l a s e r s i n
measuring gas v e l o c i t i e s i s c o n t i n u i n g .
4.
Thermal-Acoustic J e t F a c i l i t y
The cold flow d u c t i s undergoing c a l i b r a t i o n t e s t s i n
p r e p a r a t i o n f o r t h e cross-beam c o r r e l a t o r s t u d i e s t o be r u n i n October.
The i n s t r u m e n t a t i o n c a r t was d e l i v e r e d d u r i n g September and i s ready
f o r use.
The s c h l i e r e n assembly i s being s t r u c t u r a l l y modified b e f o r e
a n October i n s t a l l a t i o n . Because of t h e extremely h i g h n o i s e l e v e l s
(150 db and l e s s ) a s s o c i a t e d w i t h t h e f a c i l i t y , sound l e v e l surveys
have been t a k e n and p r e c a u t i o n s taken t o avoid a c c i d e n t a l exposure.
The helium h e a t e r d e l i v e r y was p r e v i o u s l y scheduled f o r
d i d - 0 c t o b e r b u t a n unexpected mechanical f a i l u r e d u r i n g assembly has
delayed d e l i v e r y f o r a n a d d i t i o n a l 30 days.
5.
1 4 x 14-Inch T r i s o n i c Wind Tunnel
The f o l l o w i n g t e s t s were conducted during September 1966:
( a ) An i n v e s t i g a t i o n t o determine t h e aerodynamics of
s trap-on b o o s t e r u n i t s and t h e i r i n f l u e n c e on t h e c h a r a c t e r i s t i c s of t h e
70-inch diameter b o o s t e r tanks of t h e proposed uprated S a t u r n I B configurations.
T o t a l runs:
190.
(b) An i n v e s t i g a t i o n t o determine s t a t i c s t a b i l i t y charact e r i s t i c s of t h e proposed u p r a t e d S a t u r n I B c o n f i g u r a t i o n s based on t h e
u t i l i z a t i o n of s o l i d p r o p e l l a n t s t r a p - o n s .
T o t a l runs:
244.
The t u n n e l i s h e a v i l y scheduled f o r t h e remainder of t h e c a l e n d a r y e a r .
6.
Low Density Chamber
Experiments have continued i n c a l i b r a t i n g t h e Mach 4 low
d e n s i t y nozzle,
Impact p r e s s u r e measurements a c r o s s t h e nozzle e x i t
have shown a n i s e n t r o p i c c o r e diameter i n t h e range of 2 inches t o
15 i n c h e s w i t h s t a g n a t i o n p r e s s u r e of 30 microns of mercury t o 400
microns of mercury, r e s p e c t i v e l y . A Mach number of 3.865 has been c a l c u l a t e d from t h e impact t o s t a t i c p r e s s u r e r a t i o s .
�Thc molecular beam equipment has been checked o u t , and t h e
f i r s t s e r i e s of experiments f o r determining t h e c a p t u r e c o e f f i c i e n t of
C02 on l i q u i d n i t r o g e n cooled s u r f a c e s has begun.
Work has continued on t h e t i t a n i u m pumping experiment
f o l l o w i n g a b r i e f pause f o r s e t t i n g up and c a l i b r a t i n g t h e c r y s t a l microb a l a n c e d e t e c t o r system. This s t u d y i s t o determine t h e c a p t u r e coeff i c i e n t s of hydrogen on titanium-coated c r y o s u r f a c e s . R e s u l t s from
t h i s i n v e s t i g a t i o n w i l l be used t o determine i f s u c h a technique would
b e p r a c t i c a l i n extending t h e r u n time of t h e IBFF by flow a b s o r p t i o n .
7.
Heat T r a n s f e r Measurements
I n checking t h e c a l i b r a t i o n of t h e 1000°F h e a t t r a n s f e r
gages, i t was found t h a t t h e r e i s a s h i f t i n i n i t i a l r e s i s t a n c e and
dR/dT of t h e gage a f t e r each h e a t c y c l e . A f i x has been made t o t h e
gage d e s i g n , and a d d i t i d n a l gages a r e being f a b r i c a t e d .
1
I
The perforrpance of newer type gages, such a s t h e t h i n - d i s c ,
t y p e , i s b e i n g e v a l u a t e d i n t h e IBFF using t h e NAA Dual Plane Separat i o n model.
8.
Data Reduction
Three f o r c e b a l a n c e s (14 c h a n n e l s ) and a s many a s s i x b a s e
p r e s s u r e s were used i n t h e t e s t i n g of t h e uprated S a t u r n I B i n t h e
t r i s o n i c t u n n e l . Two d a t a s y s tems were used, r e q u i r i n g e x t e n s i v e modif ic a t i o n s t o t h e d a t a r e d u c t i o n program t o accommodate t h e s e channels.
The program t o reduce t h e low d e n s i t y chamber n o z z l e
c a l i b r a t i o n d a t a has been checked o u t and i s o p e r a t i o n a l .
Four f l u c t u a t i n g p r e s s u r e t r a n s d u c e r s were l o c a t e d on t h e
u p r a t e d S a t u r n I B mode1 t o g i v e "quick-look" e s t i m a t e s of t h e e f f e c t s
Limited analog r e d u c t i o n of t h e d a t a was done by
of t h e s t r a p - o n s .
Chrys l e r and R-AERO-AF personnel us ing our equipment.
The program t o reduce t h e c a l i b r a t i o n d a t a from t h e cold
flow d u c t was w r i t t e n and p a r t i a l l y debugged i n September.
9.
P r e s s u r e Measurements
The ~ y t r e x ' ~ r e s s u rt rea n s d u c e r s which a r e o f t e n used f o r
unsteady and f l u c t u a t i n g p r e s s u r e measurements a r e expensive ($400 e a . )
100 p e r c e n t l o s s i s i n c u r r e d i n any t e s t .
and f r a g i l e . U s u a l l y a 50
S i m i l a r items from o t h e r s o u r c e s a r e being e v a l u a t e d a s a cheaper and
more rugged replacement.
-
�10.
I
S a t u r n V 4 P e r c e n t A c o u s t i c Model
The 4 p e r c e n t S a t u r n model and i n s t r u m e n t a t i o n a r e being
checked o u t f o r t h e second phase of t e s t i n g a t AEDC i n December. A l l
180 e l e c t r i c a l connectors have been r e i n s t a l l e d on t h e model's w i r i n g ,
and i n s t r u m e n t a t i o n equipment r e p r e s e n t a t i v e s have r e p a i r e d equipment
t h a t f a i l e d d u r i n g Phase I.
A p r e l i m i n a r y s e t of c a l i b r a t i o n c o n s t a n t s f o r t h e recorded
d a t a has b e e n computed and submitted along w i t h s e v e r a l r e e l s of recorded
F i n a l t a b u l a t i o n s of c a l i b r a t i o n d a t a and
d a t a t o R-AERO-AU and R-COMP.
t a p e c o n s t a n t s w i l l be a v a i l a b l e i n e a r l y October.
C.
Vehicle Design Branch
1.
Saturn V
a . NASA TM X-53517, " S t a t i c Aerodynamic C h a r a c t e r i s t i c s
of t h e Apollo-Saturn V Vehicle" has been published. This r e p o r t i n c l u d e s
s t a b i l i t y , a x i a l f o r c e , and l o a d d i s t r i b u t i o n d a t a .
b. The a b o r t aerodynamics f o r t h e S a t u r n V v e h i c l e i s being
r e v i s e d . The new d a t a w i l l r e f l e c t t h e r e s u l t s of t h e AEDC 4 p e r c e n t
load d i s t r i b u t i o n t e s t , The r e s u l t s of t h i s s t u d y , which i s being performed under t h e Northrop s u p p o r t c o n t r a c t , w i l l be a v a i l a b l e i n l a t e
October 1966.
c. Range s a f e t y aerodynamics f o r t h e S a t u r n v e h i c l e w i l l
be r e v i s e d i n t h e a n g l e of a t t a c k range of 0 t o 30 d e g r e e s f b e c a u s e of
changes i n t h e s t a b i l i t y d a t a based on r e c e n t l a r g e s c a l e wind t u n n e l
t e s t s . R e s u l t s should b e a v a i l a b l e a b o u t November 1 5 , 1966.
d. Second s t a g e a x i a l f o r c e c h a r a c t e r i s t i c s f o r t h e Apollo
S a t u r n V v e h i c l e have been d e f i n e d and published i n o f f i c e memo R-AERO-AD66-41.
The forebody a x i a l f o r c e c o e f f i c i e n t s were o b t a i n e d from wind
t u n n e l t e s t s , w h i l e t h e b a s e a x i a l f o r c e was e s t i m a t e d from d a t a o b t a i n e d
i n high a l t i t u d e simulation t e s t s .
e. The flow f i e l d parameters f o r t h e S a t u r n V I ~ o y a g e rw i t h
a 5 4 - f o o t payload e x t e n s i o n have been published i n O f f i c e Memorandum
R-AERO-AD-66-43.
The d a t a p r e s e n t e d i n c l u d e t h e l o c a l p r e s s u r e coeff i c i e n t , . C p l , l o c a l Mach number Mo, and l o c a l temperature r a t i o , T~/T,.
The d a t a a r e p r e s e n t e d f o r a Mach number range of 1.75 t o 8.00 a t z e r o
a n g l e of a t t a c k .
�f . An experimental i n v e s t i g a t i o n w i l l be conducted i n t h e
MSFC 14" t r i s o n i c wind t u n n e l t o determine s t a t i c s t a b i l i t y and a x i a l
f o r c e c h a r a c t e r i s t i c s of up-rated S a t u r n V c o n f i g u r a t i o n s . I n i t i a l
t e s t s w i l l be conducted w i t h two b a s i c S a t u r n V con£ i g u r a t i o n s : a twos t a g e v e h i c l e w i t h a payload and f i n a l s t a g e diameter of 396 inches f u l l
s c a l e , and a t h r e e - s t a g e v e h i c l e w i t h a payload f i n a l s t a g e diameter of
260 i n c h e s f u l l s c a l e . Each of t h e s e c o n f i g u r a t i o n s use f o u r 120-inch
(seven segment) s o l i d r o c k e t s a t t a c h e d t o t h e S-IC s t a g e . These t e s t s ,
scheduled f o r November 1966, w i l l be conducted a t Mach numbers from 0.50
t o 5.0.
g. A f o r c e t e s t , conducted i n t h e MSFC 14" wind t u n n e l
has been completed on t h e 0.33 p e r c e n t s c a l e model A p o l l o / S a t u r n V LOR
i n which r o l l a n g l e e f f e c t s on s t a t i c s t a b i l i t y were i n v e s t i g a t e d . The
model was r o l l e d from 0 t o 180 degrees a t 22.5-degree i n t e r v a l s and
t e s t e d a t t r a n s o n i c Mach numbers. A n a l y s i s of t h e s e d a t a i s i n p r o g r e s s
and should be published w i t h i n t h e n e x t month.
h. The Lockheed H u n t s v i l l e Research and Engineering Center
have c a l c u l a t e d s t a t i c aerodynamic load d i s t r i b u t i o n s on t h e 4 p e r c e n t
s c a l e S a t u r n V a c o u s t i c s environment model t h a t was t e s t e d i n t h e AEDC
1 6 - f o o t t r a n s o n i c t u n n e l . They have a l s o p l o t t e d l o n g i t u d i n a l s t a t i c
p r e s s u r e d i s t r i b u t i o n s . The d a t a have been used t o r e f i n e e x i s t i n g
aerodynamic load and p r e s s u r e d i s t r i b u t i o n s on t h e A p o l l o / S a t u r n launch
v e h i c l e f o r Mach numbers from 0.6 t o 1.45 and a n g l e s of a t t a c k up t o
1 0 d e g r e e s . Lockheed i s p r e p a r i n g a d a t a r e p o r t which w i l l be completed
i n November 1966.
The experimental i n v e s t i g a t i o n t o determine t h e a e r o dynamic c h a r a c t e r i s t i c s of t h e S-Ic/ S - I 1 i n t e r s t a g e i s scheduled f o r
t h e l a t t e r p a r t of November i n t h e MSFC 14" t r i s o n i c wind t u n n e l . The
d a t a w i l l be used t o p r e d i c t t h e t r a j e c t o r y of t h e i n t e r s t a g e a f t e r
s e p a r a t i o n from t h e S - I 1 s t a g e f o r range s a f e t y purposes.
i.
The t u n n e l sidewall-mounted t e s t model has been designed.
D e t a i l e d d e s i g n drawing and f a b r i c a t i o n remains t o b e done. The model
w i l l be f a b r i c a t e d in-house and should be completed by November 1 5 , 1966.
2.
Saturn I B
a.
S t a t i c s t a b i l i t y t e s t s a r e t o b e conducted f o r t h e
S a t u r n IB/AS-206 and A p o l l o / S a t u r n V models i n t h e AEDC/VKF f a c i l i t y
e a r l y i n October 1966. A 0.55 p e r c e n t s c a l e model S a t u r n IB/AS-206
and 0.33 p e r c e n t s c a l e model A p o l l o / S a t u r n V a r e t o be t e s t e d a t Mach
numbers 5, 6 , 7 and 8. T h e s e d a t a w i l l supplement t h o s e o b t a i n e d i n a
t e s t which was conducted i n August 1966 a t t h e AEDc/VKF t u n n e l "A".
�b.
T e s t s have been conducted i n t h e MSFC 14" t r i s o n i c
wind t u n n e l t o determine s t a t i c s t a b i l i t y , a x i a l f o r c e , tank loads and
a c o u s t i c c h a r a c t e r i s t i c s f o r s e v e r a l proposed S a t u r n I B c o n f i g u r a t i o n s
u p r a t e d w i t h UTC-120 s o l i d p r o p e l l a n t r o c k e t motor s t r a p - o n u n i t s .
Data were o b t a i n e d f o r Mach numbers ranging from 0.5 t o 4.0 and a n g l e s
of a t t a c k up t o 18 d e g r e e s . P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t s t r a p - o n
u n i t s cause a n i n c r e a s e i n l o a d s on t h e 70-inch diameter b o o s t e r tanks
by a f a c t o r of two o r t h r e e d e g r e e s . However, t o t a l s t a t i c f o r c e s and
moments appear t o be a s expected,
3.
General
a.
Viscous Cross-Flow S t u d i e s
Large model h i g h Reynolds number f o r c e t e s t s have been
conducted a t LTV and a r e being checked f o r accuracy. It w i l l be necess a r y t o r e p e a t s e v e r a l runs b e f o r e t h e s e t e s t s a r e complete.
In addit i o n t o t h e LTV r e p o r t , d a t a c o e f f i c i e n t s w i l l be s e n t from LTV t o MSFC
by t a p e and t r a n s f e r r e d t o IBM c a r d s f o r machine p l o t t i n g used i n f i n a l
evaluation.
A f t e r s e v e r a l d e l a y s , small s c a l e f o r c e d a t a obtained
a t MSFC a r e being p l o t t e d f o r e v a l u a t i o n . These d a t a w i l l be compared
w i t h t h e l a r g e model h i g h Reynolds number from LTV when they become
available.
Hardware f o r a d d i t i o n a l small s c a l e model t e s t s (ogivec y l i n d e r f r u s t u m - c y l i n d e r ) i s expected t o be completed by mid-October
1966. These t e s t s a r e p r e s e n t l y scheduled f o r November 1966.
b.
O r i f i c e Flow C o e f f i c i e n t Study
The i n v e s t i g a t i o n t o determine o r i f i c e flow c o e f f i c i e n t s
f o r s i m u l a t e d f l i g h t boundary l a y e r c o n d i t i o n s and v a r i o u s v e n t g e o m e t r i e s ,
i n s u p p o r t of t h e S a t u r n v e n t i n g program, i s scheduled f o r f o u r weeks
beginning October 31, 1966 i n t h e Ames 6 x 6 f o o t s u p e r s o n i c wind t u n n e l .
The f a b r i c a t i o n and assembly of the f l a t p l a t e t e s t model have been comp l e t e d by AEC, Oak Ridge, Tennessee. A t r i p t o AEC i s planned f o r
October 4 through 6, 1966, by MSFC and c o n t r a c t o r (NSL) personnel t o
make a f u n c t i o n a l checkout of t h e t e s t model and a s s o c i a t e d equipment.
Because of d e l a y s i n s c h e d u l i n g t h e wind tunnel f a c i l i t y
and l o n g e r - t h a n - a n t i c i p a t e d model d e s i g n and f a b r i c a t i o n time, the cont r a c t t o Northrop Space L a b o r a t o r i e s was extended from September 1966
t o May 1967 w i t h a s l i g h t i n c r e a s e i n c o s t .
�c.
O r b i t a l Aerodynamics
I n t h e p a s t few weeks, R. Wimberly, R-AERO-ADE, i n
c o o r d i n a t i o n w i t h L. Donehoo, J. Bal l a n c e and miss i o n s u p p o r t from
Lockheed, has worked on v a r i o u s problems i n o r b i t a l aerodynamics
i n c l u d i n g p r o v i d i n g t h e Lab w i t h t h e in-house c a p a b i l i t y of p r e d i c t i n g
t h e aerodynamics of v a r i o u s o r b i t a l c o n f i g u r a t i o n s . This c a p a b i l i t y
was o b t a i n e d by c o n v e r t i n g an a l r e a d y running computer program, prev i o u s l y w r i t t e n f o r t h e IBM 7094 t o o p e r a t e on t h e CDC 3200. The
program i s l i m i t e d t o convex bodies i n f r e e molecule flow. An a d d i t i o n a l e f f o r t was made t o expand t h e e x i s t i n g program t o i n c l u d e t h e
e f f e c t s of concave b o d i e s . The n e c e s s a r y e q u a t i o n s f o r t h e drag and
l i f t c o e f f i c i e n t s f o r t y p i c a l concave c o n f i g u r a t i o n s have been d e r i v e d
and a r e b e i n g programmed f o r t h e CDC 3200.
A t t h e r e q u e s t of J. B a l l a n c e , t h e contamination problem
of t h e ATM o r b i t a l c o n f i g u r a t i o n was s t u d i e d . The a n a l y s i s included t h e
i n v e s t i g a t i o n of t h e e f f e c t s of g i v e n leakages from t h e v e h i c l e o r b i t i n g
a t a b o u t 260 m i l e s a l t i t u d e on t h e viewing c a p a b i l i t y of a t e l e s c o p e
l o c a t e d 100 f e e t from t h e v e h i c l e . "Worst" c a s e s were considered i n
d e t e r m i n i n g t h e r a d i a l molecular d e n s i t y from t h e v e h i c l e ; i t was cone t c . ) of 24 l b s / d a y
cluded t h a t a g i v e n gaseous leakage (02, C02, N,,
from t h e v e h i c l e w i l l produce a n a d d i t i o n a l d e n s i t y of molecules a t
100 f e e t from t h e v e h i c l e i n t h e o r d e r of magnitude of a normal atmosphere t h a t would appear a t a b o u t 200 m i l e s a l t i t u d e . The Martin Company,
i n a meeting a t MSFC pointed o u t a n o t h e r p o s s i b l e c o n t r i b u t i o n , confirmed ,by t h o s e i n a t t e n d a n c e , of i c e c r y s t a l s of 1-10 microns i n
d i a m e t e r . The i c e c r y s t a l s should be few i n r e l a t i o n t o the gas p a r t i c l e s ,
depending, however, on t h e dumping r a t e s , and w i l l v a r y i n d e n s i t y i n
t h e r a d i a l d i r e c t i o n a s w e l l a s w i t h time, assuming t h a t t h e dumping i s
n o t continuous. During t h e dumping p r o c e s s , each of t h e non-ionized
p a r t i c l e s d e p a r t t h e v e h i c l e a t a f i n i t e v e l o c i t y and l e a v e t h e v i c i n i t y
of t h e t e l e s c o p e i n a m a t t e r of seconds. For those i c e p a r t i c l e s w i t h
t h e p o s s i b l e s u f f i c i e n t amount of i o n i z a t i o n t o r e t a i n a p o s i t i o n c l o s e
t o t h e t e l e s c o p e w i l l be swept away by t h e a i r molecules and vaporized
It was determined t h a t the v a p o r i z a t i o n time f o r an
by s o l a r r a d i a t i o n .
i c e c r y s t a l 1 0 microns i n diameter a t 260 m i l e s a l t i t u d e should be a b o u t
30 seconds. The combined r e s u l t s of t h e s e a n a l y s e s i n d i c a t e an i n s i g n i f i c a n t e f f e c t of leakages oh t h e ATM viewing c a p a b i l i t y .
�D.
Thermal Environment Branch
1.
Saturn I B
a.
Thermal Analysis of t h e S-IVB Workshop
An a n a l y s i s of t h e s o l a r , a l b e d o , and e a r t h r a d i a t i o n
i n c i d e n t on t h e S-IVB workshop f o r a g r a v i t y g r a d i e n t o r b i t i s a b o u t
80 p e r c e n t completed. S i n c e t h e o r i e n t a t i o n of t h e v e h i c l e i n o r b i t i s
n o t f i r m , t h e a n a l y s i s i s i n t h e form of a parameter s t u d y . Five o r i e n t a t i o n s were s e l e c t e d and t h e o r b i t a l h e a t i n g c a l c u l a t e d f o r o r b i t a l
a l t i t u d e s of 175 and 259 n a u t i c a l m i l e s . Two launch d a t e s
June 2 2 and
December 22 - were considered which w i l l g i v e minimum and maximum shadow
times
-
.
b.
S-IB High Angle-of-Attack
Aerodynamic Heating
Work i s c o n t i n u i n g on t h e d e s i g n of t h e S-IB higha n g l e - o f - a t t a c k h e a t i n g model. Analyses a r e being performed t o ' d e t e r m i n e
t h e b e s t m a t e r i a l , s k i n t h i c k n e s s , and thermocouple l o c a t i o n s . M r . H i l l
of R-AERO-AEM and M r . Wilson v i s t e d JPL personnel on September 20 t o
d i s c u s s w i t h them o u r p r e l i m i n a r y p l a n s .
c.
Aerothermodynamics
The computation of t h e maximum aerodynamic h e a t i n g
environment f o r t h e SA-206 v e h i c l e has been completed. The environment
f o r t h e SA-206 was found t o be approximately e i g h t p e r c e n t more s e v e r e
than f o r t h e SA-201, and 18 p e r c e n t g r e a t e r t h a n t h e SA-202 v a l u e s .
A n a l y s i s of t h e SA-204 launch v e h i c l e environment has
been completed. The SA-204 launch environment was found t o be s l i g h t l y
l e s s s e v e r e t h a n t h e SA-201 launch environment. Thus, no thermal problems
are anticipated.
P u b l i c a t i o n of t h e SA-204 launch environment i s scheduled
f o r t h e middle of October.
C o r r e l a t i o n of model d a t a , f l i g h t d a t a and a n a l y t i c a l
c a l c u l a t i o n s f o r t h e f i r s t t h r e e S a t u r n I B v e h i c l e s i s c o n t i n u i n g . Prel i m i n a r y r e s u l t s i n d i c a t e good agreement between a n a l y t i c a l model r e s u l t s
and f l i g h t d a t a . A v a i l a b l e wind t u n n e l d a t a f o r protuberances g e n e r a l l y
r e s u l t i n more s e v e r e environments than t h o s e i n d i c a t e d by t h e f l i g h t
d a t a . This d i s c r e p a n c y i s under i n v e s t i g a t i o n . The SA-203 d a t a c o r r e l a t i o n r e p o r t is scheduled f o r p u b l i c a t i o n i n November 1966. C o r r e l a t i o n
of t h e SA-201 and SA-202 f l i g h t d a t a w i t h model d a t a and a n a l y t i c a l pred i c t i o n s is scheduled f o r p u b l i c a t i o n i n December 1966 a s a j o i n t r e p o r t .
�d.
Base Heating
Maximum base and exhaust plume h e a t i n g environments
f o r t h e SA-205 v e h i c l e were published i n September a s CCSD TN-AP-66-67.
Analyses t o determine maximum b a s e and exhaust plume
h e a t i n g environments f o r t h e SA-206 launch v e h i c l e a r e proceeding on
s c h e d u l e . These w i l l i n c l u d e a n o p t i m i z a t i o n s t u d y of t h e plume r a d i a t i o n computer program (C00050).
+
e.
Thermodynamic F l i g h t E v a l u a t i o n
Thermal e v a l u a t i o n of t h e SA-202 f l i g h t d a t a has been
completed. The MSFC-FEWG review meetings were a t t e n d e d and f i n a l r e s u l t s
r e p o r t e d t o b o t h t h e MSFC-FEWG and t o t h e CCSD-FEG.
SA-202 thermal d a t a
were found t o be g e n e r a l l y a s expected, c o r r e l a t i n g w e l l w i t h corresponding
d a t a recorded on previous S a t u r n I B v e h i c l e s .
A n a l y s i s of t h e SA-203 i n f r a r e d spectrometer d a t a i s
c o n t i n u i n g . A s a t i s f a c t o r y s e n s o r c a l i b r a t i o n f o r one of t h e two
channels has been o b t a i n e d . P u b l i c a t i o n of t h e spectrometer d a t a r e p o r t
a w a i t s f i n a l s e l e c t i o n of t h e c a l i b r a t i o n d a t a f o r t h e o t h e r channel by
MSFC
.
2.
Saturn V
a.
General
(1)
S a t u r n VIVoyager Launch Vehicle
T r a j e c t o r i e s and flow f i e l d s have been obtained
f o r t h e S a t u r n VIVoyager launch v e h i c l e . As c e n t thermal environments
w i l l b e r u n soon. Data f o r t h e shroud have been r e q u e s t e d by October 20,
and i t seems t h a t t h i s d a t e can be met.
(2)
s a t u r n Improvement S t u d i e s
P r e l i m i n a r y plans a r e being made f o r a base h e a t ing t e s t f o r S a t u r n v e h i c l e s w i t h s t r a p - o n s .
C o n f i g u r a t i o n drawings and
t r a j e c t o r i e s have been passed on t o CAL. A r e p r e s e n t a t i v e from CAI, w i l l
p r e s e n t h i s i d e a s on a t e s t program e a r l y n e x t month. The S a t u r n V conf i g u r a t i o n i s b e i n g g i v e n more c o n s i d e r a t i o n than t h e S a t u r n I B .
�(1)
Short-Duration Model T e s t
Volume I of Document D5-15615, "Saturn V Model
Base Heating T e s t A n a l y s i s (S-IC S t a g e ) ," has been r e l e a s e d . Volume I1
w i l l be r e l e a s e d soon.
(2)
Des i g n Assurance
A n a l y s i s of t h e h e a t i n g environment f o r t h e S-IC
con£ ined d e t o n a t i n g f u s e has been published i n Coordination Sheet
ATT-H-015.
The a d d i t i o n of a f a i r i n g on t h e forward s i d e of
t h e IU r e t r o - r e f l e c t o r r e q u i r e d a r e - e v a l u a t i o n of i t s protuberance
f a c t o r s and t h e a f f e c t e d a r e a s . A c o o r d i n a t i o n s h e e t w i l l be i s s u e d a s
soon a s t h e c u r r e n t environment document d r a f t i s f i n i s h e d .
The d e f i n i t i o n of energy t r a n s f e r from s o l i d
motor p a r t i c l e s t o s u r f a c e s from experimental t e s t programs i s i n rough
draft.
F i n a l r e l e a s e depends on v e r i f i c a t i o n of the r e s u l t s of one t e s t
u s i n g t h e thermal a n a l y z e r .
(3)
O p e r a t i o n a l Thermal Environment
-
SA-501
The atmospheric d e n s i t y v a r i a t i o n was r e c e i v e d
from MSFC Aerospace Environment D i v i s i o n on September 6, 1966. F l i g h t
Mechanics produced o u r r e q u i r e d + l o h e a t i n g t r a j e c t o r i e s using t h e
o p e r a t i o n a l t r a j e c t o r y a s t h e b a s e l i n e . The a e r o - h e a t i n g environment
f o r t h e s e t r a j e c t o r i e s has been determined. A rough d r a f t of t h e t r a j e c t o r y and a e r o - h e a t i n g s e c t i o n s has been completed.
S-IC b a s e h e a t i n g and S-IC/ S-11s t a g i n g environments a r e b e i n g e v a l u a t e d . Staging p r e d i c t i o n s f o r t h e LOX dome and
i n t e r s t a g e p r e s s u r e s have been completed. The a s y m p t o t i c c a l o r i m e t e r
w a l l temperature and c o n v e c t i v e h e a t i n g r a t e s have been determined.
T o t a l and d i f f e r e n t i a l p r e s s u r e e s t i m a t e s a r e being e v a l u a t e d .
(4)
F l i g h t Evaluation
Thermal a n a l y z e r models f o r t h e instrument l o c a t i o n s on t h e f i n s and engine f a i r i n g s have been c o n s t r u c t e d . The models
w i l l be checked o u t when t h e o p e r a t i o n a l environment becomes a v a i l a b l e .
A r e q u e s t t o revamp t h e t h i n s k i n computer program
f o r u s e i n f l i g h t e v a l u a t i o n was made i n Coordination Sheet ATT-H-014.
The changes w i l l reduce i n p u t time and e r r o r s .
�c.
S - I 1 Stage
The many protuberances on t h e S - I 1 a f t i n t e r s t a g e l i e
s o c l o s e t o g e t h e r t h a t t h e i r e f f e c t s o v e r l a p . NAA has requested t h a t
l a r g e a r e a s of t h e a f t i n t e r s t a g e be i n s u l a t e d because of t h e i n t e r f e r e n c e . R-AERO-ATA reviewed t h e i r thermal environments t o determine
whether t h e r e q u e s t should be approved. R-AERO-AT. recommended t h a t
l e s s a r e a b e i n s u l a t e d than NAA r e q u e s t e d , b u t I 0 approved t h e r e q u e s t
i n t o t a l s i n c e l i t t l e o r no c o s t was involved and payload i s n o t
critical.
3.
General
a.
J u p i t e r Probe
The J u p i t e r probe s t u d y has n o t been a c t i v e l y c a r r i e d
o u t t h i s month because of t h e slowness of a c q u i r i n g a computer program
n e c e s s a r y f o r i t s p r o g r e s s . A p r e s e n t a t i o n was made by H. Hoshizaki,
K. Wilson, and A. Wood of Lockheed, Palo A l t o a b o u t t h e i r ' e n t r y h e a t
t r a n s f e r work. During t h e i r p r e s e n t a t i o n , t h e y s t a t e d t h e i r o p i n i o n
t h a t shock l a y e r temperatures f o r a J u p i t e r probe might range from
20,000°K t o 50,000°K. Heating r a t e s would be h i g h enough t o cause
II
massive" a b l a t i o n , d e s t r o y i n g t h e boundary l a y e r a s i t i s u s u a l l y
thought o f . The a b s o r p t i o n c o e f f i c i e n t s f o r t h e Jovian atmospheric
g a s e s and t h e a b l a t e d m a t e r i a l seem t o be t h e d a t a which must be
g e n e r a t e d t o complete t h e i n p u t f o r t h e problem.
b.
M a r t i a n Entry Probe Study
AS0 is c o o r d i n a t i n g a s t u d y t o determine t h e
of and problems a s s o c i a t e d w i t h combining a r e t r i e v a b l e probe
w i t h t h e Mars Manned Flyby Mission. R-AERO-ATA i s s u p p o r t i n g
s t u d y w i t h h e a t i n g d a t a and h e a t s h i e l d a n a l y s e s .
Input data
being gathered.
c.
feasibility
experiment
t h e AS0
a r e now
Research i n t o t h e Problem of I n t e r a c t i o n of Coaxial
Axisymme t r i c J e t s
The i n c l u s i o n of a s u b r o u t i n e t o c a l c u l a t e and use t h e
e q u i l i b r i u m c o n s t a n t s from NASA TN D-1454, October 1962, has been
The new s u b r o u t i n e would r e q u i r e o n l y a
deferred f o r the present.
moderate expansion of t h e program; however, i t has been decided t h a t
t h i s a d d i t i o n w i l l n o t be included u n t i l t h e e n t i r e procedure u s i n g
t h e p r e s e n t e q u i l i b r i u m c o n s t a n t s u b r o u t i n e has been checked o u t .
P r o d u c t i o n ' r u n s aye being made u s i n g t h e e q u i l i b r i u m c o n s t a n t s of
"JANAF Thermochemi.ca1 Tables," by Dow Chemical Co., August 1965. These
runs a r e f o r a n o z z l e exhaust which i n c l u d e s t h e f o l l o w i n g chemical
�s p e c i e s w i t h t h e i r corresponding mass f u n c t i o n s : hydrogen, 0.00406;
w a t e r , 0.02054; carbon, 0.00006; carbon monoxide, 0.00141; carbon
d i o x i d e , 0.62051; and methane, 0.23253.
The atmosphere i s t r e a t e d a s
a m i x t u r e of oxygen (0.23300) and n i t r o g e n (0.76700).
P r e s e n t l y t h e i n i t i a l cases of n o z z l e exhaust and
t u r b i n e e x h a u s t mixing and t h o s e of t h e t u r b i n e exhaust and e x t e r n a l
a i r mixing a r e being t r e a t e d s e p a r a t e l y a s two-stream mixing problems.
The r e s u l t s of t h e s e c a s e s w i l l b e p l o t t e d and normalized f o r use a s
i n p u t t o t h e combined t h r e e - s t r e a m mixing of t h e nozzle e x h a u s t , t u r b i n e
e x h a u s t and e x t e r n a l a i r .
d.
Base P r e s s u r e and Environment
The p o r t i o n s of t h i s s t u d y c u r r e n t l y under inves t i g a t i o n i n v o l v e t h e t u r b u l e n t boundary l a y e r growth on nozzle w a l l s w i t h
mass i n j e c t i o n and t h e r e a c t i n g s h e a r l a y e r a t t h e plume boundary.
The f i n i t e - r a t e s h e a r l a y e r program i s being used on
The r e s u l t i n g s h e a r l a y e r d e s c r i p t i o n w i l l coma s e a l e v e l F-1 plume.
p l e t e t h e a n a l y s i s of t h e e n t i r e plume f o r t h i s engine using the b e s t
a v a i l a b l e a n a l y t i c a l tools. F i n i t e - r a t e shear layer calculations a r e
a l s o planned f o r t h e CAL 1120-scale F-1 burning L O ~ I E t h y l e n e , t h e 5 - 2
w i t h water-cooled d i f f u s e r r i n g , and a Rocketdyne LOXIRP-1 t e s t engine.
A v a i l a b l e experimental d a t a f o r t h e s e plumes range from simple photographs
t o t e m p e r a t u r e and composition probes through t h e plume a t s e v e r a l a x i a l
stations.
I n a d d i t i o n , t h e GAL 1120-scale F-1 engine i s being
instrumented t o measure l o c a l s k i n f r i c t i o n on t h e nozzle w a l l which
w i l l be compared w i t h t h e p r e d i c t i o n s of LMSC'St u r b u l e n t boundary
l a y e r program.
e.
O r b i t a l Heating Program
The thermal a n a l y s i s of t h e LFV engine compartment
h a s been p u b l i s h e d i n a Technical Data Release.
The r e s u l t s of t h e
s t u d y i n d i c a t e t h a t (1) t h e s t e a d y - s t a t e temperatures i n t h e nozzle
t h r o a t and chamber r e g i o n s w i l l a l l o w s e v e r a l hours of continuous operat i o n , and (2) t h a t t h e engine compartment w a l l s should be completely
i n s u l a t e d from t h e f u e l and o x i d i z e r tanks f o r s teady-s t a t e c o n d i t i o n s .
f.
Nozzle and J e t Wake Study
Two s e p a r a t e t a s k s were completed a s a r e s u l t of cont i n u i n g e f f o r t on t h e n o z z l e and j e t wake s t u d y . These two t a s k s ,
documented a s Technical Data R e l e a s e s , a r e d e s c r i b e d b r i e f l y below:
�(1) Analysis of a 3 - 2 Engine Exhaust Flow w i t h a Mach
D i s c Type of Shock S t r u c t u r e : Flow f i e l d d a t a were generated f o r a 5 - 2
engine e x h a u s t plume, u s i n g ~ o c k h e e d ' sm e t h o d - o f - c h a r a c t e r i s t i c s program.
The c a l c u l a t e d shock s t r u c t u r e w i t h i n t h e flow f i e l d was compared w i t h
t h a t observed i n photographs of a l i v e s e a l e v e l f i r i n g .
Good agreement was obtained a f t e r a d j u s t i n g t h e
chamber p r e s s u r e t o a l l o w f o r momentum l o s s e s . A f t e r t h e l o c a t i o n of
t h e shock s t r u c t u r e was s e t , t h e s u b s o n i c r e g i o n behind t h e observed
Mach d i s c w a s approximated w i t h a one-dimensional s o l u t i o n .
( 2 ) Flow F i e l d Analysis of a Cold Flow J e t : D e n s i t y
v a r i a t i o n s , i n t e r p r e t e d a s sound waves, were observed i n shadowgraphs
of a s u p e r s o n i c j e t .
These waves appear t o o r i g i n a t e a t p o i n t s of
i n t e r a c t i o n between shock waves and t h e j e t boundary. To d e f i n e more
thoroughly t h e flow p r o p e r t i e s a t those i n t e r a c t i o n p o i n t s , a n a n a l y s i s
of t h e flow f i e l d was conducted w i t h ~ o c k h e e d ' sm e t h o d - o f - c h a r a c t e r i s t i c s
program.
Data f o r t h e f i r s t two shock/boundary i n t e r a c t i o n p o i n t s were
generated.
g.
S t a g e S e p a r a t i o n Thermodynamics
Work i s c o n t i n u i n g on t h e p r e d i c t i o n of impingement
p r e s s u r e s caused by r o c k e t exhaust plumes a d j a c e n t t o s o l i d boundaries.
U n t i l r e c e n t l y , hand c a l c u l a t i o n s were r e q u i r e d t o p r e d i c t impingement
p r e s s u r e i n t h e s t r o n g shock r e g i o n where t h e flow must become s u b s o n i c
t o t u r n p a r a l l e l t o t h e s o l i d boundary. This a n a l y s i s has been combined
i n t o a n a d d i t i o n a l computer program which uses v a l u e s from t h e methodo f - c h a r a c t e r i s t i c s (MOC) plume r u n a s i n p u t . The r e s u l t s a r e being
checked a g a i n s t experimental d a t a . An improved c a p a b i l i t y has been added
t o t h e impingement flow f i e l d a n a l y s i s . It i s now p o s s i b l e t o i n p u t a
s t a r t l i n e t o t h e MOC program which has two p a r t s : a l e f t running charact e r i s t i c p o r t i o n and t h e remainder a s t r a i g h t s t a r t l i n e . This removes
some of t h e d i f f i c u l t i e s w i t h s t a r t i n g t h e impingement flow f i e l d
experienced i n t h e p a s t .
I n connection w i t h impingement h e a t i n g r a t e s , a n e f f o r t
i s underway t o use t h e LMSC/HREC t r a n s p o r t p r o p e r t y program a l o n g w i t h
t h e MOC impingement flow f i e l d t o o b t a i n v e r y a c c u r a t e t r a n s p o r t prop e r t i e s a t each p o i n t a l o n g t h e s o l i d boundary where t h e impingement
h e a t t r a n s f e r r a t e i s d e s i r e d . Using t h e s e p r o p e r t i e s i n t h e boundary
l a y e r program, t h e o b j e c t i v e i s t o compare t h e r e s u l t i n g h e a t t r a n s f e r
r a t e s t o experimental d a t a and t o determine i f t h i s a f f o r d s a marked
improvement i n t h e acCuracy of t h e p r e d i c t i o n method.
�E.
Uns tead y Aerodynamics Branch
1.
I n f l i g h t F l u c t u a t i n g P r e s s u r e and A c o u s t i c Environment
a . Environmental p r e d i c t i o n s of t h e f l u c t u a t i n g p r e s s u r e
environment i n t h e v i c i n i t y of t h e Snap-29, a r a d i o - i s o t o p e thermoe l e c t r i c g e n e r a t o r , have been completed.
b. Environmental p r e d i c t i o n s of t h e f l u c t u a t i n g p r e s s u r e
l e v e l s i n t h e v i c i n i t y of the S-IC and S - I 1 s e p a r a t i o n plane have been
completed.
c. "Quick look" r e d u c t i o n of t h e f l u c t u a t i n g p r e s s u r e d a t a
a c q u i r e d a t AEDC on t h e 4 p e r c e n t model t e s t have been implemented. A t
t h i s time t h e r e a r e no d a t a a v a i l a b l e f o r a n a l y s i s and e x t r a p o l a t i o n t o
f u l l s c a l e f l i g h t condition.
d. A "quick look" method f o r a s s e s s i n g t h e response of t h e
S a t u r n V s t r u c t u r e t o f l u c t u a t i n g p r e s s u r e f o r c e s i s being published.
It i s planned t o u s e t h e d a t a from t h e 4 p e r c e n t model t e s t a t AEDC i n
t h e s e s t r u c t u r a l r e s p o n s e e s t i m a t i o n s which w i l l be made by R-P&VE-S.
2.
Launch S i t e Acous t i c Environment
a . A l l planned t e s t s under c o n t r a c t NAS8-20223 e n t i t l e d ,
"Acoustic S c a l e Model T e s t s of High-Speed Flows , ' I have been completed.
The d a t a r e d u c t i o n of a l l a c o u s t i c measurements has a l s o been completed,
and t h e f i n a l r e p o r t covering b o t h phases of t h i s e f f o r t i s being
prepared.
b. An e n c l o s u r e f o r t h e " J e t Flow Shadowgraph" experiments
i s r e q u i r e d t o keep extraneous l i g h t s i g n a l s from over-exposing t h e
shadowgraph f i l m d u r i n g t h e experiments. The d e s i g n of t h e e n c l o s u r e
i s expected t o be completed by t h e end of n e x t month.
c. An experiment t o determine t h e e f f e c t s on t h e a c o u s t i c
environment of a j e t exhaust impingement on water i s i n p r o g r e s s .
F a c i l i t y checkout t e s t s were conducted l a s t week, and e x p e r i m e n t a l program
t e s t s a r e expected t o b e g i n soon.
d. The e n g i n e e r i n g a n a l y s i s of t h e i n f l i g h t f l u c t u a t i n g
p r e s s u r e d a t a from AS-203 has been completed.
e . A n a l y s i s of t h e f l u c t u a t i n g p r e s s u r e d a t a from AS-202
Other d a t a on a common t e l e m e t r y l i n k w i t h c e r t a i n
i s s t i l l i n progress.
f l u c t u a t i n g p r e s s u r e d a t a a r e being reviewed t o determine t h e cause of
extraneous s i g n a l s during the f l i g h t .
�.
f
Task Order #7, f o r Baganof f A s s o c i a t e s ' d a t a r e d u c t i o n
on t h e MSFC/AMES s e p a r a t e d flow experiment has been w r i t t e n t o provide
d a t a f o r a p i l o t s t u d y t o f u r t h e r e v a l u a t e t h e flow c o n d i t i o n s and
environments. Cross PSD'S, narrow band time c o r r e l a t i o n s , and s e v e r a l
r e c o r d e r h e a d - s c a t t e r e r r o r s were r e q u e s t e d f o r v a r i o u s channel p a i r s .
g . A r e p o r t on "The Ground Plane A c o u s t i c Environments
Due t o a S a t u r n V Launch from Complex 39 a t Cape Kennedy," i s completed.
h. A m o d i f i c a t i o n t o t h e 1120th s c a l e S a t u r n V launch conf i g u r a t i o n , soon t o be t e s t e d t o measure t h e a c o u s t i c s c a l i n g f a c t o r s
and t o o b t a i n c e r t a i n o t h e r d e t a i l e d information on the sound s o u r c e
mechanisms, has been made f o r T e s t ~ a b o r a t o r y ' s f a b r i c a t i o n group.
This m o d i f i c a t i o n saved c o n s i d e r a b l e time and m a t e r i a l s i n t h e t e s t
program w i t h o u t s i g n i f i c a n t p e n a l t y t o t h e a c o u s t i c d a t a a c q u i s i t i o n
program.
i. A c o m p i l a t i o n of t h e dynamic response t e l e m e t r y
channels onboard AS-2041s-IVB and subsequent f l i g h t s has been made.
The purpose of determining t h e d a t a measuring c a p a b i l i t y is t o p l a n
f o r a m o d i f i c a t i o n i n t h e program t o o b t a i n a p o s s i b l e f l u t t e r measurement program.
3.
Aeroelasticity
The wavy-wall panel f l u t t e r t e s t s conducted i n t h e
ARC 2 x 2-foot t r a n s o n i c wind t u n n e l have been completed. The d a t a
a r e b e i n g prepared f o r shipment t o MSFC.
The p r e s s u r e phase of t h e panel f l u t t e r t e s t s f o r t h e
S a t u r n IV-B forward s k i r t has been completed. The p r e s s u r e d i s t r i b u t i o n
and boundary l a y e r p r o f i l e d a t a have been reduced; however, t h e f l u c t u a t i n g p r e s s u r e environment d a t a remain t o be analyzed. Although t h e
d a t a o b t a i n e d were good, i t w a s n o t p o s s i b l e t o a c h i e v e i n f l i g h t condit i o n s i n a l l c a s e s because of wind t u n n e l l i m i t a t i o n s . The AEDC 16-foot
t r a n s o n i c wind t u n n e l was used f o r t h e s e t e s t s and w i l l b e used d u r i n g
t h e f i r s t week of October t o t e s t t h e a c t u a l f l u t t e r model.
V.
AEROSPACE ENVIRONMENT DIVISION
1. An e x p l o r a t o r y r e s e a r c h e f f o r t has been i n i t i a t e d t o compare
FPS-16 r a d a r f ~ i m s p h e r ewind p r o f i l e d a t a w i t h t h e upper atmospheric
This w i l l be
phenomena t h a t a r e d e t e c t a b l e by LIDAR techniques.
accomplished w i t h t h e a s s i s t a n c e of S t a n f o r d Research I n s t i t u t e
p r i n c i p a l i n v e s t i g a t o r ) . SRI w i l l a r r a n g e t o
(Mr. Ronald C o l l i s
probe t h e upper atmosphere a t t h e same time t h a t wind d a t a a r e being
-
�measured w i t h a Jimsphere. This work w i l l be completed a t t h e Western
T e s t Range, P o i n t Mugu, C a l i f o r n i a where Jimsphere wind p r o f i l e d a t a
a r e r o u t i n e l y a c q u i r e d . This i s being c l o s e l y coordinated between t h e
r e s p o n s i b l e R-AERO-Y, SRI and P o i n t Mugu personnel b e f o r e t h e LIDAR
t a~
measurements a r e made. Once a l i m i t e d number of ~ i m s p h e r e / L ~d~aA
samples a r e obtained, a "quick-look" a p p r a i s a l w i l l be made. Any cont i n u a t i o n of t h i s e f f o r t w i l l depend upon the r e s u l t s of t h i s i n i t i a l
e f f o r t . The LIDAR has been used s u c c e s s f u l l y t o measure such atmospheric
phenomena a s (1) cloud h e i g h t s and i n t e n s i t y , (2) p r e c i p i t a t i o n , (3)
induced and n a t u r a l p a r t i c u l a t e m a t e r i a l s of t h e atmosphere (4) v i s i b i l i t y ,
and (5) l a y e r s of extreme wind s h e a r .
2.
The m e t e o r o l o g i c a l a s p e c t s of t h e S t r a t o s c o p e I1 P r o j e c t was
i n v e s t i g a t e d d u r i n g a v i s i t by M r . Turner and M r . H i l l t o t h e h i g h a l t i Cude b a l l o o n r e s e a r c h launch s i t e a t P a l e s t i n e , Texas. Recommendations
have been made t o t h e MSFC committee reviewing t h i s p r o j e c t .
3 . A n a l y s i s of ground wind p r o f i l e d a t a t h a t were measured i n
s u p p o r t of t h e Ground Wind Loads T e s t (GWLT) of S a t u r n V
500F.at
Cape Kennedy (LP-39A) i s c o n t i n u i n g . Information on wind v e l o c i t y cond i t i o n s , i n c l u d i n g g u s t d a t a , i s being formalized and t r a n s m i t t e d t o
M r . K r o l l (R-P&W-S) a s r e q u i r e d .
-
4. A meeting was h e l d w i t h personnel of GCA Corporation a t MSFC on
August 31, 1966, t o review t h e s t a t u s of a temperature s e n s o r developThe temperature s e n s o r i s
ment program under C o n t r a c t No. NAS8-20588.
t o be used on t h e Jimsphere b a l l o o n t o o b t a i n d e t a i l e d upper atmospheric
t e m p e r a t u r e p r o f i l e d a t a a s s o c i a t e d w i t h t h e d e t a i l e d wind d a t a being
Loutinely acquired.
This c o n t r a c t i s proceeding s a t i s f a c t o r i l y and on
s c h e d u l e . No major problems have evolved. The temperature s e n s o r has
been s e l e c t e d (a 5 m i l bead t h e r m i s t o r ) , and breadboarding of t h e temperat u r e s e n s i n g system has begun.
5. Work i s c o n t i n u i n g on a s o l a r c y c l e p r e d i c t i o n technique u s i n g
random numbers. P r e l i m i n a r y r e s u l t s s u g g e s t t h a t c y c l e twenty has a
The s o l a r a c t i v i t y should r i s e r a p i d l y i n t h e months
long p e r i o d .
ahead t o a peak n e a r a monthly average of 170 during t h e l a t t e r p a r t of
1968 followed by a few y e a r s of continued h i g h a c t i v i t y .
6. Work i s p r o g r e s s i n g s a t i s f a c t o r i l y on t h e MSFC Upper Atmosphere
Measurement Program (MUMP). Two probes w i t h omegatrons, which had been
g o l d - p l a t e d s o they t h e o r e t i c a l l y would n o t a b s o r b atomic oxygen, were
launched by GSFC i n August; however, they b o t h f a i l e d t o measure t h e
Two modified instruments which i n c l u d e a proposed
a t o m i c oxygen p r e s e n t .
s , o l u t i o n t o t h i s problem w i l l be launched by MSFC t h e l a t t e r p a r t of
October w i t h t h e remaining s i x probes now scheduled f o r launch during
January 1967.
22
r;
�7 . The i n t e r i m r e p o r t on t h e m e t e o r o l o g i c a l p o r t i o n of t h e space
s t a t i o n s t u d y was completed d u r i n g t h e l a s t week of September. A f t e r
t h e p r e s e n t a t i o n t o NASA H e a d q u a r t e r s , t h e s t u d y was extended a n a d d i t i o n a l s i x weeks.
8. The 1966 r e v i s i o n t o t h e Space Environment C r i t e r i a Guidelines
f o r Use i n Space Vehicle Development document w i l l b e completed d u r i n g
t h e f i r s t week i n October.
9.
Nine p r o p o s a l s f o r t h e d e f i n i t i o n of a n i n - f l i g h t experiment
t o inves t i g a t e the phys i c s of g a s - s u r f a c e molecule i n t e r a c t i o n s i n t h e
ambient s p a c e environment were r e c e i v e d and a r e b e i n g e v a l u a t e d . The
e v a l u a t i o n w i l l be completed i n October.
10. Work i s p r o g r e s s i n g on updating t h e models of t h e Mars, Venus,
and J u p i t e r atmospheres f o r use i n advanced m i s s i o n s t u d i e s being conducted under t h e a u s p i c e s of t h e Advanced Systems O f f i c e .
11. We a r e c o n t i n u i n g t o provide atmospheric d e n s i t y d a t a t o
s u p p o r t t h e a t t i t u d e and guidance and c o n t r o l system s t u d i e s being conducted by A s t r i o n i c s Laboratory.
12. We have i n i t i a t e d a p r e l i m i n a r y a n a l y s i s of t h e e f f e c t s of
s t a t i c f i r i n g s on t h e ionosphere. We e x p e c t t o g e t some c o n t r a c t u a l
e f f o r t underway on t h i s program d u r i n g October.
13. Work has begun on i d e n t i f y i n g s o l a r c y c l e v a r i a t i o n s i n t h e
Mars atmosphere. Knowledge of t h e amplitude of t h e s e v a r i a t i o n s i s
n e c e s s a r y i n t h e advanced p l a n e t a r y probe s t u d i e s . A t t h e same time,
some e f f o r t i s b e i n g devoted t o e s t a b l i s h i n g models of t h e Mars s u r f a c e
environment and i t s v a r i a t i o n s .
VI,
AS TRODYNAMICS AND GUIDANCE THEORY DIVISION
A.
O f f i c e of t h e Ch5ef
A NASA g r a n t h o l d e r s p r e s e n t a t i o n on Control Theory was h e l d
on September 21, 1966 a t MSFC. P a r t i c i p a t i n g were P r o f e s s o r s Kinnen,
L i n d o r f f , B r i d g l a n d , FlKgge-Lotz, Polak, Meirovich, Roy, F r a n k l i n ,
Hunt, d i s cuss i n g t h e i r NASA g r a n t s .
The second NASA I n t e r c e n t e r meeting on Control Theory was held
on September 22-23, 1966 a t MSFC. The meeting covered c u r r e n t t o p i c s
of NASA r e s e a r c h i n t e r e s t i n t h e c o n t r o l t h e o r y a r e a . A b s t r a c t s of t h e
papers a r e a v a i l a b l e from R-AERO-G.
�Work was done on t h e p o s s i b i l i t y of v e r i f y i n g t h a t t h e u s u a l
1i n e a r i z a t i o n s t a b i l i t y technique (Aizerman' s c o n j e c t u r e ) l e a d s t o bounded
s o l u t i o n s . Only p a r t i a l r e s u l t s a r e o b t a i n e d on t h i s problem.
'Methods f o r i n v e s t i g a t i n g p e r i o d i c behavior i n autonomous s y s terns
were s o u g h t , i n p a r t i c u l a r , t h o s e a p p l i c a b l e t o Hamil t o n i a n systems, s u c h
a s t h e n-body problem.
The method of Krylov-Bogoliubov i s a l i k e l y
candidate
.
E x i s t e n c e and uniqueness theorems of t h e Okamura type (necessary
and s u f f i c i e n t c o n d i t i o n s ) were considered f o r p o s s i b l e a p p l i c a t i o n s i n
(J. George).
t r a j e c t o r y c a l c u l a t i o n s and p e r i o d i c o r b i t p r o p e r t i e s .
B.
A s trodynamics Branch
1.
I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House)
a . Work i s c o n t i n u i n g on t h e f r e e f l i g h t multi-body power
s e r i e s i n t e g r a t i o n deck. The n e c e s s a r y programming changes have been
made, and t h e deck i s being checked o u t .
b. Formulation of t h e e q u a t i o n s f o r a new deck designed
p r i m a r i l y f o r parameter type s t u d i e s of low t h r u s t t r a j e c t o r i e s i s
n e a r i n g completion. The deck w i l l i n c l u d e t h e second, t h i r d , and f o u r t h
harmonics of t h e e a r t h ' s p o t e n t i a l f u n c t i o n and has a f i x e d a n g l e t h r u s t ;
t h e g r a v i t a t i o n a l f i e l d s of t h e e a r t h , t h e sun, and a s e l e c t e d t h i r d
body a r e i n t e r d e p e n d e n t . The e q u a t i o n s of motion of t h e sun, probe and
t h e t h i r d body w i l l be i n t e g r a t e d u s i n g power s e r i e s , and t h e deck w i l l
compute i t s own i n t e g r a t i o n time s t e p f o r maximum speed c o n s i s t e n t w i t h
t h e s p e c i f i e d accuracy. Furthermore, a l l computations w i l l be c a r r i e d
o u t i n double p r e c i s i o n .
2.
S t u d i e s of R a d i a t i o n P r e s s u r e on a R e f l e c t i n g S a t e l l i t e
Work i s c o n t i n u i n g on t h e s t u d y t o determine t h e e f f e c t s of
t h e new c o n t r o l laws, r e c e n t l y i n s e r t e d i n t o t h e two-dimensional o r b i t a l
parameter deck, on t h e o r b i t a l p e r t u r b a t i o n s caused by r a d i a t i o n p r e s sure.
3.
Support C o n t r a c t
a.
Cislunar Orbit Studies
The deck designed t o a i d i n minimizing t h e t o t a l v e l o c i t y
increment r e q u i r e d t o p r o v i d e o r b i t a l s t a b i l i t y i n c i s l u n a r space has
been programmed and t h e check c a s e s a r e being analyzed.
�b.
I n t e r p l a n e t a r y Trans i t S t u d i e s
The c a p a b i l i t y of i n v e s t i g a t i n g a l l c l a s s e s and types
on t h e second l e g of a fly-by m i s s i o n t o determine t h e b e s t a v a i l a b l e
o r b i t has been added t o t h e Modified Marshall I n t e r p l a n e t a r y Conic
T r a j e c t o r y Program; work has now begun on t h e f o r m u l a t i o n of the programming changes n e c e s s a r y t o add powered f l i g h t c a p a b i l i t y t o t h e
deck.
C.
Guidance Theory Branch
1.
Support C o n t r a c t S t u d i e s
a.
Low T h r u s t Guidance
The a l t e r e d IGM e q u a t i o n s mentioned l a s t month have
been checked f o r a h i g h - t h r u s t (2-D) t r a j e c t o r y w i t h a burn time of
340 seconds. The t h r u s t w i l l be lowered, and t h e r e s u l t i n g t r a j e c t o r i e s
w i l l be checked f o r a c c u r a c y of t e r m i n a l c o n d i t i o n s . The a l t e r e d IGM
e q u a t i o n s have been extended t o i n c l u d e yaw maneuvers. They have n o t
y e t been programmed and checked o u t .
b.
Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange M u l t i p l i e r s
The a n a l y s i s of a s e r i e s s o l u t i o n f o r t h e i n i t i a l
m u l t i p l i e r s f o r t h e c a s e of t r a n s f e r from a f i x e d p o i n t t o a n e l l i p s e
w i t h o n l y i t s energy and momentum s p e c i f i e d has continued. As t h e
t e r m i n a l c o n d i t i o n e q u a t i o n s a r e expanded i n t o Taylor s e r i e s , i t is
n e c e s s a r y t o determine t h e i r a c c u r a c y by observing t h e magnitude of t h e
s u c c e s s i v e remainder terms. A program has been w r i t t e n t o e v a l u a t e t h e
remainder terms us ing d a t a from a numer i c a l l y i n t e g r a t e d c a l culus-ofv a r i a t i o n s t r a j e c t o r y ; a l s o , p r o v i s i o n has been made t o r e v e r t t h e
s e r i e s f o r t i m e - t o - c u t o f f v a l u e s . The energy e q u a t i o n has been expanded
and i s now b e i n g t e s t e d .
2.
In-house S t u d i e s
a . The computer program t o compute optimal continuous
t h r u s t o r b i t a l t r a n s f e r s has been coded and checked o u t , and i s now
operational.
The m o d i f i c a t i o n needed t o compute optimal t h r u s t-coas tt h r u s t o r b i t a l t r a n s f e r s w i l l now be added t o t h e program.
b. A b r i e f summary of t h e s t u d i e s performed by MSFC on
t h e f l i g h t mechanics and guidance of r e e n t r y v e h i c l e s has been prepared
f o r p r e s e n t a t i o n a t t h e NASA Ad Hoc Groups meeting on Reentry Guidance
and C o n t r o l .
�c. A low t h r u s t o r b i t a l parameter computer program has
been formulated and s e n t t o t h e Computation Laboratory f o r coding. This
program i s t o be used i n a parameter s t u d y of d e s c e n t i n t o t h e J o v i a n
atmosphere. Programming d i f f i c u l t i e s have been encountered, which have
delayed t h i s p r o j e c t .
d. Work has been i n i t i a t e d , i n s u p p o r t of RPL, on c a l c u l a t ing low t h r u s t t r a n s f e r from E a r t h t o Mars. This s t u d y w i l l r e q u i r e
some m o d i f i c a t i o n s of e x i s t i n g computer programs.
3.
Contracts
a.
Boeing
-
Rendezvous Guidance
E v a l u a t i o n of t h e r e l a t i v e c o o r d i n a t e scheme f o r t h e
t e r m i n a l burn has continued. Using o n l y t h e p o s i t i o n e q u a t i o n s t o s o l v e
a ( t h e c o n s t a n t a n g l e i n t h e X e q u a t i o n ) , we o b t a i n a v a l u e
f o r t f and .
of t f which i s d i f f e r e n t from t h e tf o b t a i n e d from s o l v i n g t h e f u l l s e t
of guidance e q u a t i o n s . As t h e f i n a l burn phase p r o g r e s s e s , i t seems t h a t
t h e d i f f e r e n c e s i n t h e t f ' s converge t o some non-zero r e a l number, N, and
remain a t N u n t i l t h e f i n a l phase i s over. Close examination of such
t r a j e c t o r i e s i n d i c a t e s t h a t the closer N i s t o zero, the smaller the
f i n a l end e r r o r i n p o s i t i o n .
I n order t o d r i v e N t o zero, a correction
scheme was added t o t h e s t e e r i n g e q u a t i o n . This c o r r e c t i o n was K(tmf t f ) ,
where K i s a predetermined c o n s t a n t . Using t h i s scheme, range a n g l e
t o 5 x 1 0 ' ~d e g r e e s .
e r r o r s were reduced from 4 x
-
b.
Lockheed
-
Rendezvous Guidance
A phase plane a n a l y s i s of t h e rendezvous guidance problem
i s continuing.
The r e s u l t i n g guidance law i s being programmed s o t h a t
s i m u l a t i o n runs can be made. Work has a l s o begun on a guidance scheme
f o r t h e f i r s t - b u r n phase of t h e rendezvous problem. This phase w i l l be
used t o p l a c e t h e i n t e r c e p t o r i n a p o s i t i o n f a v o r a b l e f o r rendezvous and
s u i t a b l e f o r t h e t e r m i n a l scheme. The energy, a n g u l a r momentum, and
o r i e n t a t i o n of t h e t r a n s f e r e l l i p s e w i l l be d e f i n e d i n terms of t h e s t a t e
v a r i a b l e of t h e i n t e r c e p t o r and t h e s e p a r a t i o n a n g l e between t h e t a r g e t
and t h e i n t e r c e p t o r .
This scheme w i l l assume some p r i o r i n f o r m a t i o n conc e r n i n g t h e t e r m i n a l burn.
c.
Vanderbil t U n i v e r s i t y
Because of v a c a t i o n s , l i t t l e p r o g r e s s was made d u r i n g
t h e month. M r . L i n n s t a e d t e r continued s t u d y of t h e extended m u l t i s t a g e
Bolza problem. D r . Bowman developed a proof of t h e m u l t i p l i e r r u l e and
t r a n s v e r s a l i t y c o n d i t i o n s based on t e n s o r and e x t e n s o r theory.
�D.
O p t i m i z a t i o n Theory Branch
1.
Design Concept Comparison Study
A s t u d y has been i n i t i a t e d t o compare s e v e r a l promising
c o n t r o l systems and t h e i r r e l a t e d s y n t h e s i s t e c h n i q u e s , and t o examine
t h e p o s s i b i l i t y of t h e i r a p p l i c a t i o n t o t h e development of a s e t of
t o l e r a n t c o n t r o l l e r s f o r the Saturn vehicles.
S i x c o n t r o l systems w i l l be s t u d i e d : two load r e l i e f s y s tems, two " t o l e r a n t " systems, and two bending s i g n a l s u p p r e s s i o n systems.
The s t u d y w i l l proceed i n two phases. The f i r s t phase w i l l be a d e t a i l e d
examination of t h e r e l a t i v e m e r i t s of t h e systems. I n the second phase,
t h e r e s u l t s of t h i s work w i l l be a p p l i e d t o t h e p r e s s i n g need f o r f l e x i b i l i t y i n t h e S a t u r n c o n t r o l systems.
2.
A p p l i c a t i o n of Optimal Control Theory f o r Design of
Load Re1 i e f C o n t r o l
The s o u r c e of p r e v i o u s l y r e p o r t e d d i f f i c u l t i e s encountered
w i t h t h e computer program developed f o r f i n d i n g optimal f i x e d feedback
g a i n s f o r s y s tems w i t h d i s t u r b a n c e i n p u t s has been found and c o r r e c t e d .
Some r e s u l t s o b t a i n e d by t h i s method a r e now being e v a l u a t e d . New
a t t e m p t s t o use t h e Newton-Raphson technique show t h a t i t i s extremely
d i f f i c u l t t o a p p l y t h e method f o r s o l u t i o n of t h i s p a r t i c u l a r problem.
The above mentioned program i s s i m p l e r c o m p u t a t i o n a l l y and p r e s e n t s
fewer d i f f i c u l t i e s i n a p p l i c a t i o n . F u t u r e e f f o r t s w i l l c e n t e r on use
of t h i s method only.
3 . A paper on advanced f l i g h t c o n t r o l techniques f o r launch
v e h i c l e s was p r e s e n t e d t o t h e NASA I n t e r c e n t e r Meeting on Control Theory
It w i l l a l s o be p r e s e n t e d a t t h e DOD/
h e l d a t MSFC on September 22-23.
NASA/FAA Conference on Navigation, Guidance, and Control a t WrightP a t t e r s o n A i r Force Base on October 1 1 - 1 2 .
4.
Northrop Schedule Order #26
a.
Voyager Load R e l i e f
Objective:
Saturn V/~oyager.
To i n v e s t i g a t e l o a d r e l i e f systems f o r t h e
A s y s tem p r e v i o u s l y s t u d i e d by Nor t h r o p f o r a p p l i c a t i o n
t o t h e S a t u r n V/LOR i s b e i n g i n v e s t i g a t e d f o r t h e Voyager t o determine
i t s l o a d r e l i e f c a p a b i l i t i e s f o r t h i s c o n f i g u r a t i o n . This system i s a
d r i f t - m i n i m i z i n g s y s tem which employs feedback of t h e v e l o c i t y normal t o
t h e r e f e r e n c e plane. A s t u d y is a l s o being i n i t i a t e d t o determine how
i n f o r m a t i o n from t h e guidance p l a t f o r m can most e f f e c t i v e l y be used t o
p r o v i d e load r e l i e f .
�b.
Learning Systems
Objective:
To determine t h e a p p l i c a b i l i t y of l e a r n i n g
s y s tems t o b o o s t e r c o n t r o l and of f - l i n e problem s o l v i n g .
A r e p o r t on t h e s t u d y i s being w r i t t e n . It i s concluded
t h a t , w i t h one p o s s i b l e e x c e p t i o n , l e a r n i n g s y s tems a r e n o t c u r r e n t l y
a p p l i c a b l e t o b o o s t e r c o n t r o l . The one p o s s i b l e p r e s e n t a p p l i c a t i o n i s
t h e use of a p e r i o d i c sampling, t o g e t h e r w i t h high-gain n o n l i n e a r t r a c k ing systems s u c h a s some of t h e l e a r n i n g d e v i c e s . This might be s u i t a b l e
f o r g a i n s t a b i l i z a t i o n of t h e bending modes. A b r i e f e x c u r s i o n i n t o
i n f o r m a t i o n t h e o r y i s being made t o determine i f a p e r i o d i c sampling of
t h e type e n v i s i o n e d w i l l s u i t a b l y d e s t r o y t h e bending information t o
p r o v i d e a c c e p t a b l e i n p u t i n t o t h e " l e a r n i n g element."
c.
A n a l y t i c Design
Objective:
f o r l i n e a r s ys tems
.
To i n v e s t i g a t e a n a l y t i c d e s i g n techniques
A r e p o r t on t h e e v a l u a t i o n of t h e a n a l y t i c d e s i g n
technique proposed by Bass and Webber of Hughes A i r c r a f t i s being prepared.
Some r e l a t i v e l y minor i n v e s t i g a t i o n s remain t o be conducted. A
summary of t h e s t u d y t o d a t e was p r e s e n t e d a t t h e Control Theory Symposium
on September 19-21.
5.
Honeywell (NAS8-11206)
a.
Development of T o l e r a n t Control Systems
O b j e c t i v e : To develop c o n t r o l l e r s which maximize t h e
t o l e r a n c e t o v e h i c l e and environmental parameter v a r i a t i o n s .
Candidate c o n t r o l l e r s have been t e s t e d by use of t h e
s y n t h e s i s programs i n t h e h i g h dynamic p r e s s u r e r e g i o n of t h e f i r s t s t a g e
t r a j e c t o r y . Many c a n d i d a t e s had d i f f i c u l t y i n r e a c h i n g t h e g i v e n load
l i m i t i n t h i s r e g i o n f o r Model Vehicle 2.
The g o a l s were reviewed, and
Future e f f o r t s w i l l
more r e a l i s t i c v a l u e s were g i v e n t o t h e c o n t r a c t o r .
i d e n t i f y t h e range of c o n d i t i o n s ( t r a j e c t o r y s u b r e g i o n s ) over which a
g i v e n c o n t r o l l e r i s adequate.
b.
Voyager Load R e l i e f
O b j e c t i v e : To develop a n e f f e c t i v e load r e l i e f c o n t r o l
s y s tern f o r t h e S a t u r n voyager.
A meeting was held a t t h e c o n t r a c t o r ' s f a c i l i t y on
D i s c u s s i o n c e n t e r e d around t h e e q u a t i o n s of motion and
September 6-7.
d e t a i l e d s i m u l a t i o n s , and on determining a "worst" wind f o r t h e c l a s s of
Implementation of t h e s i m u l a t i o n s i s s l i g h t l y
s y s tems being i n v e s t i g a t e d .
behind s c h e d u l e .
28
�A c l a s s of s y n t h e t i c winds producing l a r g e r bending
moments f o r t h e s y s tems cons i d e r e d t h a n t h e c o n v e n t i o n a l l y employed
s y n t h e t i c p r o f i l e has been i s o l a t e d . Whereas t h e conventional p r o f i l e
has s h e a r s always i n c r e a s i n g t h e wind from a s m a l l v a l u e t o a l a r g e
v a l u e , t h e new c l a s s demonstrates s h e a r r e v e r s a l ; that i s , t h e s h e a r s
d e c r e a s e t h e wind magnitude f o r a p e r i o d of time and then s h e a r s a r e
i n t r o d u c e d which i n c r e a s e t h e wind magnitude a g a i n .
R-AERO-Y personnel were r e q u e s t e d t o determine t h e
l i k e l i h o o d of t h i s phenomenon o c c u r r i n g . R-AERO-Y could n o t r e a c h any
c o n c l u s i o n s based on t h e i r l i m i t e d s t u d y . However, based on t h e i r d a t a ,
p e r s o n n e l of t h i s branch decided t h a t t h e p r o b a b i l i t y of occurrence of
s u c h a c l a s s of winds e x h i b i t i n g l a r g e s h e a r r e v e r s a l over a l t i t u d e
i n t e r v a l s of s e v e r a l hundred meters was s u f f i c i e n t l y low t h a t i t would
n o t be used a s a b a s i c d e s i g n wind f o r t h i s study.
A more d e f i n i t i v e s t u d y of t h e p r o b a b i l i t y of occurrence
of winds w i t h s h e a r r e v e r s a l and of t h e a s s o c i a t e d s h e a r s would probably
be u s e f u l f o r f u t u r e load r e l i e f system s t u d i e s . No a c t i o n has y e t been
taken t o request such a study.
6.
Sys tems Technology, I n c .
(NAS8-11419)
O b j e c t i v e : To determine t h e 1i m i t a t i o n s of convent konal
c o n t r o l systems f o r v e h i c l e s e x h i b i t i n g a l a r g e amount of intermodal
coup1 ing
.
Design of a c o n t r o l system f o r Model v e h i c l e 2 u s i n g conv e n t i o n a l components i s c o n t i n u i n g . Use of a t t i t u d e and a t t i t u d e r a t e
s i g n a l s t o s t a b i l i z e bending has been shown t o r e q u i r e some r e l a t i v e l y
complex f i l t e r i n g between second and t h i r d modes, whereas b o t h modes
can be s t a b i l i z e d w i t h r e l a t i v e l y simple f i l t e r i n g when a high-passed
a c c e l e r o m e t e r s i g n a l i s used t o s t a b i l i z e them. The e f f e c t of s u c h a
u s e of t h e a c c e l e r o m e t e r on t h e load r e l i e v i n g c a p a b i l i t y of t h e system
i s being e v a l u a t e d .
VII.
DYNAMICS AND FLIGHT MECHANICS DIVISION
A.
Multi-Projects
1.
-
Guidance
Minimization of Turn Around Time f o r t h e
Guidance System f o r Changes i n Vehicles and Missions
The bas i c h y p e r s u r f a c e f o r determining t a r g e t i n g v a l u e s
f o r t h e t r a n s l u n a r i n j e c t i o n c o n i c i s used t o a r r i v e a t a g e n e r a l i z e d
hypersurface f o r the following missions:
�(1)
Lunar o r deep s p a c e probes.
(2)
Space-fixed near e a r t h o r b i t s .
(3)
Earth- fixed o r b i t s
(4)
Orbits with o r i e n t a t i o n free.
(5)
D i r e c t a s c e n t rendezvous m i s s i o n s .
.
The s i g n i f i c a n t d i g i t s of t h e n a v i g a t i o n a l information used
i n t h e IGM s t e e r i n g e q u a t i o n s a s w e l l a s t h e f u n c t i o n s i n t e r n a l l y used
by IGM have been p a r a m e t r i c a l l y t r u n c a t e d u n t i l t h e system becomes
i n d e t e r m i n a t e o r performance and a c c u r a c e a r e s i g n i f i c a n t l y p e n a l i z e d .
This s t u d y g i v e s some i n s i g h t i n t o t h e number of s i g n i f i c a n t d i g i t s
r e q u i r e d f o r IGM t o perform i n a s a t i s f a c t o r y manner and a l s o i n d i c a t e s
how much t h e m i s s i o n can be changed w i t h o u t needing t o r e s c a l e t h e f i x e d p o i n t launch v e h i c l e d i g i t a l computer. The t r u n c a t i o n s a r e being a p p l i e d
t o t h e f o l l o w i n g miss i o n s :
(1)
Near-earth o r b i t s .
(2)
High energy e a r t h o r b i t s , i n c l u d i n g e a r t h
synchronous o r b i t s .
(3)
Lunar miss i o n s .
(4)
Typical i n t e r p l a n e t a r y miss i o n s .
The n e x t s t e p i n t h e s t u d y w i l l be t o a c t u a l l y program a n I G M s u b r o u t i n e
i n f i x e d p o i n t , s c a l e d t o a p a r t i c u l a r m i s s i o n , and determine how much
(DAG/Northrop)
t h e m i s s i o n can be changed w i t h o u t a s e r i o u s p e n a l t y .
2.
Dynamics and Control
a.
Three-Dimens i o n a l Analysis of Large Launch Vehicles
I n c l u d i n g 6 h e l l Degrees of Freedom
The e q u a t i o n s of motion have been d e r i v e d s e p a r a t e l y
f o r t h e component of t h e s t i f f e n e d s h e l l and i n t e g r a t e d i n t h e X d i r e c tion.
These s o l u t i o n s have been combined u s i n g t h e c o n d i t i o n s of cont i n u i t y and e q u i l i b r i u m a t t h e i n t e r s e c t i o n s of t h e s h e l l segment and
beams.
The r e s u l t i s a s e t of d i f f e r e n t e q u a t i o n s i n terms of t h e
d e f l e c t i o n s and r o t a t i o n s of t h e s t i f f e n e r c e n t r o i d a l a x i s . The p e r t i n e n t s o l u t i o n s t o t h i s s e t of e q u a t i o n s y i e l d f o u r a l g e b r a i c e q u a t i o n s
(DDS/NO
t h~
c o n t a i n i n g t h e frequency of v i b r a t i o n a s a parameter
Carolina S t a t e University)
.
�b. A t e c h n i c a l r e p o r t e n t i t l e d "A Comparison of F l e x i b l e
and Rigid Ring B a f f l e s f o r S l o s h Suppression" has been published. The
included t e s t r e s u l t s i n d i c a t e that f l e x i b l e b a f f l e s g e n e r a l l y p r o v i d e
damping e q u a l t o o r b e t t e r than s i m i l a r r i g i d b a f f l e s , The r a t i o of
f l e x i b l e b a f f l e damping t o r i g i d b a f f l e damping i s shown t o v a r y from
approximately 2 t o s l i g h t l y g r e a t e r than 1 a s a f u n c t i o n of s l o s h
amplitude.
The r a t i o i s l a r g e s t f o r low amplitudes. These r e s u l t s
a g r e e v e r y w e l l w i t h d a t a p r e v i o u s l y published by Langley.
southwest
Research I n s t i t u t e )
c.
Nonlinear F i l t e r f o r High Frequency Cutoff
The f i n a l r e p o r t , "The Nonlinear Cutoff F i l t e r i n
t h e S a t u r n V Vehicle w i t h Time Varying C o e f f i c i e n t s ," August 1966, LMSC/
HREC A783123, has been d i s t r i b u t e d . This r e p o r t summarizes t h e r e s u l t s
of a n a n a l o g s i m u l a t i o n of t h e S a t u r n V w i t h time v a r y i n g c o e f f i c i e n t s ,
f l e x i b l e dynamics and t h e n o n l i n e a r f i l t e r over t h e b o o s t e r p o r t i o n of
f l i g h t . The system was s u b j e c t e d t o programmed s t e p s i n a t t i t u d e ,
v a r i a b l e wind d i s t u r b a n c e s , and a d v e r s e bending mode c o n d i t i o n s . I n
a l l c a s e s , v e r y s a t i s f a c t o r y performance was achieved, and t h e n o n l i n e a r
f i l t e r provided system s t a b i l i t y w i t h extreme changes i n t h e bending
c h a r a c t e r i s t i c s , f o r example, s i g n r e v e r s a l i n bending mode s l o p e s .
For comparison purposes, s i m u l a t i o n s were a l s o conducted w i t h t h e
AS tr i o n i c " des igned 1i n e a r f il t e r i n t h e loop.
(~~A/~ockheed)
B.
Saturn V
1.
Mission P r o f i l e
- AS-504
I g n i t i o n Time E r r o r s f o r Fixed f3
A s t u d y i s i n p r o g r e s s t o determine i f t h e t a r g e t i n g
parameter p ( a n g l e from i g n i t i o n t o t h e nodal c r o s s i n g of i g n i t i o n p l a n e
and t r a n s l u n a r p l a n e ) i s a c o n s t a n t mission-dependent i n p u t . A launch
azimuth s p r e a d of 7 2
108 degrees i s considered w i t h i n j e c t i o n s f o r t h e
f i r s t and second o p p o r t u n i t i e s . P r e l i m i n a r y i n d i c a t i o n s a r e t h a t t h e
a n g l e f3 h o l d s c o n s t a n t throughout t h e range o f azimuths, b u t a s l i g h t
e r r o r is induced when u s i n g t h e same f3, d e r i v e d from a f i r s t o p p o r t u n i t y
l a u n c h , f o r a second o p p o r t u n i t y i n j e c t i o n .
Second o p p o r t u n i t y i n j e c t i o n
time v a r i a t i o n s due t o t h e c o n s t a n t p average 20 seconds which r e s u l t i n
18 km m i s s - d i s t a n c e a t t h e moon. Midcourse c o r r e c t i o n AV requirements
a r e b e i n g determined f o r t h e s e e r r o r s . I n d i c a t i o n s a r e t h a t a c o n s t a n t
may be added t o t h e f i r s t o p p o r t u n i t y f3 t o update the a n g l e f o r u s e i n
(DA~/~oeing)
second o p p o r t u n i t y s i t u a t i o n s
-
.
�2.
P r o j e c t I n f o r m a t i o n A p p l i c a b l e t o Many V e h i c l e s
S a t u r n V C u r r e n t Performance
S a t u r n V performance b a s e d upon August 1966 c u r r e n t
v e h i c l e w e i g h t and performance d a t a was computed and t r a n s m i t t e d t o
I n d u s t r i a l O p e r a t i o n s . Payload i n c r e a s e s of a p p r o x i m a t e l y 600 pounds
o v e r t h e p r e v i o u s month o c c u r f o r v e h i c l e s SA-501 and SA-501 and SA-502.
T h i s i n c r e a s e i n performance i s t h e r e s u l t o f u p r a t e d S - I 1 and S-IVB
p r o p u l s i o n p e r f o r m a n c e . The S - I 1 and S-IVB p r o p u l s i o n d a t a f o r t h e
SA-501 and SA-502 v e h i c l e s a r e based on a c c e p t a n c e d a t a . Payload
d e c r e a s e s o f a p p r o x i m a t e l y 1000 pounds i n t h e SA-503 and 600 pounds i n
SA-504 and s u b s e q u e n t v e h i c l e s a r e i n d i c a t e d .
These payload changes
a r e p r i m a r i l y due t o t h e u p d a t e d upper s t a g e p r o p u l s i o n systems and
increases i n the vehicles stage i n e r t weights.
(DAPIBoeing)
C.
Saturn I B
1.
Mission P r o f i l e
AS-208 Guidance R e f e r e n c e R e l e a s e C o r r e c t i o n F u n c t i o n
The method proposed f o r t h e AS-2071 208 rendezvous
m i s s i o n r e q u i r e s t h e 208 v e h i c l e t o b e launched a t s u c h a t i m e t h a t ,
when o r b i t a l i n s e r t i o n o c c u r s , i t w i l l b e a g i v e n c e n t r a l r a n g e a n g l e
a h e a d of t h e AS-207 v e h i c l e ( w i t h i n t h e i n f l i g h t d i s p e r s i o n s ) .
To
maintain t h i s range a n g l e , the guidance r e f e r e n c e r e l e a s e time, and,
t h e r e f o r e , t h e l i f t o f f time must b e changed t o compensate f o r f l i g h t
t i m e v a r i a t i o n s and a s s o c i a t e d downrange d i s p e r s i o n s caused by changes
i n t h e t a r g e t p a r a m e t e r s from t h e planned o r nominal v a l u e s . The problem
o f d e t e r m i n i n g t h e new g u i d a n c e r e f e r e n c e r e l e a s e time on s h o r t n o t i c e
h a s b e e n s o l v e d and g i v e s a n a c c u r a c y w i t h 0.1 s e c o n d s . The d e t a i l s o f
how t h i s s o l u t i o n was r e a c h e d h a v e b e e n documented i n O f f i c e Memorandum
R-AERO-DAG-33-66.
2.
U p r a t e d S a t u r n I C u r r e n t Performance
Uprated S a t u r n I performance c a p a b i l i t y based upon
September 1966 c u r r e n t v e h i c l e w e i g h t and performance d a t a was computed
and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . Because o f w e i g h t c h a n g e s ,
t h e p a y l o a d c a p a b i l i t i e s o f v e h i c l e s SA-205 t h r o u g h SA-208 changed
1-35, -102, -18, and -10 pounds, r e s p e c t i v e l y . A l l v e h i c l e s i n c u r r e d
a 16-pound i n c r e a s e i n payload due t o a r e v i s i o n i n b a s e d r a g p r e d i c t i o n .
AS-207 p a y l o a d d e c r e a s e d 7 0 pounds a s a r e s u l t o f a m i s s i o n r e d e f i n i t i o n
(change i n i n j e c t i o n a l t i t u d e from 1 0 0 n.m. c i r c u l a r o r b i t ) . ( D ~ P / C h r y s l e r )
�3.
P r o j e c t Information Applicable t o I n d i v i d u a l Vehicles
AS-208: A l l a n a l y s e s have been completed t o provide
anL/V Reference T r a j e c t o r y r e f l e c t i n g t h e f i r s t o p p o r t u n i t y f o r AS-208
launch t o rendezvous w i t h AS-207.
The r e p o r t documenting t h i s s t u d y
should be submitted t o Chrysler r e p r o d u c t i o n on September 30, 1966.
The L/V T a r g e t i n g O b j e c t i v e s Proposal document has
been r e v i s e d and r e i s s u e d .
Based on t h e L/V Reference T r a j e c t o r y , work has been
i n i t i a t e d on " P r e l i m i n a r y Abort and Engine-Out S t u d i e s ," and "Launch
(DAPIChrysler)
V e h i c l e Performance Analysis."
D.
AAP
1.
Mission P r o f i l e
a.
Electromagnetic Radiation S a t e l l i t e
Data showing t h e v i s i b i l i t y times of c e r t a i n s t a r s
t o a v e h i c l e i n o r b i t a b o u t t h e e a r t h have been determined. A s t u d y
has a l s o been conducted t o determine what s t a r s would be v i s i b l e t o
t h e X-ray and photographic equipment w h i l e c e r t a i n s t a r s a r e being
observed w i t h t h e gamma-ray equipment. Analysis of t h e d a t a and
documentation a r e i n p r o g r e s s .
(DAP)
b.
Solar Pressure Perturbations
A computer r o u t i n e has been w r i t t e n and implemented
t o c o n t r o l t h e o r i e n t a t i o n of a s a t e l l i t e i n a twelve-hour e q u a t o r i a l
o r b i t i n s u c h a way a s t o e l i m i n a t e i n c l i n a t i o n changes. This i s done
by c a n c e l l i n g o u t t h e accumulated change every o t h e r o r b i t . During
t h e c a n c e l l i n g o r b i t s , t h e component of t h e s o l a r p r e s s u r e f o r c e normal
t o t h e o r b i t p l a n e i s made e q u a l b u t o p p o s i t e t o t h a t which i s experienced
w i t h t h e nominal o r i e n t a t i o n .
(DAP)
c.
ATM S o l a r E c l i p s e Observation
A b r i e f s t u d y i s being made t o determine a n o r b i t
which w i l l g i v e simultaneous o b s e r v a t i o n w i t h a ground s t a t i o n of t h e
1970 t o t a l e c l i p s e of t h e sun. The d u r a t i o n of t h e e c l i p s e vs apogee
r a d i u s has been c a l c u l a t e d . Other o r b i t a l parameters a r e now being
(DAP)
cons i d e r e d
.
�2.
Dynamics and Control
a.
Low g S l o s h S t u d i e s
A r e p o r t proposing t o perform low g s l o s h s t u d i e s i n
a r o t a t i n g cable-connected S-IVB, SLA combination has been submitted.
The s l o s h experiment packages a r e l o c a t e d i n t h e SLAY and a c c e l e r a t i o n
l e v e l s a r e v a r i e d by v a r y i n g t h e l e n g t h of t h e c a b l e . Some t y p i c a l
parameters of t h e proposed experiment a r e l i s t e d below:
Acceleration
0.00036 t o 0.0068 g ' s
TankDiameter
6and 12in.
Bond Number
.67 t o 55.
A primary advantage of t h e proposed r o t a t i n g s t a t i o n
over n o n r o t a t i n g s t a t i o n s i s t h e a b i l i t y t o measure any d e s i r e d number
of c y c l e s of o s c i l l a t i o n w i t h o u t p r o p e l l a n t consumption. Measurement t o
t h e dynamic p r o p e r t i e s of t h e r o t a t i n g , cable-connected c o n f i g u r a t i o n i s
a l s o proposed.
(DDS)
b.
F e a s i b i l i t y of Providing A r i t i f i c i a l G r a v i t y f o r Crew
i n ATM/Orb i t a l Workshop
The f e a s i b i l i t y of g e n e r a t i n g a r t i f i c i a l g r a v i t y f o r
t h e A T ~ / O r b i t a lWorkshop by s p i n n i n g t h e c o n f i g u r a t i o n a b o u t i t s t e t h e r
rod was i n v e s t i g a t e d . Without s p i n n i n g , t h e t e t h e r rod i s a1 igned a l o n g
the l o c a l v e r t i c a l , but i f a s p i n r a t e i s applied about the t e t h e r a x i s
t h e c o n f i g u r a t i o n becomes u n s t a b l e . T h e r e f o r e , i t i s n e c e s s a r y t o
r e o r i e n t the configuration such t h a t the s p i n a x i s i s perpendicular t o
the o r b i t a l plane.
Such a c o n f i g u r a t i o n was i n v e s t i g a t e d w i t h a s p i n
r a t e a p p l i e d t o produce a b o u t 116 g i n t h e crew compartment.
It was concluded t h a t a r t i f i c i a l g r a v i t y i s f e a s i b l e i f
(1) r e o r i e n t a t i o n of t h e c o n f i g u r a t i o n i s p o s s i b l e w i t h regard t o gimbal
and v i s i b i l i t y requirements f o r s o l a r d a t a r e c o v e r y , ( 2 ) f l e x u r a l s t a b i l i t y
q u e s t i o n s of t h e boom a r i s i n g from misalignment and s h i f t s of c e n t e r of
mass l o c a t i o n s can be r e s o l v e d , and ( 3 ) p h y s i o l o g i c a l e f f e c t s on a s t r o n a u t s due t o a d v e r s e C o r i o l i s f o r c e s a r e a c c e p t e d .
c.
O r b i t i n g M i r r o r Sumulation
The
i s r e f l e c t i n g a beam
s t u d i e d . .The m i r r o r
t h e d i s t a n c e between
problem of c o n t r o l l i n g a l a r g e o r b i t i n g m i r r o r t h a t
of l i g h t t o a f i x e d p o i n t on t h e e a r t h i s s t i l l being
i s c o n t r o l l e d by v a r y i n g i t s c e n t e r of mass t o a l t e r
t h e c e n t e r of p r e s s u r e and mass such t h a t r a d i a t i o n
�p r e s s u r e and g r a v i t y t o r q u e s a r e used t o c o n t r o l t h e system's a t t i t u d e
and r a t e . A l i n e a r combination of s t a t e v a r i a b l e s i s used a s a c o n t r o l
law, w i t h a c o s i n e f u n c t i o n modifying t h e c e n t e r of mass displacement
command s i g n a l . L i m i t i n g v a l u e s were placed on t h e mass displacement
and r a t e of change s o t h a t a more r e a l i s t i c model was obtained f o r
s i m u l a t i o n . S e v e r a l o t h e r minor m o d i f i c a t i o n s were made t o t h e d i g i t a l
program t o c o r r e c t f o r moment of i n e r t i a v a r i a t i o n s , c e n t e r of l i g h t
p r e s s u r e change, and e c c e n t r i c i t y of o r b i t .
A systematic search f o r control l a w gains t h a t give
s m a l l displacements and a c c e l e r a t i o n s i s b e i n g pursued. I n i t i a l runs
i n d i c a t e t h a t s u i t a b l e s t a b i l i t y and c o n t r o l can be o b t a i n e d w i t h
a p p r o p r i a t e choice of c o n t r o l g a i n s . A t p r e s e n t t h e p o i n t i n g a c c u r a c y
o b t a i n e d g i v e s a maximum d e v i a t i o n of 100 k i l o m e t e r s a b o u t a f i x e d p o i n t
on e a r t h . Maximum v a l u e s a r e o b t a i n e d i n morning and evening. F u r t h e r
s i m u l a t i o n is expected t o c o r r e c t t h i s e r r o r t o perhaps 1 0 p e r c e n t of
t h e above v a l u e . The p r e s e n t p o i n t i n g a c c u r a c y is l i m i t e d by t h e maximum
c e n t e r of mass r a t e of change (about one meter per minute) that i s being
a 1 lowed.
(DCA)
d.
C y l i n d r i c a l Payload Module S e p a r a t i o n
A memorandum p r e s e n t i n g t h e r e s u l t s of t h e RAcK/CPM
s e p a r a t i o n s t u d y h a s been d i s t r i b u t e d . R-P&VE-VAW has announced t h a t
t h e moments of i n e r t i a they s u p p l i e d f o r t h e s t u d y were i n e r r o r by a
f a c t o r of a p p r o x i m a t e l y two. S i n c e t h e moments of i n e r t i a a r e a c t u a l l y
l a r g e r t h a n t h o s e used i n t h e s t u d y , 'the d r i f t problem w i l l be a l l e v i a t e d
t o t h e e x t e n t t h a t a n a t t i t u d e maneuver d u r i n g t h e e x t r a c t i o n of t h e CPM
from t h e RACK probably w i l l n o t be r e q u i r e d . The s t u d y w i l l be redone
us i n g t h e c o r r e c t d a t a
(DC)
.
E.
General
1.
6-D Response Program
The 6-D d i g i t a l response program has been modified t o
i n c l u d e m a l f u n c t i o n s s u c h as engine o u t . Problems have occurred i n
s i m u l a t i n g t h e p r e s e n t 5-D c o n t r o l system because of h i g h frequency
components i n t h e f i l t e r s . The problem has been by-passed w i t h s l i g h t
m o d i f i c a t i o n i n t h e t r a n s f e r f u n c t i o n s of t h e f i l t e r s .
(DDD)
2.
NASA I n t e r c e n t e r Meeting on Control Theory
A d i s c u s s i o n on "Research i n C o n t r o l ~ e s i g n "was presented
a t t h e I n t e r c e n t e r C o n t r o l Conference. The p r e s e n t a t i o n c e n t e r e d a b o u t
t h e a u t o m a t i c g a i n and f i l t e r s y n t h e s i s program. A d e s c r i p t i o n of t h e
d e s i g n procedure a l o n g w i t h some of t h e d a t a o b t a i n e d from s e v e r a l checko u t c a s e s was p r e s e n t e d . A s y e t no d e f i n i t e d e c i s i o n can be made
35
�concerning t h e u t i l i t y of t h e procedure a s a p r a c t i c a l s y n t h e s i s t o o l .
S i n c e a c e r t a i n amount of e n g i n e e r i n g judgement and i n t u i t i o n i s necessary
t o p r o p e r l y s e l e c t f i l t e r p o l e s , t h e procedure i s n o t f u l l y a u t o m a t i c i n
i t s p r e s e n t form.
(DCA)
3.
Reduction of Bending Moment v i a Modern Control Techniques
A s t u d y has been completed i n which modern c o n t r o l techniques were a p p l i e d i n t h e d e s i g n of a load r e l i e f c o n t r o l l e r f o r t h e
S a t u r n type v e h i c l e . The s t u d y r e s u l t s a r e summarized i n t h e following
reports :
(1)
"The A p p l i c a t i o n of a n Algorithm f o r Optimization
of Nonlinear Control Problems t o a Minimax Bending
A782451, March 1966, by
Moment Study," LMSC/HREC
J. F. S o h l e r .
(2)
"Synthesis of a n Optimal Load R e l i e f Control
System," LMSC~HRECA782527, March 1966, by J . N.
Dashiell.
(3)
"Optimal C o n t r o l System t o Minimize t h e I n t e g r a l
of Bending Moment Squared w i t h a Terminal S t a t e
Weighting Condition," LMSC/HREC A783130, J u l y 1966,
by J. N. D a s h i e l l .
I n each r e p o r t a c o s t f u n c t i o n i s d e f i n e d which e x p r e s s e s
v e h i c l e s t r u c t u r a l l o a d i n g and t e r m i n a l d r i f t , and t h e system e q u a t i o n s
a r e f o r m u l a t e d i n t h e s t a t e space n o t a t i o n w i t h t h e n t h o r d e r systems
b e i n g d e s c r i b e d by "n" f i r s t o r d e r d i f f e r e n t i a l e q u a t i o n s . Then t h e
minimizing c o n t r o l l e r i s s y n t h e s i z e d by d i g i t a l l y s o l v i n g e i t h e r a twop o i n t boundary v a l u e problem o r t h e M a t r i x R i c c a t i d i f f e r e n t i a l e q u a t i o n .
I n t h e f i r s t r e p o r t t h e d e r i v e d c o n t r o l was n o n l i n e a r i n t h e s t a t e v a r i a b l e s
and minimized t h e maximum d r i f t r a t e f o r the r i g i d body system. I n t h e
second r e p o r t a l o a d r e l i e f c o n t r o l l e r f o r t h e v e h i c l e w i t h f l e x i b l e
dynamics was s y n t h e s i z e d , b u t no a t t e m p t was made t o minimize t e r m i n a l
d r i f t . However, i n t h e t h i r d r e p o r t a c o n t r o l l e r was s y n t h e s i z e d t o
minimize b o t h i n - f l i g h t s t r u c t u r a l l o a d i n g and t h e t e r m i n a l d r i f t .
Reports 2 and 3 formed t h e b a s i s f o r a p r e s e n t a t i o n a t t h e
MSFC C o n t r o l Theory Symposium, September 19-21, 1966. The p l a n t f o r
t h e s t u d i e s , Model Vehicle I1 w i t h time .varying c o e f f i c i e n t s over t h e
b o o s t phase of f l i g h t , was d i s t u r b e d by t h e MSFC d e s i g n wind p r o f i l e .
These s t u d i e s i n d i c a t e t h a t modern c o n t r o l techniques can be used a s
a c o n t r o l l e r d e s i g n procedure which can produce a system w i t h d e s i r a b l e
c h a r a c t e r i s t i c s i n b o t h load r e l i e f and t e r m i n a l d r i f t . However, t h e
more d e s i r a b l e r e s u l t s could o n l y be obtained w i t h a knowledge of t h e
e x a c t wind p r o f i l e .
�These s t u d i e s i n d i c a t e d that, i f t h e wind d i s t u r b a n c e could
b e known b e f o r e l a u n c h , then a b i a s s i g n a l could be added t o t h e feedback s i g n a l t o g r e a t l y reduce v e h i c l e s t r u c t u r a l l o a d s and m a i n t a i n
However, any s i g n i f i c a n t d e v i a t i o n from
terminal d r i f t specifications
t h e d e s i g n wind from which t h e c o n t r o l law was based y i e l d s n e g a t i v e
r e s u l t s i n v e h i c l e performance. S i n c e wind s t a t i s t i c s a r e of random
n a t u r e , t h e f u t u r e of t h i s type approach w i t h o u t any method of d i s t u r b a n c e
p r e d i c t i o n appears limited.
(~CA/Lockheed)
.
VIII.
FLIGHT TEST ANALYSIS DIVISION
A.
Special Projects Office
The AS-202 f l i g h t e v a l u a t i o n has been l a r g e l y completed.
I n d i c a t i o n s a r e t h a t a v e r y s a t i s f a c t o r y f l i g h t t e s t was o b t a i n e d and
t h a t t h e e i g h t f l i g h t anomalies and performance d e v i a t i o n s r e v e a l e d had
no e f f e c t on t h e accomplishment of m i s s i o n o b j e c t i v e s . These anomalies
and d e v i a t i o n s can b e sunnnarized a s f o l l o w s :
1.
Timing f a i l u r e s were experineced by 24 p e r c e n t of
t h e e n g i n e e r i n g s e q u e n t i a l cameras r e s u l t i n g i n s e r i o u s
impairment of f i l m q u a l i t y .
2.
One of two redundant onboard cameras viewing S-IBIS-IVB
s e p a r a t i o n was n o t recovered. A camera mounted i n t h e
same v e h i c l e p o s i t i o n was l o s t on t h e two previous
S a t u r n I B f l i g h t s . The p o s s i b i l i t y of boos t e r l c a m e r a
f r e e - f l i g h t t r a j e c t o r y i n t e r s e c t i o n i s being i n v e s t i g a t e d .
3.
One of f o u r r e t r o - r o c k e t motors on t h e S-IBIS-IVB i n t e r s t a g e e x h i b i t e d abnormal burning c h a r a c t e r i s t i c s , which
i s considered t o b e a random performance d e v i a t i o n .
4.
The S-IVB LH2 r e c i r c u l a t i o n s h u t o f f c o n t r o l v a l v e f a i l e d
t o c l o s e a s p r o g r a m e d . This m a l f u n c t i o n a l s o occurred
on AS-203.
5.
A 1.4 m / s c r o s s range e r r o r b i a s was accumulated by t h e
guidance s y s tem s h o r t l y a f t e r l i f t o £ f. This d e v i a t i o n
was probably due t o s a t u r a t i o n of s e r v o e r r o r s i g n a l s
caused by i n i t i a l v e h i c l e v i b r a t i o n e f f e c t on t h e
ST-124M p l a t f o r m a c c e l e r o m e t e r s .
6.
A t s p a c e c r a f t / b o o s t e r s e p a r a t i o n , t h e s e p a r a t e d S-IV%/IU
experienced SPS plume impingement caused by t h e i g n i t i o n
sequence o c c u r r i n g t o o soon a f t e r LV/SC s e p a r a t i o n .
�B.
7.
A probable s h o r t c i r c u i t on t h e o u t p u t s i d e of t h e
Q-ball s e r i e s trans i s t o r regulator c i r c u i t resulted
i n Q-ball f a i l u r e a f t e r 93.6 seconds of f l i g h t .
8.
The S-IVB LOX chilldown pump motor c o n t a i n e r experienced
a l o s s of p r e s s u r e d u r i n g countdown which was probably
caused by a s e a l leakage.
F l i g h t E v a l u a t i o n Branch
1.
S a t u r n I.B
a.
AS-202 Guidance Analysis
GLOTRAC d a t a have been r e c e i v e d f o r t h e AS-202 f l i g h t .
Comparisons w i t h guidance d a t a i n d i c a t e t h a t t h e p o s t f l i g h t t r a j e c t o r y
and GLOTRAC a r e i n good agreement u n t i l a b o u t 420 seconds where GLOTRAC
i s l o s t f o r a b o u t 50 seconds. The v e l o c i t y d i f f e r e n c e s between b o t h
GLOTMC and t h e r e f e r e n c e t r a j e c t o r y i n d i c a t e t h a t the t o t a l guidance
e r r o r s a r e w e l l w i t h i n t h e 3-0 t o l e r a n c e .
The problem i n reducing t h e guidance a c c e l e r o m e t e r
d a t a has n o t been c o r r e c t e d . Hopefully, a programmer w i l l be o b t a i n e d
i n t h e n e a r f u t u r e t o look i n t o t h e d a t a r e d u c t i o n program t o e l i m i n a t e
t h e t r o u b l e . The guidance v e l o c i t i e s f o r AS-203 and AS-202 were Lagrange
i n t e r p o l a t i o n s of t h e guidance computer o u t p u t s .
(1 )
Separation
A s p e c i a l meeting of t h e l e v e l I1 c o n f i g u r a t i o n
c o n t r o l board was h e l d on September 19. The purpose of t h e meeting was
t o determine t h e a d v i s a b i l i t y of extending t h e time from outboard engine
c u t o f f (OECO) t o s e p a r a t i o n s i g n a l by .5 second i n o r d e r t o i n c r e a s e
t h e p r o b a b i l i t y of s u c c e s s f u l s e p a r a t i o n i n t h e e v e n t t h a t a r e t r o r o c k e t f a i l e d t o i g n i t e . A n a n a l y s i s performed by CCSD on t h e AS-204
con£ i g u r a t i o n i n d i c a t e s t h a t t h e change w i l l i n c r e a s e t h e p r o b a b i l i t y
of s u c c e s s f u l s e p a r a t i o n ( r e t r o - o u t ) from approximately 17 t o 95 p e r c e n t .
The meeting r e s u l t e d i n a d e c i s i o n t o implement t h i s sequence change on
AS-204 and subs.
(2)
Wind Limits
I n f l i g h t wind l i m i t s f o r t h e AS-204 launch v e h i c l e
have been e s t a b l i s h e d f o r t h e 5 t o 15 km a l t i t u d e range, based on t h e
s t r u c t u r a l c a p a b i l i t i e s of t h e launch v e h i c l e p r e s e n t e d i n Memorandum
R-P&VE-SJ-66-183, " S t r u c t u r a l Limits f o r Uprated S a t u r n I, AS-204,"
�August 23, 1966. These l i m i t s a r e p r e s e n t e d i n terms of a n g l e of a t t a c k ,
gimbal a n g l e , Mach number and dynamic p r e s s u r e . The e f f e c t s of 99 perc e n t s h e a r s and g u s t and 3-0, C, and C2 v a r i a t i o n s were used t o e s t a b l i s h
t h e s e wind l i m i t s . These d i s t u r b a n c e s were a l l combined i n t h e "worst"
way t o e s t a b l i s h t h e peak wind l i m i t a s measured by t h e FPS-16I~imsphere
system. A t t h e most c r i t i c a l a l t i t u d e (12 km), t h e v e h i c l e i s windl i m i t e d t o 62, 96, and 66 m/sec f o r a head, t a i l , and c r o s s wind,
r e s p e c t i v e l y . These r e s u l t s , a s w e l l a s s u r f a c e wind r e s t r i c t i o n s , a r e
i n c l u d e d i n Memorandum R-AERO-FF-42-66, "Wind Launch C r i t e r i a f o r AS- 204,"
September 7 , 1966.
(3)
Emergency D e t e c t i o n
A document, 66-FMP-16, "Emergency D e t e c t i o n System
(EDS) and F l i g h t Dynamics Limits," August 15, 1966, c o n t a i n i n g t h e recommended l i m i t s e t t i n g s and a d i s c u s s i o n of t h e f a i l u r e modes f o r v a r i o u s
f 1i g h t p e r i o d s has been pub1 ished.
2.
Contracts
a.
S a t u r n I B Sys tems C o n t r a c t (CCSD, New Orleans)
CCSD w i l l assume r e s p o n s i b i l i t y f o r e s t a b l i s h i n g t h e
i n t e r m e d i a t e (7-day) and f i n a l (14-day) t r a j e c t o r i e s on S a t u r n IB v e h i c l e
beginning w i t h AS-204.
To s e e i f CCSD had t h e c a p a b i l i t y , i t was
decided f o r them t o perform t h i s t a s k on AS-202 a s i f i t were t h e i r
r e s p o n s i b i l i t y . CCSD s a t i s f a c t o r i l y e s t a b l i s h e d t h e s e t r a j e c t o r i e s on
AS-202 i n a t i m e l y manner.
To e s t a b l i s h t h e t r a j e c t o r y r a d a r d a t a from
7 d i f f e r e n t s t a t i o n s , ODOP and GLOTUC S t a t i o n I d a t a were a v a i l a b l e .
The f i n a l GLOTUC PVA d a t a were n o t r e c e i v e d i n time t o b e used i n
e s t a b l i s h i n g t h e f i n a l t r a j e c t o r y , b u t i t d i d v e r i f y t h e a c c u r a c y of
t h e t r a j e c t o r y . I n summary, CCSD proved themselves f u l l y capable and
prepared t o assume t h i s r e s p o n s i b i l i t y on t h e remaining S a t u r n IB v e h i c l e s .
c.
S a t u r n V Sys tems C o n t r a c t (TBC)
The Boeing Company was scheduled t o assume a l l t h e p o s t f l i g h t t r a j e c t o r y r e s p o n s i b i l i t i e s on t h e S a t u r n V v e h i c l e beginning
It has now been decided t h a t , because of u n c e r t a i n d a t a
w i t h AS-504.
d e l i v e r y s c h e d u l e s and o t h e r c o n s i d e r a t i o n s , t h e r e s p o n s i b i l i t y f o r t h e
p r e l i m i n a r y (48-hour) t r a j e c t o r y w i l l remain inhouse. TBC i s p r e p a r i n g
t o assume t h e r e s p o n s i b i l i t y f o r t h e e s t a b l i s h m e n t of t h e i n t e r m e d i a t e
(7-day) and f i n a l (14-day) t r a j e c t o r y .
Copies of some of t h e computer
programs now used by MSFC have been d e l i v e r e d t o TBC, who is developing
t h e remainder of t h e programs r e q u i r e d . I n some a r e a s , such a s d a t a
e d i t i n g and f i l t e r i n g , TBC has s u f f i c i e n t c a p a b i l i t y , w h i l e i n most of t h e
remaining a r e a s , t h e y have no proven c a p a b i l i t y . For TBC t o do a
p a r a l l e l e f f o r t beginning on AS-501, c o n s i d e r a b l e work i n most a r e a s is
necessary.
�C.
F l i g h t Mechanics Branch
1.
Saturn I B
The o p e r a t i o n a l t r a j e c t o r y r e p o r t was d i s t r i b u t e d on
September 30 w i t h a n addendum r e f l e c t i n g t h e change i n t h e S-IBIS-IVB
s e p a r a t i o n sequence.
P a r t s of t h e d i s p e r s i o n a n a l y s i s have been r e c e i v e d
from CCSD.
The f i n a l d a t a a r e a v a i l a b l e t o
t r a j e c t o r y . The S-IB t i l t program and S-IVB IGM
have been completed. The S a t u r n I B "block-type"
(based on 205 d a t a ) has been documented i n Range
5-66, d a t e d August 26, 1966.
generate the operational
guidance p r e s e t t i n g s
range s a f e t y r e p o r t
S a f e t y Data Report No.
The p r e l i m i n a r y range s a f e t y a n a l y s i s has been documented i n Range S a f e t y Data Report No. 6-66, d a t e d August 26, 1966.
A t t h e August 30, 1966 " t a s k team" meeting, t h e symbols
and u n i t s f o r t h e t a r g e t i n g parameters were agreed on. The minutes of
t h e meeting a r e documented i n a memo "Minutes of 20718 J o i n t T a r g e t i n g
Meeting h e l d on August 30, 1966," dated September 2, 1966.
2.
Saturn V
(1) An e r r a t a s h e e t prepared by R-AERO-FMT on t h e
AS-501 o p e r a t i o n a l t r a j e c t o r y r e p o r t has been g i v e n t o TBC, who i s
supposedto s u p p l y R-AERO-FMT w i t h a n o f f i c i a l e r r a t a s h e e t from t h e i r
shop t o d i s t r i b u t e w i t h t h e i r o p e r a t i o n a l t r a j e c t o r y r e p o r t .
(2) The f i n a l AS-501 range s a f e t y document has been
n e g o t i a t e d w i t h TBC, R-AERO-FMT, and t h e P r o j e c t O f f i c e . It was r e s o l v e d
t h a t TBC would c o r r e c t t h e i r AS-501 range s a f e t y document t o i n c o r p o r a t e
r e v i s e d 3-0 maximum and minimum cases. This document i s now due on
October 14, 1966. It was a l s o agreed t h a t t h e AS-503 p r e l i m i n a r y range
s a f e t y document would r e f l e c t t h e 3-0 maximum and minimum c a s e s . The
due d a t e f o r t h i s r e p o r t was changed t o November 10, 1966.
�(3) R-AERO-FMT i s s t i l l a w a i t i n g t h e AS-501 guidance
presettings.
The f i n a l c o p i e s a r e expected by September 30, 1966.
These w i l l b e forwarded t o R-ASTR-NG a s soon a s we g e t them.
3.
General
The in-house open loop MARVES i s almost complete except
A d e t a i l e d check w i t h t h e
f o r a problem w i t h p r o p u l s i o n t a p e look-up.
open loop B-2 i s b e i n g made t o a s s u r e a complete MARVES s i m u l a t i o n ,
which h a s been slowed because of l a r g e r e v i s i o n s of t h e IBM flow
diagrams.
The l o g i c , however, has been programmed and should be
checked o u t soon.
D.
Tracking and O r b i t a l Analysis Branch
1. The aerodynamic f o r c e s a c t i n g on t h e o r b i t i n g AS-204 payload were f u r n i s h e d t o M r . Marcus Meadows of CCSD, who provides s u p p o r t
t o R-PSrVE-PT.
2. Aerodynamic f o r c e s and a c c e l e r a t i o n s on t h e S-IVB/LM/CSM
con£ i g u r a t i o n f o r P r o j e c t Thermo were f u r n i s h e d t o M r . Nathan, R-AERO-T,
f o r o r b i t a l a l t i t u d e s of 125, 150, 175, and 200 n.m.
Aerodynamic drag
c o e f f i c i e n t s were r e c e i v e d from R-AERO-A f o r t h i s con£ i g u r a t i o n .
3. A memorandum, R-AERO-FT-33-66, e s t a b 1 i s h i n g optimal o r b i t a l
azimuths f o r t h e proposed Multiband Camera Experiment, assuming Weslaco,
Texas, a s a t a r g e t s i t e , has been d i s t r i b u t e d .
4 . The p r e d i c t e d l i f e t i m e of t h e o r b i t i n g AS-204 S-IVB has
been d i s t r i b u t e d i n Memorandum R-AERO-FT-35-66.
5. V a r i a t i o n s i n t h e o r b i t a l plane of SA-lO/Pegasus C and t h e
p r e d i c t e d l i f e t i m e of SA-10 have been f u r n i s h e d t o D r . G. Anderson of
Bellcam.
This i n f o r m a t i o n , r e q u e s t e d t o f u r t h e r p l a n t h e Pegasus C
rendezvous m i s s i o n , was t r a n s m i t t e d by l e t t e r t o D r . Anderson on August 30,
1966.
6. A viewgraph has been s u p p l i e d t o M r . G i l l i s of R-AERO-DA
f o r a p r e s e n t a t i o n t o M r . Weidner concerning t h e 209/210/211/212/213
m i s s i o n i n t h e unmanned mode. The viewgraph p r e s e n t e d t h e l i f e t i m e of
t h e S-IVB f o r v a r i o u s c i r c u l a r a l t i t u d e s assuming t h a t t h e v e h i c l e
s t a b i l i z e s due t o t h e g r a v i t y g r a d i e n t b r o a d s i d e t o t h e d i r e c t i o n of
mot ion.
7. A j o i n t R-AERO-FT and R-ASTR-IR memorandum p r e s e n t i n g
t h e S a t u r n V/Voyager t r a c k i n g and communications c h a r a c t e r i s t i c s f o r
v a r i o u s proposed launch azimuths was d i s t r i b u t e d (R-AERO-FT-39-66).
�8. M r . R. Benson a t t e n d e d a p r e s e n t a t i o n on the rendezvous
w i t h Pegasus C and t h e coupon r e t r i e v a l from t h e meteoroid p a n e l s .
This p r e s e n t a t i o n was g i v e n t o NASA Headquarters personnel t o b e t t e r
a c q u a i n t them w i t h t h i s proposed experiment b e f o r e s u b m i t t i n g t h e
Form 1138 f o r a p p r o v a l of t h i s experiment. R-RP-P p r e s e n t e d t h e
o r b i t a l a t t i t u d e of Pegasus C and s t a t e d t h e a t t i t u d e would remain
r e l a t i v e l y t h e same w i t h t h e e x c e p t i o n that t h e f l a t s p i n would damp
t o a n o s c i l l a t i o n . M r . T e l f e r , R-AERO-DA, p r e s e n t e d performance d a t a
on AS-210, t h e proposed rendezvous v e h i c l e . M r . R. Benson p r e s e n t e d
t h e o r b i t a l l i f e t i m e of Pegasus C based on t h e l a t e s t o r b i t a l a t t i t u d e .
This r e c e n t l y a t t a i n e d a t t i t u d e p r o f i l e i n c r e a s e d t h e p r e d i c t e d o r b i t a l
l i f e t i m e by approximately 1100 days. This i n d i c a t e s t h e h i g h degree of
dependence of o r b i t a l l i f e t i m e on t h e Pegasus C o r b i t a l a t t i t u d e . Prev i o u s l i f e t i m e p r e d i c t i o n s were based on a randomly tumbling v e h i c l e .
9. An e f f o r t i s underway t o complete t h e Phase "B" s t u d y of
p r o j e c t d e f i n i t i o n f o r t h e proposed M u l t i s p h e r e S a t e l l i t e Experiment
(Odyssey I ) .
10. The a n g u l a r s e p a r a t i o n a s viewed by Bermuda and S-IVB
s t a g e s of AS-501 a f t e r S-111s-IVB s e p a r a t i o n was documented i n Memorandum
R-AERO-FT-44-66.
This i n f o r m a t i o n was p r e v i o u s l y g i v e n t o I-MO-R.
11. The Sequencing Optimization Automatic Program (SOAP) was
s u p p l i e d t o Emerson E l e c t r o n i c s of S t . Louis on September 27, 1966.
This program w i l l be used on a n Emerson c o n t r a c t t o Marshall on EVA
experiment sequencing.
IX.
ADVANCED STUDIES OFFICE
A.
F l i g h t Mechanics and Performance Analysis Group
1. A memorandum summarizing t h e performance c a p a b i l i t i e s of
s e l e c t e d c o n f i g u r a t i o n s of t h e S a t u r n V and S a t u r n I B f o r s p a c e s t a t i o n
s u p p o r t has been assembled.
2. New c o n t r o l l o g i c f o r t h e mode deck i s b e i n g developed t o
p r o v i d e g r e a t e r f l e x i b i l i t y and more r a p i d convergence i n t h e optimizat i o n of p r o p e l l a n t l o a d i n g s f o r two s t a g e v e h i c l e s .
3 . The e x i s t i n g two-dimensional r i g i d body c o n t r o l deck i s
being r e v i s e d t o meet t h e requirements imposed by t h e improved S a t u r n
The r e v i s e d program w i l l a l l o w b o t h l i q u i d and s o l i d
con£ i g u r a t i o n s .
motors t o be used i n f l i g h t s i m u l a t i o n .
�4. M r . W. D. Goldsby and M r . Ron T o e l l e v i s i t e d t h e Space
and I n f orma t i o n Sys terns D i v i s i o n of Ray theon Company t o review work
performed under c o n t r a c t NAS8-1107.
Raytheon w i l l be a t MSFC on
October 26 t o g i v e a p r e s e n t a t i o n on t h e i r p r o g r e s s and proposed f u t u r e
work.
5. M r . Don Perkinson a t t e n d e d t h e C o n t r a c t o r (GD/C) O r i e n t a t i o n
f o r a Study of Large Space S t r u c t u r e s Experiment f o r U P . R-AERO-XF has
been r e q u e s t e d by R-ASTR-A t o s u p p o r t t h e m o n i t o r s h i p and assessment of
t h e r e s u l t s of c o n t r a c t NASW-1438 ( F e a s i b i l i t y Study of Space E r e c t a b l e
Antennas f o r S/AAP Experiments).
6. A p r e l i m i n a r y m i s s i o n a n a l y s i s f o r a package of exper iments proposed f o r a synchronous o r b i t m i s s i o n (510) has been i n i t i a t e d .
R-AERO-XF is working c l o s e l y w i t h R-AERO-DA and R-AERO-FT i n performing
t h e t i m e l i n e a n a l y s i s f o r which R-AERO has been g i v e n t h e l e a d .
B.
Systems Analysis Group
S a t u r n Improvement S t u d i e s
The f i n a l p r e s e n t a t i o n s of the S a t u r n Improvement S t u d i e s of
FY-65 were p r e s e n t e d by t h e c o n t r a c t o r s t o MSFC on October 3 , 4 , and 5 .
The c o n t r a c t e d e f f o r t c o n s i s t e d of two phases:
Phase I was a t r a d e
s t u d y p e r i o d l a s t i n g approximately 6-8 weeks, and Phase I1 c o n s i s t e d
of d e t a i l e d d e s i g n s t u d i e s on s e l e c t e d base1 i n e c o n f i g u r a t i o n s t h a t
evolved d u r i n g t h e t r a d e s t u d y phase.
The s t u d i e s covered b o t h t h e S a t u r n I B and S a t u r n V growth
v e r s i o n s . A S a t u r n I n t e r m e d i a t e Range of Vehicle con£ i g u r a t i o n s evolved
which cons is t e d of S a t u r n V upper s tages used i n v a r i o u s "ground launchq1
modes.
I n g e n e r a l , t h e aerodynamic c h a r a c t e r i s t i c s p r e s e n t e d by
Chrys l e r , t h e Boeing Company, and North American were " b e s t e s t i m a t e s "
based on T i t a n I11 experimental d a t a and v a r i o u s a n a l y t i c a l approximat i o n s . Advanced Systems O f f i c e and t h e s u b j e c t c o n t r a c t o r s a l l agreed
t h a t i f any of t h e s e v e h i c l e s a r e s t u d i e d i n more d e p t h i n t h e f u t u r e ,
wind t u n n e l t e s t i n g w i l l be necessary. R-AERO-AD concurred.
The unknowns r e l a t i v e t o base h e a t i n g of uprated v e h i c l e s
u s i n g s o l i d motor s t r a p - o n s have r e v e a l e d t h e need f o r base h e a t i n g
R-AERO-AT i s i n v e s t i g a t i n g t h e requirements and r e s o u r c e s
tests
a v a i l a b l e f o r such a base heating t e s t .
.
�R e p r e s e n t a t i v e s of R-AERO-AU expressed a need f o r t e s t d a t a
i n any f u t u r e in-depth s t u d i e s on c o n f i g u r a t i o n s w i t h s o l i d s t r a p - o n
motors. P a r t i c u l a r problem a r e a s a r e where shock waves from s o l i d motor
nose cones impinge upon t h e c o r e v e h i c l e .
D e t a i l e d f i n a l r e p o r t s of t h e s t u d y e f f o r t can be made a v a i l a b l e
t o interested parties.
C.
As trodynamics and Miss i o n Analysis Group
1.
Manned P l a n e t a r y Flyby Missions Based on S a t u r n / ~ p o l l o
Sys terns
The f i r s t q u a r t e r l y review of t h i s s t u d y i s scheduled t o
t a k e p l a c e i n approximately t h r e e weeks. North American A v i a t i o n , t h e
m i s s i o n s t u d y c o n t r a c t o r , has j u s t n e g o t i a t e d c o n t r a c t s w i t h AVCO and
AiResearch f o r s u b c o n t r a c t s covering s c i e n t i f i c a s p e c t s and l i f e s u p p o r t
s y s t e m s , r e s p e c t i v e l y . On October 14, NAA i s having a meeting w i t h
t h e i r s i x s c i e n t i f i c c o n s u l t a n t s t o s e l e c t s c i e n t i f i c experiments f o r
t h e manned f 1yby miss ions.
2.
R-AERO-XA i s c o o r d i n a t i n g and conducting a two t o t h r e e
month s t u d y on t h e Mars S u r f a c e Sample Return Probe (MSSR). The probe
would be launched from a manned f l y b y s p a c e c r a f t a t some time b e f o r e
a r r i v a l a t m r s . The probe a r r i v a l time would be sequenced t o a r r i v e
a t Mars ahead of t h e manned s p a c e c r a f t , descend t o t h e Martian s u r f a c e ,
o b t a i n a s u r f a c e sample, then ascend t o rendezvous w i t h t h e passing
s p a c e c r a f t . There a r e s e v e r a l major problem a r e a s a s s o c i a t e d w i t h t h i s
problem t h a t r e q u i r e i n v e s t i g a t i o n b e f o r e determining miss i o n f e a s i b i l i t y .
R e p r e s e n t a t i v e s from s e v e r a l Aero Laboratory d i s c i p l i n e s a r e p a r t i c i p a t i n g
i n t h e s t u d y i n a d d i t i o n t o personnel from R-P&VE, R-ASTR, R-RP, and
Northrop Space L a b o r a t o r i e s .
�PUBLICATIONS
1.
Dalton, Charles C., " E f f e c t s of Recent NASA-ARC Hypervelocity
Impact R e s u l t s on Meteoroid Flux and Puncture Models," NASA TM
X-53512, September 7 , 1966, U n c l a s s i f i e d .
2.
" S t a t i c Aerodynamic C h a r a c t e r i s t i c s of t h e Apollo-Saturn V Vehicles,"
TM X-53517, September 16, 1966, Vehicle Aerodynamics S e c t i o n , R-AERO-AD,
Unclass i f i e d
.
3.
Smith, Robert E. and 0. N. Vaughan, J r . , "Space Environment C r i t e r i a
G u i d e l i n e s f o r Use i n Space Vehicle Development,'%SA
TM X-53521,
September 22, 1966, U n c l a s s i f i e d .
4.
Mull i n s , L a r r y D., "Optimization of Impulsive Hohmann T r a n s f e r s
between Non-Coplanar C i r c u l a r O r b i t s , " Aero-Astrodynamics I n t e r n a l
Note 15-16, September 20, 1966, U n c l a s s i f i e d .
5.
O f f i c e Memorandum R-AERO-Y-114-66, "Cape Kennedy, F l o r i d a , January
and J u l y R e l a t i v e D e v i a t i o n s of D e n s i t i e s from t h e P a t r i c k Reference
Atmosphere, 1963 f o r S e l e c t e d P e r c e n t i l e Values from t h e S u r f a c e
t o 30 km," September 7 , 1966.
6.
O f f i c e Memorandum R-AERO-Y-108-66, "Comments on Atmospheric S t a t i s t i c s f o r Voyager," September 8 , 1966.
7.
O f f i c e Memorandum R-AERO-Y-119-66, " P r o b a b i l i t i e s of Thunderstorm
Occurrences and Associated Ground Winds a t Cape Kennedy," dated
September 26, 1966.
8.
Young, J. C . , " C r i t i c a l V e l o c i t i e s v s Wind D i r e c t i o n , " R-AERO-AU-66-81,
dated September 19, 1966.
9.
Wilhold, G. A., " F e a s i b i l i t y of Monitoring S-IVB Forward and A f t
S k i r t Panel Areas f o r Evidence of Panel F l u t t e r Phenomena,"
~-AERo-Au-66-84, September 22, 1966.
10.
Walker, R. W., "uprated Wind Tunnel Data," R-AERO-AU-66-85,
September 26, 1966.
11.
Beranek, R. G., " P r e t e s t Conference
Panel F l u t t e r T e s t y v 1R-AERO-AU-66-89,
12.
Walker, R. W . , " P r e d i c t e d F u l l - S c a l e Bending Moment f o r S a t u r n V
Empty-On-Pad C o n f i g u r a t i o n w i t h 4 112 p e r c e n t of Damping,'' R-AEROAU-66-92, September 30, 1966.
-
dated
S a t u r n S-IVB Forward S k i r t
dated September 2 1 , 1966.
�PUBLICATIONS (Continued)
13.
R-AERO-DD-57-66,
" O f f i c i a l Data f o r AS-503 C o n t r o l System Design."
14.
R-AERO-DD-62-66, " S l o s h Damping Device Requirement f o r AS-5011
S-IVB LOX Tank.''
15.
R - A E R O - D D - ~ ~ -"~C~o,r r e c t i o n of AS-502 Dynamic Data.''
16.
R - A E R ~ - D D - ~ ~ - "~S~l o, s h T e s t Requirements i n Low g Environments
."
1r
I
17.
"The Use o f Wind S h e a r s i n t h e Design of Aerospace V e h i c l e s , "
R o b e r t S. Ryan and James R. Scoggins. P r e p a r e d f o r p r e s e n t a t i o n
a t t h e 23rd Meeting o f t h e S t r u c t u r e s and M a t e r i a l s P a n e l , AGARD,
October 4, P a r i s , Franch.
18.
R-AERO-IN-DD-14-66,
"Damping P r o p e r t i e s o f Some Polymer Films f o r
Spacecraft Structures."
19.
R-AERO-DCC-14-66,
20.
R-AERO-DC-007-66, " F e a s i b i l i t y of P r o v i d i n g A r t i f i c i a l G r a v i t y
f o r Crew i n ATMIOrbital Workshop."
"RACKICPMS e p a r a t i o n Study," August 23, 1966.
R-AERO-DA-32-66, "Guidance E q u a t i o n f o r S-IVB S t a g e Second Burn
f o r SA-501 and Subsequent," September 1 2 , 1966.
R-AERO-DA-33-66, " P r e l i m i n a r y Guidance R e f e r e n c e R e l e a s e C o r r e c t i o n
F u n c t i o n f o r t h e AS-208 V e h i c l e Based on AS-207 O r b i t a l P a r a m e t e r s , "
September 1 5 , 1966.
R-AERO-DA-34-66, "Guidance A n a l y s i s f o r t h e S-V AS-502 M i s s i o n , "
September 1 6 , 1966.
R-AERO-DA-35-66, "Data Format of t h e S-IB E r r o r A n a l y s i s Beginning
w i t h t h e AS-2071208 M i s s i o n , " September 1 6 , 1966.
R-AERO-DAM-15-66, "Launch Window Study R e p o r t s f o r t h e 20718
Rendezvous Miss i o n . "
R-AERO-DAM-16-66, "Data Requested by t h e Payload I n t e g r a t i o n
C o n t r a c t o r s i n S p l i n t e r Meetings."
R-AERO-DAM-19-66,
" S a t u r n V Synchronous O r b i t . "
i
R-AERO-DAP-76-66,
"September C u r r e n t Weights
."
�PUBLICATIONS (Continued)
29.
R-AERO-DAP-77-66, "Saturn IB September 1966 Current Performance."
30.
R-AERO-DAP-78-66, "Saturn V September 1966 Performance ~eport."
31.
R-AERO-DAP-79-66, "Saturn I~/ServiceModule Performance to a 200
Nautical Mile Circular Orbit.
32.
R-AERO-DAP-80-66, "Launch Vehicle Reference Trajectory Saturn V
AS-503 Mission."
33.
R-AERO-DAP-81-66, "Verification of Data for AS-503 Performance
Analysis."
34.
R-AERO-DAP-82-66, "Saturn IB and V Inertial Guidance Platform
Realignment Study
..
R-AERO-DAP-83-66, "Saturn V Project Able."
35.
."
�AERO-ASTRODYNAMICS LABORATORY
MONTHLY PROGRESS REPORT
O c t o b e r 11, 1966
APPROVAL
Aero-As t r o d y n a m i c s L a b o r a t o r y
E . D. G e i s s l e r
D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y
DISTRIBUTION
R-AERO-D I R
Dr. G e i s s l e r
M r . Jean
R-AERO-P
(8)
R-AERO-D
(16 )
R-AERO-R
M r . B u t l e r (4)
Mrs. Hightower
R-AERO-A
(20)
R-AERO-G
(5)
R-AERO- T
Mr. M u r p h r e e
Mr. Cummings
Mr. D i c k e y
Dr. Heybey
Mr. L a v e n d e r
Mr. J a n d e b e u r
Dr. Liu
Dr. K r a u s e
M r . von P u t t k a m e r
R-AERO-Y
(5)
R-AERO-F
(8)
R-AERO-X
(2)
R-DIR,
Dr. M c C a l l
PAO, M r . K u r t z
I-V-P,
Harold P r i c e
�
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
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spc_stnv_000047
Title
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: October 11, 1966."
Creator
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George C. Marshall Space Flight Center
Date
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1966-10-11
Temporal Coverage
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1960-1969
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Saturn Project (U.S.)
NASA space programs
Project management
Type
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Progress reports
Text
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Saturn V Collection
Box 19, Folder 19
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000027_000050