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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
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.
.
I1
v
.
.
.
..
.
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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
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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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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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.......
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.
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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
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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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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_000038
Title
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"Aero-Astrodynamics Laboratory Bimonthly Progress Report: June - July 1968."
Description
An account of the resource
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.
Creator
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George C. Marshall Space Flight Center
Date
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1968-08-01
Temporal Coverage
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1960-1969
Subject
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Saturn Project (U.S.)
NASA space programs
Project management
Type
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Progress reports
Text
Source
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Saturn V Collection
Box 27, Folder 37
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