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ADVANCED ASTRIONICS
PROJECT REVIEW
IBM NO. 68-KO5-0001
30 JANUARY 1968
c
I
�PROJECT REVIEW
ADVANCED
ASTRIONICS
IRAD TECHNICAL SEMINAR
GAITHERSBURG, NLARYLAND
JANUARY 30, 1968
F. L. PUGH
PRINCIPAL INVESTIGATOR
E. C. CALDWELL
ADVANCED IU SYSTEMS
IBM HUNTSVILLE
�TASK
SYNOPSIS
a
NEED IU FOLLOW -ON PROGRAh4
a
OBJECTIVES O F ADVANCED ASTRIONICS P R O J E C T
a
a
-
DEFINITION O F FUTURE SYSTEMS
-
IDENTIFICATION O F APPLICATIONS
-
DEVELOP SYSTEM DESIGNS AND HARDWARE
-
DEVELOP, A T LEAST, 1 OFF-THE-SHELF PRODUCT IN EACH SUBSYSTEM AREA
1968 APPROACH
-
ANALYTICAL STUDIES (REQUIREMENTS AND TECHNOLOGY)
-
LAB T E S T (IU -S IVB SEPARATION)
-
PRELIMINARY DESIGN FOR PRINCIPAL APPLICATIONS
1969 APPROACH
-
LAB TESTS
-
BREADBOARD HARDWARE
-
COMPUTER AIDS T O DESIGN
a
CONTINUING CUSTOMER CONTACT
a
EVENTUAL SUBCONTRACTOR INVOLVEMENT
�SUMMARY O F PREVIOUS AND CURRENT E F F O R T S
e
1967 : REQUIREMENTS AND TECHNOLOGY STUDIES
Q,
1968
e
-
CONTINUE
-
START LAB TESTS (IU - S-IVB SEPARATION)
-
PRELIMINARY REQUIREMENTS/TECHNOLOGY REPORT B Y 3/1/68
E F F O R T S SUMMARIZED IN SUBSEQUENT TECHNICAL DATA
-
ANALYTICAL
-
LAB T E S T
�ANALYTICAL
RESULTS
�MISSIONS
(1970 - '85)
PROFILES
EARTH ORBITAL
Q
-
LUNAR
-
PLANETARY
VEHICLE TESTS
OMECTIVES
-
SPACE SCIENCES (ASTRONOMY, BIOMEDICINE, ASTROPHYSICS, ETC .)
NASA APPLICATIONS
COMMUNICATIONS
METEOROLOGY
RESOURCES
NAVIGATION
GEODESY
DEVELOPMENT (VEHICLES,
RESCUE, INDUSTRY)
-
MILITARY
RECON
COMMUNICATIONS
NAVIGATION
-
~OMMAND/CONTROL/COMMUNIC ATION
MANNEDPLANETARYEXPLORATION
�MISSION
9
(1970 - '85)
PLANETARY (SCIENCE AND EXPLORATION)
NASA
-
a
PREMISE
-
UNMANNED (SOLAR PROBES, FLYBY, ORBITERS, ETC. )
0 . 1 TO 5.6 AU
-
SOFT LANDINGS IN ' 80'S
LUNAR
NASA
-
LIMITED MANNED SURFACE
-
LUNAR ORBITAL SUPPORT, E. G., COMMUNICATIONS
SEVERAL WEEKS
-
MONTH
EARTH ORBITAL (SCIENCES, APPLICATIONS, ENGINEERING DEVELOP. )
NASA AND USAF
-
DEVELOP MANNED PLANETARY CAPABILITY
-
ASTRONOMICAL SCIENCES
-
EARTH RESOURCES SURVEY / APPLICATIONS
MANNED /UNMANNED
MILITARY RECON, COMM. AND NAVIGATION SATELLITES
LAUNCH AND SPACE VEHICLE DEVELOPMENT
�TRENDS I N UNMANNED MISSIONS
F Y 1969
START
I
I
I
1
I
NOW
TYP
I
; LEAD
I
I
I
I
1
I
I
J
t
I
I
TIME
I
I
I
NUMBER
OF
MISSIONS
\
I
CALENDAR YEAR
PLANNED
IN F Y 1968
BUDGET
�EXAMPLE SPACE SCIENCE APPLICATIONS PLAN - COMMUNICATIONS
(BASIS FOR FLIGHT PLAN)
0 11
(COMMON CARRIER)
- TV
SYNCOM - VOICE
- RELAY
-
TECHNOLOGY
SERIES
APPLICATIONS
SATELLITES
TV STUDIES
DIRECT
COMMUNITY
AAP EXP.
e SYNC ORBIT EXP
COMM. SATS.
LUNAR
COMM. SATS
(ABANDONED MODULES)
ATS-C
SERIES
NIMBUS E
- INTERROGATE
- RECORD
- LOCATE
o ORBITING
RELAY
* RELAY O F BALLOON COLLECTED DATA
7
�MSFC PROVIDED SPACE DEVELOPMENT PLAN
"SATURN UTILIZATION STUDY"
- LANDING
- RENDEZVOUS
- UNMANNED LOGISTICS
e SURFACE & ORBITAL
- LAUNCH/RENDEZVOUS
- MANNED OPS
e SCIENCE
- DAY/NITE OPS
- SUB -SURFACE
- ASTRONOMY
- SOIL SAMPLES
-
SAMPLING
MAN
- SUBSYSTEMS
(b
MAN
- SYNC ORBIT
e NUCLEAR
PLANETARY
- STAGE DEV.
- PROP. CLUSTERTNG
e HIGH S P E E D
REENTRY
a SPACE
a MANNED
PLANETARY
ENCOUNTER
e DEV. D E E P SPACE
DEV. 1OOK LBS
T O EARTH
ORBIT
e DEV. 400K LBS
EARTH ORBIT
8
�EARTH ORBITAL FLIGHT PLAN
/
*
s FLJGHTS SCHEDULE
TO BE DETERMINED
a PRELIMINARY ESTIMATE FOR
NUMBER OF LAUNCH VEHICLES
-
-
20 INTERMEDIATES NEW)
57 TITANS (USAF)
7 ATLAS -AGENAS
a 221 LAUNCH VEHICLES
THROUGH 1985
A Lunar Module (LM)
V
0
0
0
8
t)
Command and Service Module (CSM)
LM/CSM
Scientific & Earth Resources Experiments
Orbital Workshop - Spent Stage
Orbital Solar Observatory
Orbiting Astronomical Observatory (OAO)
a
Apollo Telescope Mount (ATM )
One Year Module - Ground Fitted
8 Applications Technology Satellites
D Orbiting Telescope - Man Tended
(D Orbiting Geophysical Laboratory (OGO)
BB Scientific Satellite - Atmosphere, Ionosphere
& Magnetosphere (GSFC)
0
�LUNARANDINTERPLAMETARYFLIGHTPLAN
/
/
UNMANNED SURFACE
JUPITER & NEPTUNE
#
b
7
@
0
Lunar ~odule/Command& Service Mbdule
Lunar Flying Vehicle ) (LFV)
I
Local Scientific Survey Module ( L S S ~
Lunar Module Shelter
Surveyor
8
Mars
Q
enu us
Mercury
�NASA / OMSF MISSION PROSPECTUS
TOTAL : 50 TO 103 FLIGHTS
?
(MAX : 81 FLIGHTS)
,
2
1
EARTH ORBITAL FTATIONS I
J
6
RESUPPLY TO
7
10
0
19
CALENDAR YEARS
�MSFC SUPPLIED FLIGHT PLAN - OPTIMISTIC
("SATURN UTILIZATION STUDY")
BALANCED
- BUDGET CONSTRA (NED
NMED SAT V IN -21
10 SM V I N -a
o UN,%C~UNDSAT v I M -m
V MANNED SAIURRV
V UUMC\tJMD SATURN V
R4TEi) SAT V UtMNNED
TOTAL LAUNCH VEHICLES : 116
��PAYLOAD WEIGHT REQUIREMENT TRENDS (PRELIMINARY)
*IWEO - INITIAL #EIGHT EARTH ORBIT
(SPENT BOOSTER + PAYLOAD)
CALENDAR YEAR
�WEIGHT REQUIREMENTS - LUNAR LANDED ASTRIONICS
OPTIMISTIC P R O J E
*INCLUDES A L L SUPPORTING SUBSYSTEMS
15
�PAYLOAD-VELOCITY REQUIREMENTS VS.
- TECHNOLOGY
100 NM
ORBIT
LUNAR
INJECTION
SYNC
ORBIT VESTA
JUPITER
FLYBY
FLYBY
*4 F-1 ENGINES ON S-IC
4.68 G'S MAX. ASCENT
�LAUNCH VEHICLE PAYLOAD GROWTH CAPABILITY
-
WEIGHT IN 100 NM EARTH ORBIT
CALENDAR YEAR
�LAUNCH VEHICLE OPTIONS (100K LBS)
PAYLOADS T O 100 NM FROM E T R
(LBS)
A
SAT V
SIB
DEFUVATIVE:
DERIVATIVE:
INTERMEDIATE -20
MS -260
3I 3
DERIVATIVE:
MS-I56
\
PRESSURE
FED
STORABLE
TITAN I I IG
�ASTRIONIC FUNCTIONS
I
Astrionic Subsvstem
I
Payload Checkout
Prelaunch
- - - - - - - - - - - - - - -
- - - - - - - - -
&
Booster
Boost
I
I
I
I
i
Phase
(GNC)
Reuse
I
I Maneuvers (GNC) I
P o s t Boost
Injection
Rendezvous &
Phase
Orbital A s s y / A C ~
Attitude Control
Data Eva1 & Transm.
Midcourse
@
Support
0
0
@
(GNC & Support Role)
Payload
Subsystem Functions
Unmanned
Satellite
Experiment
Carrier
Landing
Interim Exp. Module
Piggyback Sensor Dev.
OWS Support
0 9 Month Lifetime
Completely Integrated
Astrionic Subsystem
Space Station Exp. Module
6-9 Man
1 -1/2 year lifetime
Lunar and
Interplanetary
I
�ASTRIONIC
SUBSYSTEM
�SYSTEMS ANALYSIS METHODOLOGY
(1968 EFFORT)
I
SCIENCE
DEV. PLANS
MISSION
ANALYSIS
I
I
FLIGHT PLANS
AND PROFILES
I
I
VEHICLES
LAUNCH/SPAC ECRAFT
OVERALL ASTFUONICS
I
- - - - - - -
SUBSYSTEMS
C=J
TECHNOLOGY
\
- - - - -
HAIDWARE
DESIGN
I
IREQUIREMENTS I
PROJ. APPLICATIONS
AND COMMONALITY
I
�ASTRIONIC SUBSYSTEM PARAMETERS
i
SUBSYSTEMS,
PARAMETERS
I
LV
GNCS
IC S
EPS
ECS
LIFETIME (HOURS)
X
X
X
WEIGHT (POUNDS)
X
X
X
VOLUME (CUBIC F E E T )
X
X
PRIME POWER (WATTS)
X
THERMAL POWER DISSIPATED (WATTS)
VELOCITY ACCURACY (FT/SEC)
X
I
X
X
X
X
�PROJECTED ASTHONIC CONFIGURATIONS
a
0
BLOCKIIIU
-
MODERATE UPDATES IN TECHNOLOGY
-
1968 - '75
ADVANCED ASTRIONICS
-
1975 - '85
-
ALL NEW TECHNOLOGY
�EVOLUTION OF ADVANCED ASTRIOM CS
BLOCKI.1 IU
I
m
1968-71
o
II
4
R
I
I
I
ADVANCED ASTFUONICS
4
I
4
1971-75
I
4
P
0
EXTENDED LIFE I U
SYNC ORBIT
4
15
e
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6
HI 1U
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ADVANCED I U
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4
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24-36 HI I U
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a
a
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LAUNCH
ORBIT CHECKOUT
EXPERIMENT
CRRRIER
a
a
EXPERIMENT MODULES
a
AAP-A (2 WK IU)
LASER SYSTEM COMMUNICATION
EXPERIMENT (LSCE)
CLUSTER
UNMANNED SATELLITE
4
EXPERIMENT MODULES
I
:
a
a
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LSCE
CLUSTER
DATA PROCESSING
SATELLITE
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MISSION SUPPORT MODULES
MISSION SUPPORT MODULES
EARLY WORKSHOP
3 M O IU
PASSNATION
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2 YR LIFE
MARS MISSION
LORL
GNC
---
DATA PROCESSING
ATTITUDE
POINTING
POWER
-
ENVIRONMENT
�GUIDANCE
NAVIGATION
CONTROL
SUBSYSTEM
�GNC FUNCTIONAL REQUIREMENTS (UNMANNED MISSIONS)
ORIENT THRUST.
ROUND BASED
STAR FIXES.
DOPPLER RADAR.
HORIZON SENSING.
MIDC OURSE
.
�GNC FUNCTIONAL REQUIREMENTS (UNMANNED MISSIONS)
MISSION PHASES
NG ATTITUDE.
ANDDOPPLER.
SERTION INTO
ARTH-PLANET TRAJ*
PLANETARY-BOUND
TRAJECTORY
ORIENT THRUST,
GROUND BASED.
GROUND BASED.
ORIENT (INCREASED
MIDCOURSE,
CELESTIAL FIXES*
RANGE & RATE
-
EXPERIMENTS,
ANTENNAS.
27
�INTERPLANETARY GNC REQUIREMENTS
AND CAPABILITIES
?
MARINER IV
\
PRIOR TO
C
JUPITER
FLYBY
PRIOR
9
- 1
13
I
,1
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b
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ACTUAL
ESTIMATED
I
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CALENDAR YEARS
I
1
DSN ONLY
SELF-CONTAINED
DSN + ONBOARD
SENSOR @ 30M
NM FROM JUPITER
�SATURN GUIDANCE AND NAVIGATION P E R F O R M A N C E
Vehicle Number
Velocity Vector E r r o r
n v (fti~)
.,*
rl,
Required Performance
Radius V e c t o r E r r o r
A
R (ft)
Injection Angle E r r o r
b ++(deg. )
�GNC TECHNOLOGY TRENDS
BOOST PHASE
MIDCOURSE
CORRECTIONS
PAYLOAD ATTITUDE
CONTROL
NAVIGATION
STATE O F THE ART
Command Gui,
Limited
(In B o o s t e r )
AV
Temporary Excursions
f o r A V Corrections
MODIFICATION
*
L e s s Accurate
Fixes at Periodic
and C r i t i c a l
0
Aided by OnBoard Radar/
0
Augmented by
Multiple 4 V
Corrections
Measurements
Command Gui.
Improved Impact
Parameter
S t a t i s t i c a l Nav.
A c c u r a t e OnBoard Nav.
Multiple Optical
Radar Verifi-
f o r AV C o r r e c t i o n s
A c c u r a t e Att. Cont.
& Radar Sensors
Cold Gas J e t s & CMGts
Correction
�TECHNOLOGY TRENDS
- WEIGHT AND ACCURACY TRADES
PROPELLANT WE
REQUIREMENTS
AV- FT/SEC
STRAP-DOWN ACCURACY
�INSTRUMENTATION
COMMUNICATIONS
SUBSYSTEM
�MILESTONES
TIME (W)
MINIMUM
PREDESIGN CONCEPTS
PAPER MODEL & BREADBOARD
(SELECT TECHNOLOGY)
DEVELOPMENTAL MODEL
(IN A USABLE CONFTGURATION)
PROTOTYPE MODEL
(LIKE PRODUCTION)
PRODUCTION MODEL
(QUALITY TEST & PRODUCTION UNITS)
FLIGHT PASSENGER
(FLIGHT QUALIFY)
FLIGHT ACTIVE
(ASSIGNED TO A MISSION)
TOTAL TIME
MAXIMUM
�ICS CIRCUIT TECHNOLOGY
ADVANCED ASTRIONICS SYSTEM
BLOCK I1 IU (MODERATE
0
BI-POLAR TIEANSISTER
INTEGRATED CIRCUITS
(LSI) 50 + GATES/CHIP
- TRANSISTER-TRANSISTER
- BI -POLAR
- DIODE - TRANSISTER LOGIC
- CURRENT MODE LOGIC
- INSULATED GATE FIELD
• NEW TECHNOLOGIES
- LOW TEMPERATURE
EFFECT TMNSISTER (IGFET)
SINGLE DIFFUSION (DC & AC)
COMPLEMENTARY
- HYBRID BI-POLAR/IGFET
- COMPLEMENTARY -
INTEGRATION
- MOLECULAR CIRCUITS
�INTEGRATED LOGIC CIRCUIT GATES P E R CHIP TRENDS
10K
POWER GATES
1000
P4
H
z
U
g 100
PI
8
E
POSSIBLE BREAKTHROUGH COULD
CAUSE SIGNIFICANT INCREASE IN
NUMBER O F GATES P E R CHIP
4
a
10
LOWER
POWER GATES
TIME OF AVAILABILITY
35
�INTEGRATED CIRCUIT CHIP SIZE TRENDS
'72
'7 4
TIME OF AVAILABILITY
'7 6
�I
INTEGRATED LOGIC CIRCUIT POWER-SPEED PRODUCT TRENDS
TIME O F AVAILABILITY
37
�COMMUNICATION TECHNOLOGY
- DATA RATE GROWTH
J
-10
-
-----
10 FRAMES/SEC
8
-l o
-
I
-
.
-
----
-
6
-
-
-
-10 4
- --
- - ---
-
1 FRAME/SEC.
1 F R A M E / ~SEC.
~
YEARS
�DATA ACQUISITION REQUIREMENTS
�ELECTRICAL
POWER
SUBSYSTEM
�UNMANNED SATELLITE ELECTRICAL BOWER REQUIREMENTS
SATELLITE TYPES
GE - GEOPHYSICAL EXPEFUMENT
SE - SPACE EXPLORATION
WS - WEATHER SATELLITE
ND - NUCLEAR DETECTION
MD - METEOROID
BE - BIOLOGICAL EXPERIiVIENT
CS - COMMUNICATIONS SATELLITE
BT -BALLISTIC TEST
CALENDARYEAR
�lYIANNED SPACECRAFT POWER REQUIREMENTS
CALENDAR YEAR
�BATTERYANDFUELCELLTECHNOLOGY
FLIGHT
PR!MAR'( FUEL- CELLS
U N I T POWER
1
5 KW
1
I
��NUCLEAR POWER TECHNOLOGY
CALENDAR YEAR
�ENVIRONMENTAL
CONTROL
SUBSYSTEM
�ENVIRONMENTAL CONTROL REQUIREMENTS AND TECHNOLOGY
Electronic Propelled
Lunar Options
MO L- RTGS
,-a
Missions Louvers, Radiators,
Active IU: Circ Fluid, Heaters, cold
Plates, & Sublimator
-prated
Mariner 'Mars: Passive
with Louvers & Heaters& Cold Plates
s & Heaters & Cold Plates
neer: passive /
1
57
-
6b
65
7b
75
CALENDARYEAR
do
85
�LAB
TESTS
IU
-
S-IVB
SEPARATION SYSTEM
�PURPOSE AND DEFlbllTlOkl OF PAYLOADS A AND B
a
DETERMINE OPTIMUM SENSORS
Q
lN IT IATE SPACE MITEOROLOGY AND EARTH SURVEY
6
DETERMINE VALUE OF MAN'S PARTI C l PAT lON
METEOROLOGY (A)
NATURAL RESOURCE SURVEY (B)
6
MICROWAVE RADIOMETRY
a
MULTI SPECTRAL PHOTOGRAPHY
a
I R SPECTROSCOPY
a
INFRARED RADIOMETRY AND SPECTROSCOPY
a
POLAR IM n R Y
a
RADAR
a
UV PHOTO-S PECTROMETRY
��DOCKING RING
PER l MENT RACK
RACKllU INTERFACE CABLE 2
�CLUSTER MISSION! PROFILE
S-IVB CLUSTER
WORKSHOP
---------
5.
4.
9.
IUlSLA DOCKED
CSM DOCKED
TO IUlSLA
CSM SEPARATION
b
14 DAYSl90DAYS
12. REENTRY
�PROJECT THERMO
PURPOSE : VERJFY LONG DURATION CRYOGENIC VEHICLE DESIGN
TECHNIQUES
-
PROPULSION, I, E., MARS FLYBY
-
FUEL CELLS
EXPERIMENTS (AT
e
lom2TO
G'S)
-
CONDENSING HEAT TRANSFER
-
BOILING HEAT TRANSFER
INTERFACE STABILITY
-
HIGH PERFORMANCE INSULATION
-
STRATIFICATION
-
MASS GAGING
PROPELLANT TRANSFER
- DESTRATIFICATION
BOILOVER (ON PROPELLANT TRANSFER AM) BOILING H. T o TANKS)
VENT SEPARATOR
WEIGHT
: 15K LBS
S I B CAPABILITY : 22K LBS T O 260 NM
�PROJECT THERMO IU/SLA SATELLITE (IBM-LOCKHEED-MSFC)
IU - S-IVB
SEPARATION
�PROJECT THERMO IU/SLA EXPERIMENT MODULE
(UNMANNED SATELLITE)
LOWER SLA
ACCELERATI
THRUSTERS
THRUSTER
PROPELLANT
TANKS
�P R O J E C T THERMO IU/SLA
EXPERIMENT MODULE
I
LOWER
SLA*
THRUSTERS
*SLA
- SPACECRAFT LM ADAPTER
1 / 6 0 ~SCALE
~
1
JETS
bHYDROGEN TANK
DOME
�PAYLOAD WEIGHT CONSTRAINTS
(UPRATED SATURN-IB)
EST. INJECTED WEIGHT
(ABOVE S -1VB)
:
LESS NOSE CONE & SLA
:
INJECTED PAYLOAD WEIGHT :
22,400LBS.
-
3,640LBS.
18,760 LBS.
PAYLOAD MA RGIN (260NM)
3800 LBS.
PAYLOAD (1000 LBS),
�SATURN S-IVB AFT DMTERSTAGE SEPARATION SYSTEM
UPRATED SATURN
SATURN
�RECOHHEMDEB IU/S-BVB SERARAT ION CONCEPT
BEFORE SEPARATION
AFTER SEPARATION
�RECOMMENDED IU/S-IWW SEPARATION CONCEPT
I U STRUCTURE
TENS lON PLATE
DEBRIS SHIELD
SEPARATION PLANE
��IU/S-IVB SBPARATIOM SYSTEM QUALlFlCATlOM APPROACH
o
SMALL SEGMENT TESTS TO VER IFY PYROTECHNIC
CHARGE AND STRUCTURE
0
LARGE SEGMENT TESTS TO VER IFY ENVIRONMENT
0
STATIC LOAD TESTS
0
SEPARATION SYSTEM QUALIFICATION TEST
-
COMPLETE I U STRUCTURE
-
S IVBISLA STRUCTURAL SEGMENTS
�R I S K S
DEPENDENCIES
MARKETING
�DEPENDENCIES
AND
RISKS
DEPENDENCIES
NASA PLANNING AND BUDGET
-
OSSA UNMANNED MISSION INCREASE
ADVANCED SPACE STATION - WHEN?
-
MANNED PLANETARY FLIGHT - WHEN?
NUCLEAR STAGE DEVELOPMENT
ELECTRICAL POWER TECHNOLOGY VS COMMUNICATIONS TECHNIQUES,
E. G.
, LASERS
TWO -YEARS MAN -IN -SPACE
-
-
o
(EARTH ORBIT)
NASA/USAF MISSION INTEGRATION
ASTRIONICS NASA BUDGET : $1.2B T O $0.4
8
SELECTED LAUNCH VEHICLE MIX
-
TITAN VERSUS S -1VB DERIVATIVES
LSI CIRCUIT BREAKTHROUGH - WHEN? HOW?
-
PRE-EMPTION BY OTHER CONTRACTORS
RISKS
-
Iu/s-IVB
-
MINIMAL CURRENT INVESTMENT, RISK REDUCED
SEPARATION SYSTEM HARDWARE ($50K) VS APPROVED NASA PROJECTS
�MARKETING
1 9 6 8 PLANS IN PREPARATION
STRATEGY
-
COORDINATE STUDY, TESTS, DESIGNS WITH NASA/USAF
PROPOSE FULL -SCALE IU -S IVB SEPARATION SYSTEM DEVELOPMENT
SUBMIT UNSOLICITED PROPOSALS : EACH DESIGN DEVELOPED IN 1968
LEAD CUSTOMER
NEW APPLICATIONS
PROJECT IDENTIFICATION
TECHNOLOGY
HARDWARE DESIGN
ACTIVITIES
-
IBM/LOCKHEED/MSFC
PROPOSING IU/SLA FOR THERMO
MEETINGS/VISITS
NASA HEADQUARTERS AND MSFC
WEEK AVERAGE)
LOCKHEED, HUNTSVILLE (WEEKLY T O DAILY)
NASA E R C PLANNED 3/68
BATELLE MEMORIAL INSTITUTE (NAsA/OSSA)
MARTIN MARIETTA : IU/SLA,
-
-
11/20/67
11/1/67
ESTABLISH USAF CONTACTS THROUGH FSD-WEST AND WASHINGTON MARKETING
�
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Title
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Saturn V Collection
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Saturn V Collection
Description
An account of the resource
<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
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Identifier
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spc_stnv_000037
Title
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Advanced Astrionics project review.
Alternative Title
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IBM No. 68-K05-0001
Description
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Given at the IRAD Technical Seminar, Gaithersburg, Maryland, January 30, 1968. F. L. Pugh, Principal investigator; E. C. Caldwell, Advanced IU Systems, IBM Huntsville.
Creator
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Caldwell, E. C.
Pugh, F. L.
International Business Machines Corporation. Federal Systems Division. Space Systems Center
Date
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1968-01-30
Temporal Coverage
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1960-1969
Subject
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Launch vehicles (Astronautics)--Guidance systems
Launch vehicles (Astronautics)--Control systems
Spacecraft electronic equipment
Spacecraft instruments
Type
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Reports
Text
Source
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Saturn V Collection
Box 25, Folder 24
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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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
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10987/Guidandcontrosatulaunvehi_080807145656.pdf
9cad960d606445523f8dffe7cd223561
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
An account of the resource
<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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Guidandcontrosatulaunvehi_080807145656.pdf
spc_stnv_000316
Title
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"Guidance and Control of Saturn Launch Vehicles."
Alternative Title
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AIAA Paper No. 65-304
Description
An account of the resource
The navigation, guidance, and control modes and problems of the Saturn launch vehicles are given as the requirements for the guidance and control methods. Two path adaptive guidance modes, featuring flight path optimization, in the form of a polynomial mode and an iterative mode are given in their computation form and compared with respect to mission flexibility, implementation requirements, and performance. Attitude control during the propelled flight phases requires consideration of various bending and sloshing modes; stability of the control system is obtained by phase stabilization of the low frequencies and by attenuation of the higher frequencies. Typical shaping networks and their transfer functions are given. The attitude control system during coasting periods is briefly described. The functional behavior and characteristic data of the main guidance and control hardware such as the inertial sensors, stabilized platform, digital computer, data adapter, control computer, and actuation system are described. Reliability requirements are emphasized. The principle of redundancy is extensively used to obtain highest reliability for long operating times. Data and results from recent Saturn I flights summarize the performance of the guidance schemes.
Creator
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Haeussermann, Walter
Date
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1965-07-26
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
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Saturn project
Launch vehicles (Astronautics)--Control systems
Launch vehicles (Astronautics)--Guidance systems
Navigation
Spacecraft guidance
Spacecraft control
Type
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Text
Design Analyses
Source
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Saturn V Collection
Box 14, Folder 32
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
Information about rights held in and over the resource
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_000300_000324
Is Referenced By
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<a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17179"> View this item in ArchivesSpace </a>