jet propulsion laboratory - ntrs.nasa.govjet propulsion laboratory california institute of...
TRANSCRIPT
JET PROPULSION LABORATORY
V O Y A G E R SPACECRAFT SYSTEM
FlUAl TECHNICAl REPORT
VOLUME E D E S I G N F O R O P E R A T I O N A L SUPPORT EQUIPMENT- 1969 TEST FLIGHT t
prepared for
JET P R O P U L S I O N L A B O R A T O R Y CALIFORNIA I N S T I T U T E OF TECHNOLOGY
PASADENA, C A L I F O R N I A
U N D E R
C O N T R A C T N O . 951111 J U L Y 1 9 6 5
T H E B O E l N G C O M P A N Y A E R O - S P A C E D I V I S I O N S E A T T L E , W A S H I N G T O N
LYSLE A. WOOD VICE PRESIDENT-GENERAL MANAGER
AERO-SPACE DIVISION
THE BOEING COMPANY
SEATTLE. WASHINGTON 98124
J u l y 29, 1965
Jet Propuls ion Laboratory C a l i f o r n i a I n s t i t u t e of Technology 4800 Oak Grove Drive Pasadena, C a l i f o r n i a
Gentlemen:
This t e c h n i c a l r e p o r t cu lmina tes n e a r l y t h r e e yea r s of Mariner/Voyager s t u d i e s a t Boeing. During t h i s t i m e , w e have ga ined an a p p r e c i a t i o n of t h e magnitude of t h e task, and f e e l c o n f i d e n t t h a t t h e expe r i ence , r e sources and d e d i c a t i o n of The Boeing Voyager Team can adequate ly m e e t t h e cha l l enge .
The Voyager management t a s k is accen tua ted by three prime requi rements : An i n f l e x i b l e schedule of launch o p p o r t u n i t i e s ; t h e need f o r an informat ion- re t r ieva l system capable of re l iab le h i g h - t r a f f i c t r ansmiss ion over i n t e r - p l a n e t a r y d i s t a n c e s ; and a s p a c e c r a f t des ign f l e x i b l e enough t o accommodate a number of d i f f e r e n t miss ion requirements . W e b e l i e v e t h e t e c h n i c a l approach presented h e r e s a t i s f i e s t h e s e des ign r equ i r emen t s , and t h a t management techniques developed by Boeing f o r space programs w i l l a s s u r e d e l i v e r y of operable s y s t e m s a t each c r i t i c a l launch da te .
M r . E. G. Czarnecki has been a s s igned program management r e s p o n s i b i l i t y . H i s group w i l l be ab ly assisted by E l e c t r o - o p t i c a l Systems i n t h e area of s p a c e c r a f t power, P h i l c o Western Development L a b o r a t o r i e s w i l l be respon- sible for telecommunications, and t h e Au tone t i c s D iv i s ion , North American Avia t ion w i l l provide t h e a u t o - p i l o t and a t t i t u d e r e f e r e n c e sys t em. This team has already demonstrated an e x c e l l e n t working r e l a t i o n s h i p dur ing the execu t ion of t h e Phase I A c o n t r a c t , and w i l l have my f u l l conf idence and suppor t dur ing subsequent phases.
This program w i l l r e p o r t d i r e c t l y t o George H. S t o n e r , V i c e P r e s i d e n t and A s s i s t a n t D iv i s ion Manager f o r Launch and Space Systems. M r . S tone r has t h e a u t h o r i t y t o a s s ign t h e r e sources necessa ry t o meet t h e o b j e c t i v e s as s p e c i f i e d by JPL.
The Voyager Spacec ra f t System r e p r e s e n t s t o us more than a b u s i n e s s oppor- t u n i t y or a new product o b j e c t i v e . W e view i t as a chance t o ex tend s c i e n t i f i c knowledge of t h e u n i v e r s e w h i l e s imul t aneous ly c o n t r i b u t i n g t o n a t i o n a l p r e s t i g e and w e n a t u r a l l y look forward t o t h e o p p o r t u n i t y of s h a r i n g i n t h i s adventure .
- J Lys le A. Wood
Bn.€.NG
D2 -82 709-5
CONTENTS P a g e
INTRODUCTION
SUMMARY
PART I OSE FOR 1969 TEST FLIGHT, GENERAL 1-1
PART 11 OSE FOR ATLAS/CENTAUR LAUNCHED 1969 TEST FLIGHT 11-1
I1 1.0
I1 1.1
I1 2.0
I1 2.1
I1 2.2
I1 2.3
I1 3.0
I1 3.1
I1 3.2
I1 3.3
I1 3.4
I1 3.5
I1 3.6
I1 3.6.1
I1 3.6.2
I1 3.7
OSE OBJECTIVES AND DESIGN CRITERIA
SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA
OSE DESIGN CHARACTERISTICS AND RESTRAINTS
OSE SEQUENTIAL FLOW CHART
OSE DESIGN PARAMETERS
OSE DESIGN CRITERIA
FUNCTIONAL DESCRIPTION -- SYSTEM LEVEL OSE
MDE FUNCTIONAL DESCRIPTION
LCE FUNCTIONAL DESCRIPTION
S I C FUNCTIONAL DESCRIPTION
AHSE - SYSTEM LEVEL
SPACECRAFT S IMUL AT0 R
SPECIAL SYSTEM LEVEL OSE, FUNCTIONAL DESCRIPTIONS
F u n c t i o n D e s c r i p t i o n s o f t h e T r e n d D a t a E q u i p m e n t
Magnetic ?E.apping E q u i p m e n t , F u n c t i o n a l D e s c r i p t i o n
EQUIPMENT L I S T
iii
BDE/Nc
D2-82709-5 J
I1 4.0
I1 4.1
I1 4.2
I1 4.3
I1 4.4
I1 4.5
I1 4.6
I1 4.7
SUBSYSTEM TEST EQUIPMENT
TELECOMMUNICATIONS SUBSYSTEM OSE
POWER SUBSYSTEM OSE
PROPULSION SUBSYSTEM OSE
ENGINEERING MECHANICS
SPACE SCIENCE OSE
ATTITUDE REFERENCES AND AUTOPILOT OSE
CENTRAL COMPUTER AND SEQUENCER (CCSS) OSE
P a r t I11
I11 1.0 OSE OBJECTIVES AND DESIGN CRITERIA
I11 1.1 SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA
OSE FOR SATURN IB/CENTAUR LAUNCHED 1969 TEST FLIGHT 111-1
I11 2.0 OSE DESIGN CHARACTERISTICS AND RESTRAINTS
I11 2.1 OSE SEQUENTIAL FLOW CHART
I11 2.2 OSE DESIGN PARAMETERS
I11 2.3 OSE DESIGN CRITERIA
I11 3.0 FUNCTIONAL DESCRIPTION -- SYSTEM LEVEL OSE
I11 3.1 MDE FUNCTIONAL DESCRIPTION
I11 3.2 LCE FUNCTIONAL DESCRIPTION
I11 3.3 STC FUNCTIONAL DESCRIPTION
I11 3.4 AHSE FUNCTIONAL DESCRIPTION
I11 3.5 SPACECRAFT SIMULATOR
I11 3.6 SPECIAL SYSTEM LEVEL OSE
b
I 1 .
D2-82709-5
I11 4.0 SUBSYSTEM TEST EQUIPMENT
I11 4.1 TELECOMMUNICATIONS
I11 4.2 POWER SUBSYSTEM OSE
I11 4.3 PROPULSION AND REACTION CONTROL OSE
I11 4.4 ENGINEERING MECHANICS
I11 4.5 SPACE SCIENCE OSE
I11 4.6 ATTITUDE REFERENCE AND AUTOPILOT
I11 4.7 CENTRAL COMPUTER AND SEQUENCER (CCSS) OSE
V
INTRODUCTION
D2-82709-5
. INTRODUCTION
I n f u l f i l l m e n t of t h e J e t Propuls ion Labora tory (JPL) C o n t r a c t 951111,
t h e Aero-Space D i v i s i o n . o f t h e Boeing Company submits t h e Voyager Space-
c r a f t F i n a l Technica l Report . The complete r e p o r t , r e spons ive t o t h e
documentation requi rements s p e c i f i e d i n t h e Statement of Work, c o n s i s t s
of t h e f i v e fo l lowing documents:
VOLUME TITLE
BOEI NG DOCUMENT NUMBER
A P r e f e r r e d Design F l i g h t Spacecraf t and Hard- D2-82709-1 ware Subsystems
P a r t I
Sec t ion 1 .O Voyager 1971 Mission O b j e c t i v e s and Design C r i t e r i a
Sec t ion 2.0 Design C h a r a c t e r i s t i c s and R e s t r a i n t s
Sec t ion 3.0 System Level Funct iona l D e s c r i p t i o n s of F l i g h t Spacec ra f t
P a r t I1
Sec t ion 4.0 Funct iona l D e s c r i p t i o n f o r Space- c r a f t Hardware Subsystems
P a r t I11
Sec t ion 5.0 Sec t ion 6.0 System R e l i a b i l i t y Summary Sec t ion 7.0
Schedule and Implementat ion P lan
I n t e g r a t e d T e s t P l a n Development
B A l t e r n a t e Designs Considered-Fl ight Space- D2-82709-2 c r a f t and Hardware Subsystems
C Design f o r Opera t iona l Support Equipment D2-82709-3
D Design f o r 1969 Test Spacec ra f t D2-82709-4
E Design f o r Opera t iona l Support Equipment 02-82709-5 f o r 1969 Test F l i g h t Spacecraf t
1
BCK€ING
D2-82709-5
For convenience t h e h i g h l i g h t s of t h e above documentation have been
summarized t o g i v e an overview o f t h e scope and dep th of t h e t e c h n i c a l
e f f o r t and management implementat ion p l a n s produced du r ing Phase I A .
T h i s summary i s conta ined i n Volume 0, Program H i g h l i g h t s and Manage-
ment Phi losophy, D2-82709-0.
provided t o f u r n i s h d e t a i l e d in fo rma t ion developed through t h e cour se
of t h e c o n t r a c t and t o provide s u b s t a n t i a t i n g r e f e r e n c e m a t e r i a l
which would not o the rwise be r e a d i l y a v a i l a b l e t o JPL personnel .
A d d i t i o n a l l y , a f u l l s c a l e mock-up of t h e p r e f e r r e d des ign s p a c e c r a f t
has been assembled. Th i s mock-up, shown i n F igu re 1, has been d e l i v e r e d
t o JPL. The mock-up has been provided w i t h t h e view t h a t it would be o f
v a l u e t o JPL i n subsequent Voyager S p a c e c r a f t System planning.
Will iam M. A l l en , P r e s i d e n t of The Boeing Company, M r . Lys l e A. Wood,
Vice-pres ident and Aerospace Div i s ion General Manager, M r . George H.
S tone r , Vice-president and A s s i s t a n t D i v i s i o n Manager r e s p o n s i b l e f o r
Launch and Space Systems a c t i v i t i e s , and M r . Edwin G. Czarnecki , Voyager
Program Manager, a r e shown w i t h t h e mockup.
A number o f suppor t ing documents a r e
M r .
During t h e t h r e e month pe r iod covered by C o n t r a c t 951111, Boeing has:
1) Performed system a n a l y s i s and t r a d e s t u d i e s necessa ry t o a c h i e v e
a n optimum o r p r e f e r r e d des ign of t h e F l i g h t Spacec ra f t .
Determined t h e r equ i r emen t s and c o n s t r a i n t s which a r e imposed
upon the F l i g h t S p a c e c r a f t by t h e 1971 mis s ion and by t h e o t h e r
systems and e lements of t h e p r o j e c t , i n c l u d i n g t h e s c i e n c e
payload.
Developed f u n c t i o n a l d e s c r i p t i o n s f o r t h e F l i g h t S p a c e c r a f t and
f o r each o f i t s hardware subsystems, exc lud ing t h e s c i e n c e payload.
2)
3)
2
BnE.NG
D2-82709
I
Figure 1: Preferred Design Mockup
Wil l iam M. Al len Edwin G. Czarnecki Lysle A. Wood George H. Stoner
Left to Right :
3
D2-82709-5
* 4) Determined t h e requi rements f o r t h e F l i g h t Spacec ra f t a s s o c i a t e d
"
I .
,
Opera t iona l Support Equipment (OSE) necessa ry t o accomplish t h e
Voyager 1971 mission.
5 ) Developed a p r e l i m i n a r y des ign of t h e OSE.
6 ) Developed f u n c t i o n a l d e s c r i p t i o n s f o r t h e OSE.
7 ) Determined t h e o b j e c t i v e s of a 1969 t e s t f l i g h t and t h e d e s i g n of
t h e 1969 Test F l i g h t Spacec ra f t u s ing t h e Atlas/Centaur Launch
Vehic le . An a l t e r n a t e t e s t f l i g h t program i s p resen ted which
u t i l i z e s t h e Sa turn IB/Centaur Launch Vehicle.
8) Developed f u n c t i o n a l d e s c r i p t i o n s f o r t h e F l i g h t S p a c e c r a f t Bus,
and i t s hardware subsystems, and OSE f o r t h e 1969 tes t s p a c e c r a f t .
9 ) Updated and supplemented the Voyager Implementation P lan o r i g -
i n a l l y conta ined i n t h e response t o JPL Request f o r Proposa l
3601.
The Voyager program management Team, shown i n F igure 2 i s under t h e
d i r e c t i o n of M r . Edwin G. Czarnecki. M r . Czarnecki i s t h e s i n g l e
e x e c u t i v e r e s p o n s i b l e t o J P L and Boeing management f o r t h e accomplish-
ment of t h e Voyager S p a c e c r a f t Phase I A , and w i l l d i r e c t subsequent
phases of t h e program. He r e p o r t s d i r e c t l y t o M r . George H. S tone r
who has t h e a u t h o r i t y t o commit t h o s e c o r p o r a t e r e s o u r c e s necessa ry t o
f u l f i l l JPL 's Voyager Spacec ra f t System o b j e c t i v e s .
Although Boeing has a t e c h n i c a l management c a p a b i l i t y i n a l l a s p e c t s
o f t h e Voyager Program, i t i s planned t o ex tend t h i s c a p a b i l i t y i n
d e p t h through a s s o c i a t i o n w i t h companies recognized a s s p e c i a l i s t s i n
c e r t a i n f i e l d s . Use of team members t o s t r e n g t h e n Boeing's c a p a b i l i t y
5
.
SYSTEMS TEST AND LAUNCH OPERATIONS
K. K . McDANlELS
. i
k
FACILITIES OPERATIONS
R. K. MILLS L. B. BARLOW
SYSTE PROG
I FLIGHT SPACECRAFT COGNIZANT ENGINEERS
1 ~
FABRICATION - . . AND ASSEMBLY
QUALITY CONTROL MISSION OPERATIONS
SYSTEMS TESTING LAUNCH OPERATIONS
SYSTEM ANALYSIS SYSTEM REQUIREMENTS
r- TEST BOARD
MISSION ANALYSIS SYSTEM INTEGRATION
1 MATERIEL
BD€..MS
D2-82709-5
QUALITY ASSURANCE CONTRACT RELIABILITY AND ADMINISTRATION SAFETY FINANCE
~ ~ -
!AM MANAGER
ENGINEERING MANAGER
, W. C. GALLOWAY
SPACECRAFT ENGINEERiNG
G. B. WILLIAMS
SYSTEMS M A N AGE M ENT
PLANNING PROGRAM A N D REPORTS
LOGISTICS SPACE SCIENCE
W. F. HILTNER
TECHNOLOGY INTEGRATION
T. G. DALBY
CONFIGURATION MANAGEMENT 8 CONTROL
ELECTRONICS TECHNOLOGY TECHNOLOGY
I STRUCTURES AND 1 I I BIOASTRONAUTICS I MATERIALS 1 TECHNOLOGY
1 M. J. TURNER I 1 A. J. PlLGlM I Figure 2 Boeing Voyager
Spacecraft Systems Management S t ruc tu re
7- 7
D2-82709-5
P was cons ide red e a r l y du r ing pre-proposal a c t i v i t i e s . The b a s i c concept
was t o add team members who would complement Boeing expe r i ence and
c a p a b i l i t y , and s i g n i f i c a n t l y improve t h e amount and q u a l i t y of
t e c h n i c a l and management a c t i v i t i e s . Based upon compe t i t i ve con-
s i d e r a t i o n s i n c l u d i n g expe r i ence and p a s t performance and g i v i n g
s t r o n g e s t emphasis t o t e c h n i c a l q u a l i f i c a t i o n s and management w i l l i n g -
nes s t o suppor t t h e Voyager e f f o r t , Au tone t i c s , P h i l c o Western Develop-
ment L a b o r a t o r i e s , and Elec t ro-Opt ics Systems were chosen a s team
members. Th i s team arrangement , s u b j e c t t o JPL approva l , i s shown
i n F igu re 3.
be accomplished by t h i s Team i s i l l u s t r a t e d i n F igure 4.
l e a d i n g t o t h e format ion o f t h i s team were i n i t i a t e d l a t e i n 1964,
The f l i g h t s p a c e c r a f t des ign and i n t e g r a t i o n t a s k t o
Discuss ions
formal work s t a t emen t agreements have been a r r i v e d a t , and t h e r e has
been a cont inuous and complete free exchange o f i n fo rma t ion and docu-
menta t ion ; p e r m i t t i n g t h e Boeing team t o s a t i s f y JPL's requi rements
i n dep th and wi th confidence.
9
BLTElNG
D2 -82 709-5
~
BOEING VOYAGER TEAM
VOYAGER SPACECRAFT AND SPACE SCIENCES PAYLOAD INTEGRATION CONTRACTOR
The Boeing Comoany S e a t t l e , Washington
M r . E. G. Czarnecki - Program Manager
SUBCONTRACTOR
A u t o n e t i c s , North American Aviat ion Anaheim, C a l i f o r n i a
Au t o p i 1 o t and A t t i t u d e Refer-
Sub system
M r . R . R . Mueller Program Manager
SU BCONTRACTOR
P h i l c o , Western Development Lab.
Pa lo A l t o , C a l i f o r n i i
Telecommunication Subsystem
Mr. G. C. Moore Program Manager
FIGURE 3
10
SUBCONTRACTOR
Elec t ro -Opt i ca l Systems, I n c . Pasadena, C a l i f o r n i a
E l e c t r i c a l Power Subsystem
M r . C. I . Cummings Program Manager
.
PHILCO TELECOMMUNICATIONS SUBSYSTEM BOElNd
WROTE(
I
IISMS
Figure 4: Voyager Flight Spacecraft Subsystem I ntegration
1 1
This document, D2-82709-5, Design for Operational Support Equipment
for 1969 Test Flight, is summarized below.
OSE preliminary design data is presented for both the Atlas/Centaur
launched 1969 test flight and the alternately proposed Saturn IB/
Centaur launched 1969 test flight. The basic philosophy of the
design of OSE for the 1969 test flight includes the use of 1971
Voyager OSE with minimum modifications wherever practicable.
Design for OSE for the 1969 test flight is presented by noting
the differences and exceptions to the material presented in D2-82709-3
(Design for OSE, 1971 Voyager Mission).
ences and exceptions which influence OSE design for the 1969 test
flight relate to the fact that a science package and a flight capsule
are not planned for the Atlas/Centaur launched test flight, and only
simulated science packages and flight capsules are planned for the
Saturn IB/Centaur launched test flight.
In broad terms, the differ-
13
c
PART I OSE FOR 1969 TEST FLIGHT, GENERAL
D2-82709-5 . PART I , OSE FOR 1969 TEST FLIGHT, GENERAL
This volume d e s c r i b e s t h e p re l imina ry des ign of Opera t iona l Support
Equipment r e q u i r e d t o suppor t each of t h e two 1969 t e s t f l i g h t space-
c r a f t c o n f i g u r a t i o n s d e f i n e d by D2-82709-4, “Design f o r 1969 T e s t
Spacecraft .’’ These two c o n f i g u r a t i o n s a r e :
1)
2)
Atlas/Centaur launched 1969 t e s t s p a c e c r a f t ;
Sa tu rn IB/Centaur launched 1969 t e s t s p a c e c r a f t .
The 1969 t e s t OSE des ign i s presented i n t h e same manner used f o r t h e
1969 t e s t s p a c e c r a f t i n D2-82709-4.
t e s t f l i g h t i s p resen ted i n P a r t I1 and OSE f o r t h e Sa tu rn IB/Centaur
OSE f o r t h e Atlas/Centaur launched
launched t e s t i s p resen ted i n P a r t 111. I n o r d e r t o avoid r e p e t i t i o n ,
t h e OSE des ign f o r each of t h e s e t e s t f l i g h t s i s d e f i n e d a s excep t ions
t o t h e 1971 miss ion OSE des ign def ined i n D2-82709-3.
The OSE d e s i g n phi losophy f o r t h e 1969 t e s t f l i g h t i nvo lves t h e use of
1971 miss ion OSE w i t h minimum modif ica t ion . The employment of 1971 OSE
concep t s , t echno log ie s and equipment f o r t h e 1969 t e s t w i l l a ch ieve
improved p r o b a b i l i t y of 1971 mission success by a ) provid ing v a l i d a t i o n
of d e s i g n s and s p e c i f i c hardware through a c t u a l u se under miss ion con-
d i t i o n s ; b) i d e n t i f y i n g s p e c i f i c problem a r e a s f o r c o r r e c t i o n ; and c )
deve loping procedures , and personnel s k i l l s p r i o r t o t h e 1971 miss ion
ope ra t ion .
c
CONTENTS
PART II OSE FOR ATLAS/CENTAUR LAUNCHED 1969 TEST FLIGHT
II 1.0
II 1.1
II 2.0
II 2.1
II 2.2
II 2.3
II 3.0
II 3.1
II 3.2
II 3.3
II 3.4
II 3.5
II 3.6
OSE OBJECTIVES AND DESIGN CRITERIA I
SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA I I
OSE DESIGN CHARACTERISTICS AND RESTRAINTS
OSE SEQUENTIAL FLOW CHART
I
FUNCTIONAL DESC
MDE FUNCTIONAL DESCRIPTION
LCE FUNCTONAL DESCRIPTION
STC FUNCTIONAL DESCRIPTION
[ON - SYSTEM W E 1 O S
I
AHSE - SYSTEM LEVEL
SPACECRAFT SIMULATOR
SPECIAL SYSTEM LEVEL OSE, FUNCTIONAL DESCRIPTIONS
II 3.6.1 Functional Descriptions of the Trend Data Equipment
II 3.6.2 Magnetic Mapping Equipment, Functional Description
II 3.7
II 4.0
II 4.1
II 4.2
H 43 II 4.4
II 4.5
II 4.6
II 4.7
EQUIPMENT LIST
SYSSYSTEM TEST WuwlMcwT TELECOMMUNICATIONS SUBSYSTEM OSE
POWER SUBSYSTEM OSE
? R V ? t m l O N ~ ask ENGINEERING MECHANICS
SPACE SCIENCE OSE
ATTITUDE REFERENCES AND AUTOPILOT OSE
CENTRAL COMPUTER AND SEQUENCER (CCW OSE
5 1
D2-82709-5 . U
PART 11 OSE FOR ATLAS/CENTAUR LAUNCHED 1969 TEST FLIGHT
. I1 1.0 OSE OBJECTIVES AND DESIGN CRITERIA
Th i s s e c t i o n of t h e document r eco rds t h e o b j e c t i v e s and des ign
c r i t e r i a t h a t apply t o t h e o p e r a t i o n a l suppor t equipment (OSE) f o r
t h e 1969 t e s t s p a c e c r a f t launched by t h e Atlas/Centaur.
D e f i n i t i o n s of t h e v a r i o u s r e q u i r e d c a t e g o r i e s of OSE a r e i d e n t i c a l
t o t h o s e i n Sec t ion 1.0 of D2-82709-3 except t h a t :
t h e Sc ience Package, o r t h e F l i g h t Capsule do no t apply; 2 ) Refer-
ences t o t h e P l a n e t a r y Veh ic l e where used i n t h e sense of t h e u l t i -
mate f l i g h t a r t i c l e app ly t o the t e s t f l i g h t s p a c e c r a f t .
1) References t o
I1 1.1 SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA
The primary o b j e c t i v e of t h e o p e r a t i o n a l suppor t equipment (OSE) f o r
1969 t e s t f l i g h t i s t h e enhancement of t h e p r o b a b i l i t y of success f o r
t h e Voyager 1971 mission.
t h e 1969 t e s t s p a c e c r a f t a r e i d e n t i c a l t o t h o s e l i s t e d i n D2-82709-3,
Paragraph 1.1.
Addi t iona l OSE o b j e c t i v e s i n suppor t of
, I1 2.0 OSE DESIGN CHARACTERISTICS AND RESTRAINTS
The OSE des ign c h a r a c t e r i s t i c s and r e s t r a i n t s f o r t h e Voyager-71
mis s ion , noted i n Sec t ion 2.0 of D2-82709-3, app ly t o t h e Atlas/Centaur
launched 1969 t e s t s p a c e c r a f t except a s noted below.
All r e f e r e n c e s i n S e c t i o n 2.3 o f D2-82709-3 t o t h e Science Package o r
t h e F l i g h t Capsule, o r t o any ope ra t ions invo lv ing o r r e s u l t i n g from
11-1
D2 - 82 709-5
assembly o r i n t e g r a t i o n of t h e s e u n i t s w i t h t h e s p a c e c r a f t bus i n t o a
P l a n e t a r y Vehicle , a r e no t a p p l i c a b l e . Where used i n t h e sense of t h e
u l t i m a t e f l i g h t a r t i c l e , t h e term IIPlanetary Vehicle" i s changed t o
r ead "1969 Test F l i g h t Spacec ra f t .'I
I1 2.1 OSE SEQUENTIAL FLOW CHART
The process ing of t h e f l i g h t hardware f o r t h e 1969 t e s t f l i g h t space-
c r a f t and t h e r e l a t e d 1969 PTM t e s t a c t i v i t i e s a r e e s s e n t i a l l y t h e
same a s t h o s e shown i n t h e flow c h a r t of D2-82709-3, F igure 2.1-1 and
t h e a n a l y s i s m a t r i c e s of F igu res 2.1-2 through 2.1-6.
d u p l i c a t i o n o f t h e k inds of t e s t s and t h e i r sequencing i s s i g n i f i c a n t
t o p roof ing o r v a l i d a t i o n of t h i s p rocess ing f o r t h e 1971 miss ion
f l i g h t hardware process ing .
I n f a c t , t h e
The d i f f e r e n c e s i n f low t h a t a r e a consequence of d i f f e r e n c e s i n t e s t
f l i g h t c o n f i g u r a t i o n requi rements a r e a s fo l lows :
1) Test and o p e r a t i o n s a c t i v i t i e s f o r t h e c a p s u l e , s o l i d motor, and
s c i e n c e package a r e d e l e t e d f o r t h e At las /Centaur launched t e s t
f l i g h t s p a c e c r a f t .
The mission p r o f i l e i s a Mars f l y b y r a t h e r t h a n a Mars o r b i t a l
f l i g h t .
2 )
I1 2.2 OSE DESIGN PARAMETERS
OSE d e s i g n parameters f o r t h e Atlas/Centaur launched 1969 tes t f l i g h t
a r e t h e same a s t h o s e d e f i n e d f o r t h e 1971 miss ion i n D2-82709-3,
Sec t ion 2.2, Tab le s 2.2-1 through 2.2-4, w i t h t h e fo l lowing excep t ions :
1) Launch Pads 36A and 36B a r e used i n s t e a d of Pads 34 and 37.
V
c
11-2
L
BO€/N&
D2-82709-5 . 2) Two f l i g h t - r e a d y T e s t F l i g h t S p a c e c r a f t s h a l l be made r eady f o r
each launch, one on each launch pad. A t e s t model w i l l be used
a s a sou rce of f l i g h t accep tab le s p a r e s .
The term "P lane ta ry Vehicle" i s r e p l a c e d by "Test F l i g h t
s p a c e c r a f t . "
3)
I1 2.3 OSE DESIGN CRITERIA
OSE des ign c r i t e r i a f o r t h e Atlas/Centaur launched 1969 t e s t f l i g h t
a r e i d e n t i c a l t o t h o s e d e f i n e d f o r t h e 1971 miss ion i n D2-82709-3,
Paragraph 2.3.
I1 3.0 FUNCTIONAL DESCRIPTION - SYSTEMS LEVEL
Func t iona l d e s c r i p t i o n s f o r system l e v e l OSE f o r t h e Atlas/Centaur
launched 1969 t e s t f l i g h t a r e i d e n t i c a l t o t h o s e noted f o r t h e Voyager '71 miss ion
a s d e f i n e d i n Sec t ion 3.0 of D2-82709-3, excep t a s noted i n t h e follow-
i n g s u b s e c t i o n s .
I1 3.1 MISSION DEPENDENT EQUIPMENT (MDE) FUNCTIONAL DESCRIPTION
The f u n c t i o n a l d e s c r i p t i o n s of MDE noted i n Sec t ion 3.1 of D2-82709-3
a p p l y t o t h e 1969 t e s t f l i g h t with t h e fo l lowing excep t ions desc r ibed
below and i n d i c a t e d on Figure 3.2-1.
The so f tware used a t t h e DSIF and t h e SFOF has t h e c a p a c i t y t o p rocess
a g r e a t e r amount of eng inee r ing d a t a but need no t have t h e c a p a c i t y t o
p r o c e s s capsu le s c i e n c e d a t a .
t h e DSIF a r e reduced.
Q u a n t i t i e s of MDE hardware r e q u i r e d a t
11-3
\
.
4- CENTAUR
TELEMETRY
1969 UMBILICACSET MAY BE DIFFERENT LENGTH THAN SET PROVIDED FOR T C 1 7 1 A IHL 19, I rdlltlSSiON r
SPACE VEHICLE
CENTAUR
I - 7; TO AF-ETR I I VHF i FACILITIES I I
I-+ I I I I I I I I I I I I I I I I I I I I I
I I I I I I I I I I I I I I
PLAN ET A RY VE H
P/V STATUS LAUNCH 0 LAUNCH0
P/VPOWER I TIME 4321
---------
I
I . .
PROVI
D2-82 709-5
'
DATA PROCESSOR
FORMATTING UNIT AND
CONSOLE AND SUBSYSTEM MONITOR PANELS ARE MODIFIED FOR 1969 TEST FLIGHT BY SUBSTITUTION OF BLANK PANELS AND/OR INTER- CHANGEABLE PLUG-IN IDENTITY CARDS AND DISPLAY MODULES
EQUIPMENT ITEMS SUBJECT TO TANT OPERATOR CONTROL G OPERATIONS VEHICLE SUBSYSTEM
15 ORDNANCE
CAPSULE ORDNANCE CONT. 0 0 NOSE FAIRING CONT. 0 0
I I I I I I I I I I I
iX EQUIPMENT (PAD)
'e 3.2-1: Voyager OSElLCE Launch-Pad Operations - LCE Variat ions for 1969 Fl ight Test
7
D2-82709-5
I1 3.2 LAUNCH COMPLEX EQUIPMENT FUNCTIONAL DESCRIPTION
The LCE f o r t h e 1969 t e s t f l i g h t w i l l be t h e same a s t h a t desc r ibed
i n Sec t ion 3.2 o f D2-82709-3 f o r t h e 1971 Voyager miss ion , except a s
noted b e l ow.
1 ) Programming ( so f tware ) f o r t h e d a t a p rocesso r and fo rma t t ing
u n i t i s provided s p e c i f i c a l l y f o r t h e 1969 f l i g h t t e s t .
2) The P l a n e t a r y Vehic le monitor console a s planned f o r 1971 i s
used f o r t h e 1969 t e s t f l i g h t . Engineer ing f l i g h t d a t a d i s -
p l a y i n c r e a s e s a r e accommodated by t h e u s e of module l o c a t i o n s
made a v a i l a b l e by t h e d e l e t i o n of t h e s p a c e c r a f t s c i ence pay-
load and capsu le measurement requi rements and t h e r e d u c t i o n i n
s p a c e c r a f t power moni tor ing requi rements . S u b s t i t u t i o n s of
a p p r o p r i a t e l y engraved p l a s t i c f u n c t i o n i d e n t i t y c a r d s on t h e
conso le f r o n t p a n e l s and in t e rchangeab le plug-in s t anda rd numeric
modules and s t a n d a r d s t a t u s modules w i l l be made t o accommodate
t h e a d d i t i o n a l eng inee r ing da ta d i s p l a y s . The q u a n t i t y of added
eng inee r ing d a t a d i s p l a y s i s l i m i t e d t o t h e number of f u n c t i o n s
d e l e t e d from subsystems monitor p a n e l s having reduced o r d e l e t e d
requi rements f o r monitor d i sp l ays .
The Sc ience Payload and Capsule Subsystem Monitor Pane l s a r e 3)
blanked a s r e q u i r e d where subsystem f u n c t i o n s a r e d e l e t e d , o r
eng inee r ing measurements fo r o t h e r subsystems a r e d i sp l ayed
i n t h e s e Panels .
4) Monitor f u n c t i o n s e l imina ted by t h e d e l e t i o n of one of t h e t h r e e
s p a c e c r a f t b a t t e r i e s i n t h e Power Subsystem w i l l be blanked o u t
on t h e Power Subsystem Monitor Panel . The Module space on tne
11-7
BnE0W.G
D2-82709-5
PV Monitor Console i s a v a i l a b l e f o r a d d i t i o n a l eng inee r ing
d a t a d i s p l a y s .
The phys ica l l e n g t h of t h e umbi l i ca l h a r d l i n e s may r e q u i r e change
bu t t h e b a s i c c o n f i g u r a t i o n f o r 1969 i s t h e same a s f o r 1971 and
t h e e l e c t r i c a l impedance i s r e q u i r e d t o match 1971 c o n f i g u r a t i o n .
5 )
The mod i f i ca t ions provided f o r t h e Atlas/Centaur launched 1969 t e s t
f l i g h t do not a f f e c t e v a l u a t i o n of LCE performance s u i t a b i l i t y f o r Voy-
a g e r 1971 mission.
I1 3.3 STC FUNCTIONAL DESCRIPTION
The STC f o r t h e Atlas/Centaur launched 1969 t e s t f l i g h t i s i d e n t i c a l
i n des ign t o t h a t desc r ibed f u n c t i o n a l l y i n S e c t i o n 3.3 of D2-82709-3
f o r t h e 1971 miss ion , except t h a t t h e s p e c i f i c equipments r e q u i r e d t o
permi t t e s t i n g wi th t h e F l i g h t Capsule and t h e Sc ience Package i n s t a l l e d
o r s imula ted a r e n o t i n s t a l l e d . Space, power and environmental c o n t r o l
p r o v i s i o n s are , however, i nc luded t o permi t i n c o r p o r a t i o n of t h e above
t e s t equipment items w i t h minor rework.
I1 3.4
The f u n c t i o n a l d e s c r i p t i o n s o f system leve l AHSE f o r t h e Atlas/Centaur
launched 1969 t e s t f l i g h t a r e a s d e s c r i b e d i n D2-82709-3, S e c t i o n 3.4
w i t h t h e fo l lowing excep t ions .
t h e OSE a r e :
1) a ) No VHF antenna ,
ASSEMBLY, HANDLING, AND SHIPPING EQUIPMENT (AHSE) -- SYSTEM LEVEL
Spacec ra f t s t r u c t u r a l changes a f f e c t i n g
b ) e i g h t f o o t p a r a b o l i c high-gain a n t e n n a ,
11-8
D2-82709-5 . . c ) modified high-gain antenna suppor t s t r u c t u r e ,
d)
These changes a f f e c t a ) t h e mechanism deployment t e s t s t a n d ,
reduced and r e o r i e n t e d s o l a r panels .
b) t h e magnetic mapping t e s t s t a n d , and c ) a l ignment s t a t i o n s .
E l imina t ion o f c a p s u l e and sc i ence payload d e l e t e s requirement
f o r t h i s AHSE.
The s m a l l e r Atlas/Centaur nose f a i r i n g r e q u i r e s changes o f t h e
2)
3)
e n c a p s u l a t i o n a r e a p l a t f o r m set , and new AHSE i n l i e u o f s i m i l a r
equipment f o r t h e S a t u r n IB/Centaur c o n f i g u r a t i o n , a s fol lows:
a ) Acoust ic Test F i x t u r e
b)
c )
T e s t Stand - Spacecraft/Nose F a i r i n g S e p a r a t i o n
Test F i x t u r e - Antenna Range and E 1 T e s t
c ) T r a n s p o r t e r , Encapsulated F l i g h t S p a c e c r a f t
e ) Access Equipment
f ) Simulated Nose F a i r i n g
g ) Encapsulated i n Nose F a i r i n g S p a c e c r a f t L i f t i n g F i x t u r e
h )
i )
Changes t o t h e p ropu l s ion module a l lows d e l e t i o n o f t h e r o c k e t
S p a c e c r a f t t o Launch Vehicle I n s t a l l a t i o n K i t
Nose F a i r i n g t o Spacec ra f t I n s t a l l a t i o n K i t
4)
motor a l ignment f i x t u r e and r e q u i r e s modif ied equipment d e s i g n s
as fol lows: ( a ) p o r t a b l e b l a s t b a r r i e r and ( b ) p r o p e l l a n t s h i e l d s .
5) The u s e of AFETR launch pad 36 r e q u i r e s minor m o d i f i c a t i o n s t o t h e
hand l ing , a c c e s s and c e r t a i n s a f e t y AHSE used a t t h e pad.
11-9
A?n€/.G
D2-82 709-5
I I 3.5 SPACECRAFT SIMULATOR
The Spacec ra f t S imula tor f o r t h e Atlas/Centaur Launched 1969 t e s t f l i g h t
w i l l be t h e same a s t h e 1971 s p a c e c r a f t s i m u l a t o r (Reference D2-82709-3,
Sec t ion 3.5) w i t h t h e fo l lowing except ions :
1) There need be no p r o v i s i o n s f o r i n t e r c o n n e c t i n g t h e F l i g h t Capsule
Simulator o r t h e Sc ience Payload Simula tor .
The 1969 Simula tor w i l l be des igned t o i n t e r f a c e w i t h AFETR
launch complexes 36A and 36B.
2)
I1 3.6 SPECIAL SYSTEM LEVEL OSE, FUNCTIONAL DESCRIPTIONS
This equipment i n c l u d e s t h a t f o r t r e n d d a t a a n a l y s i s and t h a t f o r magne-
t i c mapping.
I1 3.6.1 Funct ion D e s c r i p t i o n s of t h e Trend Data Equipment
Th i s ca tegory of OSE i s i d e n t i c a l t o t h a t d e s c r i b e d i n 3.6.6 of D2-82709-3
except f o r d i f f e r e n c e s i n so f tware r e s u l t i n g from t h e e l i m i n a t i o n s o f t h e
VHF r a d i o and antenna o r b i t i n s e r t i o n s o l i d r o c k e t motor, t h e F l i g h t Cap-
s u l e , t h e Science Package and t h e minor d i f f e r e n c e s i n t h e S p a c e c r a f t bus.
I1 3.6.2 Maqnetic Mappinq Equipment Func t iona l D e s c r i p t i o n
Th i s equipment i s i d e n t i c a l t o t h e magnetic mapping equipment d e s c r i b e d
i n 3.6.2 except f o r t h e d i f f e r e n c e s i n s u p p o r t i n g AHSE d e s c r i b e d i n 3.4
of t h i s document.
I1 3.7 EQUIPMENT LIST
The system l e v e l OSE equipment r e q u i r e d f o r t h e 1969 Voyager t e s t f l i g h t
u s ing t h e Atlas/Centaur l aunch v e h i c l e i s l i s t e d i n t h e fo l lowing t a b l e s .
11-10
D2-82709-5 I -
~ I The listing is tabulated by category, and an identification number is
assigned to each item. This identification number also relates the
item to the subsection of Section 3 which describes the equipment
category. Use assignments for each item are indicated by an "X" in
the appropriate column.
at a later point in the program.
Space is provided to add equipment quantities
,
I 14 1
h
c,
D2-82709-5 -
x x x x
x X x x x x x x x x x x x x
x X x x x x x x x x x x x
x X x x x x x x x x x x x
$Q X x x x x x x x x x x x
x X x x x x x x x x --
x X x x x x x x x x x x
X X x x x x x x x x x x x x x x x x
k a, N .rl C 0 k
C b v)
c, .rl
5:
m n
k 0 4 m 4 2 a 0
CI k k a l o
.rl c, k 0 k = I m k Oc, acn 2 c v ) o
0 ala, -PIX m l x m
c, + m
m c c c n m X
2
.rl n m
.rl
k a, N
.rl c 0 k c 0 C r v)
c, .rl m
h
k 0 c, m -4 2 a 0
2 k O ac,
.rl v k 2 k k mc, 0 c n a c 2 0 m v
a, al& c, m m lxc, m + a m - o .rl
C z m l-l
k a, N .rl C 0 k c 0 C $. 0
a,
k c4 a C m k 0 c, 0 c,
2
$ 0 0 al
k a, c, cn
n
r"
k al N .rl C cn 0 0 a,
k l x 0 c , 0 m c c , b
v)
0 8 o m a , k
m a c , + m
0 0 , c c .rl .rl k k a l a , a l a , c c .rl .rl c n m c c w w
g a l
a h
S a
k a, N .rl C cn 0 0 a, lx 0 C $. v)
al
k %I a
s 3
a m c, m
0, C .rl k al a, C
.rl 0, C w
al k m 3 c, %I
63 0 CJ m
i v
k 0
cn
- a, k m c, +I 0 v)
0 CJ m
L
; W
k 0 cn cn a, 0 0 k a c 0 .d In cn .rl
C m k I- a C
5
i-?l 0 u
a, k 0 L c, * 0 v)
0 CJ m m 8 W
k 0 u) cn a, 0 0 k a a m k I- c, 2 a C H
A
a, k m 3 c, +I 0 I/)
0 01 m v)
8 v
k 0 cn cn al 0 0 k a x k c, a, 2 -4 a, t-.
- al k 0 3 c, +I 0 m 0 CJ m
; v
k 0 v) cn a, 0 0 k a c, 2 a
2
k a, a 0 0 a, a 24 0 0
G -4 m C 0 cn 0 G c, k
4 .I+ m dl k 0 c, m 4 2 -a 0
a k al
.rl k k 0 0 sl 7 v)
2
- al k a 4 rcl
3
0 k v ) 0
CI
al k
c, +I
0 v)
d d 0
B
2 d 0 r v
k 0 In cn a, 0 0 k a c, 2 z1 c, 2
m a r c 0 4 4 4 4
- 4 4 - 4 - 4
m m m m
11-12
Bm..iNG
D2-82709-5
H
x x x x x x x x x
x x x x x x x x x
- a, k m 3 c, +I 0 v)
d d 0 s d 0 P
k 0 v) v) al 0 0 k a
v
L- $ c, al
4 (E I-
n a, k m 3 c, +I 0 v)
d 6 0 P
s W
k 0 v) v) a, V 0 k D.0
c, 2 2 H
- a, k m 3 c, +I 0 v)
d 6 0 b
5 H
k 0 v) v)
a, 0 0 k a r k t' a,
U
2 4 a1 I+
n a, k m 3 c, rcr 0 cn d- D 0 F
z H
k 0 u) u) a, 0 0 k a c, 2 a c,
U
a, k m 3 c, +4
0 v)
k 0 m u) al V 0 k a -0 c m
0 u 0 d 0 b
U
s
55 H
- a, k m 3 c, rcr 63 d 6 0 P
5
: H U
k 0-l 0 k a v)
.rl v) r 4 m C 4 c c, ([I a c, c u, .rl
2
- a, k m 3 c, rcr 0 v) v
4 0 k c, C 0 u -0 c m C 0
.rl c, i-0 k UI a, c, c H
c 0
.r( u) v)
.rl P
11-13
D2 -82 709-5
x x x x x x x x x x x x x x x x x x-_--x
x x x x x x x x x x x x x x x x x x x
x x x x x x x x x x x x
x x x x x x x x x x x x x x
I, .d c 3 m c .d
c, 4 3 v)
k a, 3 0 a a C 3 0 k c3
.do
c, .d c 3 m
k C
c 3 L
rl m 0
c, a, v)
4 m 0
.d rl Q
9 k a,
.d
5 c m k I-
: .d a, 0 a, a:
m l-l
Lr, 3: > k
m CI L 3: > k
k 0 v) (0 a, 0 0 k
a, rl 0 u) c s rl 0 k c, C s a, -0
2 a k 0 0 a, a:
a, rl 0 v) c 0 0 k 0 c, .d C 0 z a, 4 0 2 > > k 0 c, a, C m 4 a
n
8 v)
rl a, C m a k 0 c, .d C
W
8 g c, v) > v) a 3 v)
0 .d m m a:
a, 0, m k 0
t; m c,
2 v)
a, 0
$ v)
m C C a, c, c a
C a, k a, * a, a: a, m 3 c, c, c, a
.d
a (0 0 4 > m a a, 0 C a, .d 0 v)
11-14
z E * w o
D2-82709-5
x x x x x x x x x x
x x x x x x x x x x
x x x x x x x x x x x
x x x x x x x x x x x
X
a m c a, .d
n a, k m 3 c, rcI 0 v)
k a, c, c,
v
2 0
0 u)
v ) o ::
0 a , k
. . 4 a m u
k a m x c a, .rl 4 + a v
.rl a,
0 c v C k a , a , + c , c c < H
$ e c
c, .rl c 3 m c
.rl c 0 .d c, .rl W c 0 u k
4 a, 4 a rn c, k 0 a
.rl
W u I 4
m c .rl 4 a ra u 0, c .d c, 0 a, c c 0 V k a, + c H
n
c, .d e 3 m c
.rl 4 0 0 u a, 4 a m + k 0 a
- k P .d P 07a,
.rl 0-m 4 a, .rl a k > a 0 2 x a, -+ a m 0
a,c
A
11-15
A?n€.NG
D2-82709-5
a, 4
~ x x x x x x x x x x x x x x x
x x x x x x x x x x x x x x x x
k a, c, C
- k a , & k m a 3 c
+ m +I k o r a , m m a
k - 4 k n o
m m a t x k k c n c n m m o o * * k m
.d
2 g . z :
a k d a
5 c, u) r v)
cn c .d 4 0 0 u a C 0
a, k 7 c, 0 7 k c, v)
& 0 m CI:
m C .rl k .d E 4 m 0 .d k c, 0 a, 4 W
a C m n
5 c, u) r v)
k a,
a 4: V m tx
z
k 0 c, (0 4
2
2
.d v)
a, 4
a m u c, r: cn .d 4 L
k 0 u) u) a, 0 0 k a 24 C .d 4 m c, 2 k 7 m c, c a, u
cn a, 4 Q m u 4 m C k a, c, x W
n cn c, C a, C 0 a
u 2
E v
u) C 0 .d c, m 0 .d C
i! 0 V a, .-I a,
t+
n cn c, C a, C 0 a
u u
5
G
z W
k a,
a 0 .rl k c, 0 a, 4 W
n cn c, C a, 0 a
u u b v)
k a, 0 C a,
a, v)
a C m k a, c, 7
0 u 4 0 k c, C a, u
2
v
s
2
n u)
c, C a, C 0 a
u u 5
G W
c, 0 4 .d a 0 c, 3
a c m
+I
al tx a, a 7 c, .d c, c, 4
a
- cn c, C a, C 0 a
u u G v
4 0 k c, C 0 u a, k 7 c, m k a, a 5 7 5
r"
cn
.d c m c 0
!2 - k 0 > +I
.,-l cn c,
W k m
k 0
0 a, 01 cn m m
I u)
7 C .d
g
-5
; v
s 2 In
k al c, 0 7 c a u)
u
11-16
D2-82709-5
~
c
m
X
X
W
z 0
t- X 0
X
cl 4 0 W
X
x x x
x x X x x
x x x x x x x x x x x x
n 5 iu z
n P a,
.A rcI 4 P
r" m a m 4
n v) k a, c, a m P m u) u) a, 4
C 0 .d c, m c, m c, c
W
W
5 [r .d 4 4
U
P c m c, m c, u) a, b a, a 0 2 a, a, k !A
a, k 7 c, X .d c4 -I-' u) a, b
C 0 .d c, m k m a a, m 0, c .d k .d m c4 a, v)
> rcI rn k 0 a, 0 m a m
P c m c, m c, (0 a, t- a, c 0 c, v) a 4 s
n 3 a, z m a m 4
a, k 7 c, X .d L
c, u) a, t- H W
a c m a, cn c m a: m c c a,
c
W
a
n
5 z m a o\ 4 v
a, k 7 c, X
;4" c, u) a, k 0 .d + (0
7 0 0 a
n P a, v) .d
5 a: m a m 4
a c m c, m -I-' u) a, k rn c .d a a
W
r" 0 .d c, a, c cn 2
m a m 4 v
4 rcI m k V a, 0 m a m c, c r n .d 4 L
a a, c, m 4
a m V
W
c, k 0 a u) c m k b
z
h
k a, c, k 0 a u) c rn k t- c, a, m
w 0 a, c, .d m a, c, 0
a: 2
k a, c, k 0 a u) c m k b W C.7 0
11-17
X b v)
x x x
D2 - 82 70 9-5
W z - u
a 4
V
x x X c3 x x X X
X X X X
x x x x x X X X X
- -0 a, u) .d
5 a: m \o m 4
k a,
.rl k k
V
8
- -0 a, u)
.rl
2 lx (r a 0 4 V
c, a, v)
5 0 q, c, m 4 a m a, k 4 C 0
.rl c, ([I 4
Q (11 0 C W
2
c, a, v)
E k 0 +I c, m 4 a m a, k U a, 0 c m 4
m" '=. c m
.rl
CI
w l 4 rl
c, C
Q .rl 3 W W u) u) a, 0 0 4 c 0 .d c, m 4 4 (11 c, u) c H
4 m 0 .d 4 .I+
v
A E 3
c, C a,
Ea .d 7 W W u) u) a, 0 0 U a, m ([I v) 3 k 0 c, m 4
2 .rl I/)
c, C a,
5 s .d
W v) u) a, 0 0 4 C 0 .d -e, ([I k a, a 0
H 0
.
11-18
BoE/AI%
D2-82 709-5
c
x x x x x x x x x x
x x x x X x x X X
x x X x x x x x X x x x
m c, C a, c 0 Q
u k a, 0, m r 0 > k 0 rc,
r 4 4 0
a, cn 0 a k 7 a 4 m k a, C a, U
s
n
a, 0 .d
5 n c 0 .d c, m 4 4 m c, cn c H
cn c, C a, C 0
0 u c, 4l m k 0 a, 0 m a 10
3
k a, > u" a, ? .d c, 0 a, c, 0 k a m a, k 4 u h 0)
k Q)
u a, > .I4 -P 0 a, -P 0 k a a, C 0 -P cn a d 0 U
2 cn s 0 0: c m a, 4 u a, 4 a m c, k 0 a
- a a, (0
.rl
5 E m \o m r( v
cn a, 0 .d
5 a a, > .d c, 0 a, c, 0 k a cn C .d 4 a, 2 c4
k a,
u a, 0, a k 0
$ h 0
U k 0 a cn c a h b
cn a, k 7 cn 0 4 0 cn c cr: W W z c 0 .d c, m N u .ti 4 U .d k a, a c, a 32
2 i5
E
8
k a, C
a, u) 0 z sz 4 .d E
.d c, m rc, m
c, rc, a k 0 a, 0 0 Q v)
c, c 0,
.r(
cj
4 a, > a, cl
5 c, cn r v)
k 0 rc,
c, a, v)
0, c .d 4 10
0 d d m
11-19
D2 -82 709-5
c)
t;
H
X
X X
X x x
X x x
X x x x x
t, a, m C 0 .d t, m d 4 m t, u) C H
a C m Cn C
.rl t, +l
.rl 4 W v) 0
t, .d x a, 4 0 .d c a, 5
5 c 3 m 4 0 t,
t, +l m k 0 6, 0 m a v)
t, +l tu k 0 6, 0 m a m 0 4
m c .rl k .d m c4 a, u) 0 z
4 .d x k 6, t, a m a 4 s x 0 t,
t, s m .d 4 c4
In b
d m
11-20
. I
-
.. I
c
k 3 m -+
w c ua, l-lu ->
D2 -82 709-5
x x x x x
x x x x x
k a, c, 4 0
7 l a >
I X
4
\o
+ a, 0 0 v) 0 3: cn C .d C 0 .d + .d a C 0 u k
.A 4
k a, 4
0 4 a, C cn 2 0 c, m cn x 3 rl c4
a, k 3 c, x L
cn C .d a Lz
.rl
2 4 0 C m a k m rl
6
k 0 + 0 rl 3 E .d cn rl rl a, u k m 7 4 0 v)
BDE2N.E
D2-82709-5
I1 4.0 SUBSYSTEM TEST EQUIPMENT
I1 4.1 TELECOMMUNICATION SUBSYSTEM OSE
The te lecommunicat ions OSE f o r t h e 1969 t e s t f l i g h t launched by t h e
Atlas/Centaur i s i d e n t i c a l t o t h a t d e f i n e d f o r t h e 1971 mission i n
D2-82709-3, Paragraph 4.1, w i t h t h e fo l lowing except ions :
1) The r e l a y r a d i o subsystem t e s t s e t and t h e r e l a y r a d i o subsystem
sh ipping c o n t a i n e r w i l l n o t be r e q u i r e d because t h e Capsule i s
n o t inc luded i n t h e t e s t f l i g h t s p a c e c r a f t c o n f i g u r a t i o n .
I n conduct ing subsystems i n t e g r a t i o n t e s t s , a s t a n d a r d d i g i t a l
s i g n a l w i l l be used a s an i n p u t t o t h e T/M and d a t a s t o r a g e sub-
system.
a VHF t e s t s i g n a l i n t o t h e r e l a y r a d i o subsystem v i a t h e VHF
an tenna .
The component mounting i n t e r f a c e mock-up w i l l be modif ied by t h e
omission o f t h e c a b l e connec tors f o r i n t e r f a c e between t h e T/M
and d a t a s t o r a g e subsystem and t h e r e l a y r a d i o subsystem.
2)
Th i s d i f f e r s from t h e 1971 i n t e g r a t i o n tes ts which i n p u t
3)
I1 4.2 POWER SUBSYSTEM OSE
The power subsystem OSE f o r t h e 1969 t e s t f l i g h t , launched by t h e At l a s /
Centaur , i s i d e n t i c a l t o t h a t de f ined f o r t h e 1971 miss ion i n D2-82709-3,
Paragraph 4.2, excep t t h a t minor changes i n AHSE a r e r e q u i r e d t o provide
c o m p a t i b i l i t y w i th t h e r e v i s e d mounting p r o v i s i o n s on t h e s o l a r pane l s .
The 1971 OSE des ign p rov ides adequate f l e x i b i l i t y t o handle t h e At l a s /
Centaur launched t e s t f l i g h t s p a c e c r a f t power subsystem des ign . Changes
11-22
D2-82709-5 . *
i n t h e t e s t f l i g h t power subsystem from t h e 1971 des ign inc lude :
a ) I n c r e a s e i n eng inee r ing d a t a used t o monitor s p a c e c r a f t power
subsystem performance.
b)
c ) Decrease i n t h e number of s o l a r panel s t r u c t u r a l s e c t i o n s from
Decrease i n s p a c e c r a f t b a t t e r i e s from t h r e e t o two.
s i x t o t h r e e .
c I t i s planned t h a t no a d d i t i o n s w i l l be made t o t h e 1969 power sub-
system OSE f o r t h e 1971 miss ion except i n t h o s e c a s e s where t h e 1969
t e s t h a s i n d i c a t e d a need f o r improvement.
I1 4.3 PROPULSION SUBSYSTEM OSE
The p ropu l s ion subsystem OSE f o r t h e 1969 t e s t f l i g h t , launched by
t h e Atlas/Centaur , i s i d e n t i c a l t o t h a t d e f i n e d f o r t h e 1971 miss ion
i n D2-82709-3, Paragraph 4.3, except a s no ted below.
The 1969 t e s t f l i g h t w i t h t h e Atlas/Centaur does n o t i n c l u d e an o r b i t
i n s e r t i o n maneuver. The d e l e t i o n of t h i s requi rement e l i m i n a t e s t h e
requi rement f o r t h e o r b i t i n s e r t i o n s o l i d r o c k e t motor and r educes t h e
p r o p e l l a n t requi rements i n t h e midcourse and o r b i t t r i m l i q u i d r o c k e t
system.
The d i f f e r e n c e s i n t h e 1969 Atlas/Centaur and 1971 Voyager p ropu l s ion
system r e s u l t i n t h e fo l lowing o p e r a t i o n a l suppor t equipment d i f f e r e n c e s :
1)
2)
Delete requi rement f o r rocke t motor t r a n s p o r t e r .
Delete requi rement f o r TVC Freon s e r v i c i n g u n i t .
11-23
D2-82709-5
The remaining o p e r a t i o n a l suppor t equipment must be capable of handl ing
a s m a l l e r module w i t h reduced p r o p e l l a n t and p r e s s u r a n t l oad ing r e q u i r e -
ments.
While t h e above noted OSE d i f f e r e n c e s e x i s t , t h e 1969 tes t f l i g h t w i l l
s t i l l be h i g h l y d e s i r a b l e i n e v a l u a t i n g t h e p ropu l s ion OSE i n a r e a l -
i s t i c environment.
I1 4.4 ENGINEERING MECHANICS
The Mechanisms, Packaging 8, Cabl ing , Temperature Cont ro l and Pyro techn ics
OSE f o r t h e Atlas/Centaur launched 1969 t e s t f l i g h t i s i d e n t i c a l t o t h a t
d e s c r i b e d i n D2-82709-3, Paragraph 4.4 f o r t h e 1971 miss ion , excep t t h a t :
1) t h e requirement t o a l i g n t h e magnetometer i s e l imina ted , s i n c e t h i s
i n s t rumen t w i l l n o t be inc luded i n t h e s p a c e c r a f t ;
s c i e n t i f i c payload in s t rumen t s a r e removed from t h i s t e s t f l i g h t , t h e
2) because t h e
check o u t requi rements a s s o c i a t e d w i t h t h e d e l e t e d in s t rumen t i s elim-
i na t e d .
Although t h e number of py ro techn ic d e v i c e s a r e reduced on t h i s space-
c r a f t , dummy l o a d s a r e provided f o r each o f t h e d e v i c e s n o t i nc luded
and t h e complete f i r i n g sequence w i l l be s imula t ed .
.
The 1969 t e s t w i l l a f f o r d a n o p p o r t u n i t y t o o p e r a t e t h e OSE under a
r e a l i s t i c mission environment and a l l o w r e f i n e m e n t s and improvements
i n methods, p rocesses and t echn iques t o be i n c o r p o r a t e d i n t o t h e 1971 OSE.
Bn..lMG
D2-82709-5 . c
I1 4.5 SPACE SCIENCE OSE
The 1969 t e s t s p a c e c r a f t c o n f i g u r a t i o n launched by t h e Atlas/Centaur i s
d e f i n e d i n D2-82709-4, P a r t 11. As such i t c a r r i e s no s c i e n c e payload.
..
There fo re , no space s c i e n c e OSE i s r e q u i r e d f o r t h i s 1969 t e s t f l i g h t .
I1 4.6 ATTITUDE REFERENCES AND AUTOPILOT OSE
The a t t i t u d e r e f e r e n c e s and a u t o p i l o t OSE f o r t h e Atlas/Centaur launched
1969 tes t f l i g h t i s i d e n t i c a l t o t h a t desc r ibed i n D2-82709-3, Paragraph
4.6, excep t a s noted below.
1) S igna l Monitoring--The s i g n a l s appea r ing on t h e t e s t connec tor f o r
t h e 1971 mission w i l l be t e l eme te red on t h e 1969 mission. The mon-
i t o r i n g of t h e s e s i g n a l s by the OSE i s provided f o r i n t h e 1971 OSE
c o n f i g u r a t i o n f o r subsystems tests. I n t h e system t e s t complex,
t h e 71 c o n f i g u r a t i o n p rov ides d i r e c t connec t ion t o t h e t e s t connec-
t o r . I n t h e 69 c o n f i g u r a t i o n t h e s e s i g n a l s w i l l be monitored through
t h e t e l e m e t r y l i n k which r e q u i r e s an a d d i t i o n a l i n t e r f a c e between
t h e telecommunications OSE and t h e a t t i t u d e r e f e r e n c e and au to-
p i l o t OSE t o r ecove r t h e s e s i g n a l s .
i s recovered by t h i s l i n k a s shown i n Volume C, Paragraph 4.6.
The normal (71) t e l e m e t r y d a t a
2 ) Programming--The programming f o r bo th t h e l o c a l t a p e r e a d e r and r e -
mote computer w i l l be changed t o accommodate t h e moni tor ing of t h e
a d d i t i o n a l s i g n a l s th rough the t e l e m e t r y l i n k . Changes i n t h e pro-
gramming a r e a l s o r e q u i r e d t o be compatible w i t h t h e modified g a i n s
ir! t h e a u t o p i l o t , f o r A t l a s v e h i c l e i n e r t i a , and f o r e x e r c i s i n g t h e
acce le romete r s e l f - t e s t f e a t u r e .
11-25
A?n€lNG
D2-82 709-5
I1 4.7
The C e n t r a l Computer and Sequencer OSE f o r t h e 1969 t e s t f l i g h t ,
launched by t h e At las /Centaur , i s i d e n t i c a l t o t h a t de f ined f o r t h e
1971 mission i n D2-82709-3, Paragraph 4.7, excep t a s noted below.
CENTRAL COMPUTER AND SEQUENCER (CCSS) OSE
The major d i f f e r e n c e between t h e 1969 Atlas/Centaur launched t e s t
f l i g h t and t h e 1971 mission t h a t a f f e c t s t h e CCSS, i s t h e d e l e t i o n of
t h e F l i g h t Capsule i n t h e 1969 s p a c e c r a f t . E l e c t r i c a l i n t e r f a c e s
s i m u l a t i n g t h e F l i g h t Capsule t h a t w i l l be i n s t a l l e d i n t h e 1969 t e s t
v e h i c l e w i l l a l s o be s imula t ed i n t h e CC&S OS€.
t o program t h e CCSS OSE w i l l be modified t o r e f l e c t t h e 1969 t e s t
f l i g h t , i nc lud ing F l i g h t Capsule dummy l o a d s . Emphasis on r e a l t ime
command, command message v e r i f i c a t i o n and message e r r o r t e s t i n g p l u s
s t o r e d program sequencing v e r i f i c a t i o n i s planned u s i n g t h e CC&S OS€.
The t e s t t a p e s used
The CC&S 03E w i l l be capable of performing a l l i t s f u n c t i o n s t o a s s u r e
t h e complete f l i g h t r e a d i n e s s of t h e CCSS a s i n s t a l l e d i n t h e 1969 t e s t
v e h i c l e . The performance of t h o s e f u n c t i o n s w i l l a l s o o b t a i n maximum
b e n e f i t from t h e 1969 t e s t f l i g h t by a s s u r i n g a h igh degree of c o n f i -
dence f o r t h e 1971 mission.
I 1-26
i
CONTENTS I
PART 111 OSE FOR SATURN IB/CENTAUR LAUNCHED 1969 TEST FLIGHT ~
111 1 .O OSE OBJECTIVES AND DESIGN CRITERIA
111 1.1 SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA
111 2.0 OSE CHARACTERISTICS AND RESTRAINTS
111 3.0 FUNCTIONAL DESCRIPTION - SYSTEM LEVEL OSE
111 3.1 MDE FUNCTIONAL DESCRIPTION
111 3.2 LCE FUNCTIONAL DESCRIPTION
111 3.3 STC FUNCTIONAL DESCRIPTION
111 3.4 AHSE FUNCTIONAL DESCRIPTION
111 3.5 SPACECRAFT SIMULATOR
111 3.6 SPECIAL SYSTEM LEVEL OSE
111 4.0 SUBSYSTEM TEST EQUIPMENT
111 4.1 TELECOMMUNICATIONS
REACTtON CONTROL OSE
111 4.5 SPACE SCIENCE OSE 111 4.6
111 4.7
ATTITUDE REFERENCE AND AUTOPILOT
CENTRAL COMPUTER AND SEQUENCER (CC&S) OSE
I D2-82709-5 * .
PART I11 OSE FOR SATURN IB/CENTAUR LAUNCHED 1969 TEST FLIGHT
I11 1.0 OSE OBJECTIVES AND DESIGN CRITERIA
Th i s s e c t i o n of t h e document r eco rds t h e o b j e c t i v e s and des ign c r i t e r i a
t h a t a r e unique t o t h e o p e r a t i o n a l support equipment (OSE) f o r t h e 1969
t e s t s p a c e c r a f t launched by t h e Saturn IB/Centaur.
D e f i n i t i o n s of t h e v a r i o u s r equ i r ed c a t ( j o r i e s of OSE a r e i d e n t i c a l t o
t h o s e i n Sec t ion 1.0 of D2-82709-3, except t h a t : 1) References t o t h e
Sc ience Package, o r t h e F l i g h t Capsule, app ly t o t h e Simulated Sc ience
Package and t h e Simulated F l i g h t Capsule.
I11 1.1 SPACECRAFT SYSTEM OSE OBJECTIVES AND CRITERIA
The primary o b j e c t i v e of t h e o p e r a t i o n a l suppor t equipment (OSE) f o r
t h e 1969 t e s t f l i g h t i s t h e snhancement of t h e p r o b a b i l i t y of success
f o r t h e Voyager 1971 miss ion .
t h e 1969 tes t s p a c e c r a f t a r e i d e n t i c a l t o t h o s e l i s t e d i n D2-82709-3,
Paragraph 1.1.
Addi t iona l OSE o b j e c t i v e s i n suppor t o f
I11 2.0 OSE DESIGN CHARACTERISTICS AND RESTRAINTS
The OSE des ign c h a r a c t e r i s t i c s and r e s t r a i n t s f o r t h e Voyager '71
mis s ion , noted i n S e c t i o n 2.0 of D2-82709-3, a p p l y t o t h e Sa tu rn IB/
Centaur launched 1959 t e s t s p a c e c r a f t except a s no ted below.
111-1
Bn..fNB
D2-82709-5
A l l r e f e r e n c e s i n Sec t ion 2.0 of D2-82709-3 t o t..e Sc ience Payload o r
t h e F l i g h t Capsule apply t o t h e Simulated Sc ience Payload o r t h e Simu- I
l a t e d F l i g h t Capsule.
I11 2.1 OSE SEQUENTIAL FLOW CHART
The process ing of t h e f l i g h t hardware f o r t..e 1969 t e s t f l i g h t space-
c r a f t and the r e l a t e d 1969 PTM t e s t a c t i v i t i e s a r e e s s e n t i a l l y t h e same
a s those shown i n t h e f low c h a r t of D2-82709-3, F igure 2.1-1 and t h e
a n a l y s i s mat r ices of F igu res 2.1-2 through 2.1-6.
c a t i o n of t he k inds of t e s t s and t h e i r sequencing i s s i g n i f i c a n t t o
p roof ing o r v a l i d a t i o n of t h i s process ing f o r t h e 1971 mission f l i g h t
hardware process ing .
I n f a c t , t h e d u p l i -
The d i f f e r e n c e s i n f low t h a t a r e a consequence of d i f f e r e n c e s i n t e s t
f l i g h t conf igu ra t ion requi rements a r e a s fo l lows:
Payload t e s t and o p e r a t i o n s a c t i v i t i e s a r e modif ied a s r e q u i r e d f o r a
s imula ted capsule r a t h e r t h a n a " l i v e " capsu le and a " l i v e " s c i e n c e
payload.
Capsule and Sc ience
I11 2.2 OSE DESIGN PARAMETERS
OSE des ign parameters f o r t h e Sa tu rn IB/Centaur launched 1969 t e s t
f l i g h t a r e the same a s t h o s e de f ined f o r t h e 1971 miss ion i n D2-82709-3,
Sec t ion 2.2, Tables 2.2-1 through 2.2-4.
I11 2 .3 OSE DESIGN C R I T E R I A
OSE des ign c r i t e r i a f o r t h e Sa tu rn IB/Centaur launched 1969 t e s t f l i g h t
a r e i d e n t i c a l t o t hose d e f i n e d f o r t h e 1971 mis s ion i n D2-82709-3, Para-
graph 2.3.
111-2
Bn€ANG
D2-82709-5 . -J
I11 3.0 FUNCTIONAL DESCRIPTION - SYSTEM LEVEL OSE This section provides functional descriptions of the Systems level OSE
for the Saturn IB/Centaur launched 1969 test flight, in terms of excep-
tions to the OSE design for the 1971 Mission.
I11 3.1 MDE FUNCTIONAL DESCRIPTION
The Mission Dependent Equipment for the 1969 Saturn IB/Centaur launched
test flight, is identical to that defined for the 1961 mission in
D2-82709-5 paragraph 3.1 except as noted below.
Software is modified to be compatible with the test flight profile, the
replacement of the Science Payload and the Capsule by simulators, and
the increased availability of engineering data channels.
I11 3.2 LCE FUNCTIONAL DESCRIPTION
The LCE is identical to the LCE for the 1971 mission described in
D2-82709-3, Section 3.2, with the exception that:
1) Fewer display and data channels are required for the simulated
Spacecraft Science Subsystem and Simulated Capsule then for the
1971 Science Subsystem and Capsule.
Increased Spacecraft engineering data channel capability is provided. 2)
I11 3.3 STC FUNCTIONAL DESCRIPTION
The STC is identical to the STC for the 1971 mission described in
D2-82709-3, Section 3.3, wi th t h e except ions noted below.
111-3
Bn€...&=
D2-82709-5
1) The SIC s u p p o r t s t h e i n t e g r a t i o n of t h e Simulated S p a c e c r a f t
Science Subsystem and Simulated Capsule , r a t h e r t h a n t h e opera-
t i o n a l Sc ience subsystem and Capsule.
The STC u s e s t h e t e l e m e t r y OSE channels no t used f o r Capsule and
Science t o p rov ide i n c r e a s e d c a p a b i l i t y f o r a c q u i r i n g S p a c e c r a f t
engineer ing d a t a .
2)
I11 3.4 AHSE FUNCTIONAL DESCRIPTION
The AHSE i s i d e n t i c a l t o t h e AHSE f o r t h e 1971 miss ion d e f i n e d i n
D2-82709-3, S e c t i o n 3.4.
I11 3.5 SPACECRAFT SIMULATOR
The S p a c e c r a f t Simulator i s i d e n t i c a l t o t h e S p a c e c r a f t S imula to r f o r t h e
1971 mission d e f i n e d i n D2-82709-3, S e c t i o n 3.5.
I11 3.6 SPECIAL SYSTEM LEVEL OSE
The t r e n d da ta equipment i s i d e n t i c a l t o t h a t f o r t h e 1971 mission d e s c r i b e d
i n D2-82709-3, S e c t i o n 3.6, excep t t h a t s o f t w a r e changes a r e r e q u i r e d t o
hand le t h e Science and Capsule s i m u l a t o r s , and t o s u p p o r t t h e i n c r e a s e d
c a p a b i l i t y f o r S p a c e c r a f t Engineer ing Data.
The magnetic mapping equipment i s i d e n t i c a l t o t h a t d e s c r i b e d i n
D2-82709-3, Sec t ion 3.6.
I 11-4
Bn€"G
D2 -82 709-5
b
.
111 4.0 SUBSYSTEM TEST EQUIPMENT
I11 4.1 TELECOMMUNICATIONS
The Telecommunications OSE for the Saturn IB/Centaur 1969 Test Flight
is identical to that defined for the 1971 mission in D2-82709-3,
Paragraph 4.1.
I11 4.2 POWER SUBSYSTEM OSE
The power subsystem OSE for the Saturn IB/Centaur 1969 Test Flight is
identical to that defined for the 1971 mission in 02-82709-3, Paragraph 4.2.
I11 4.3 PROPULSION AND REACTION CONTROL OSE
The Propulsion and Reaction Control OSE for the Saturn IB/Centaur 1969
Test Flight is identical to that defined for the 1971 mission in D2-82709-3,
Paragraph 4.3.
I11 4.4 ENGINEERING MECHANICS
The Engineering Mechanics OSE for the Saturn IB/Centaur 1969 Test Flight
is identical to that defined for the 1971 mission in D2-82709-3, Paragraph
4.4 with the following exceptions:
1)
2)
Magnetometer alignment provisions are not included.
Engineering mechanics checkout provisions are eliminated f o r those
scientific payload instruments that are deleted for the test flight.
I11 4.5 SPACE SCIENCE OSE
The 1969 test spacecraft as launched by t h e S a t u r n IB /Cen t iu r is defined
in D2-82709-4, Part 111. It carries a simulated science payload in lieu
111-5
BmE.Nc
D2 - 82 709-5 . . of a sc ience payload. I t i s expected t h a t development and d e s i g n of
t h e OSE requ i r ed t o check o u t t h e s imula ted s c i e n c e payload would be
c a r r i e d out under t h e cognizance of t h e same agency t h a t i s r e s p o n s i b l e
f o r t h e s e l e c t i o n , des ign , development, and d e l i v e r y of t h e space s c i e n c e
experiments.
The OSE f o r t h e s imula t ed space s c i e n c e payload must be capab le of
checkout and c a l i b r a t i o n of a l l s i m u l a t o r e l e c t r i c a l i n t e r f a c e s w i t h
t h e s p a c e c r a f t b e f o r e i n s t a l l a t i o n of t h e s i m u l a t o r i n t h e s p a c e c r a f t .
D e f i n i t i o n of t h e i n t e r f a c e would p a r a l l e l t h e d e f i n i t i o n of t h e i n t e r -
f a c e f o r t h e 1971 s p a c e c r a f t d e f i n e d i n D2-82709-1 ( s e e S e c t i o n 4.5).
Se lec t ed p o r t i o n s of t h e s imula to r w i l l be used i n t h e Systems Test
Complex t o p rov ide t h e s t i m u l i and measurement c a p a b i l i t y r e q u i r e d
f o r t h e func t ion ing of t h e s i m u l a t o r du r ing s p a c e c r a f t system t e s t i n g .
I11 4.6 ATTITUDE REFERENCE AND AUTOPILOT
The A t t i t u d e Reference and Au top i lo t OSE f o r t h e S a t u r n IB/Centaur 1969
T e s t F l i g h t i s i d e n t i c a l t o t h a t de f ined f o r t h e 1971 miss ion i n
D2-82709-3, Paragraph 4.6, w i t h t h e excep t ion of minor changes t o match
t h e t e l eme t ry o u t p u t s a v a i l a b l e a t t h e s p a c e c r a f t "OSE Connector."
I11 4.7
The CCSS OSE f o r t h e S a t u r n IB/Centaur 1969 Test F l i g h t i s i d e n t i c a l t o
t h a t def ined f o r t h e 1971 miss ion i n D2-82709-3, Paragraph 4.7.
CENTRAL COMPUTER AND SEQUENCER (CCSS) OSE
f
,
.
111-6
e
i
Delete itzms nKbered 3.3.7
a ~ d 3.3.8
"Fl ight C q s u l e S i m d a t o r .