apollo command and service module system specification block 1 26 august 1964

8/6/2019 Apollo Command and Service Module System Specification Block 1 26 August 1964

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1,

S I D 63-313APOLLO COMMAND AND S E R V I C E MODULE

S Y S T E M S P E C I F I C A T I O N !BLOCK I )(U ) NAS 9-15028 August 1964///, Exhibit I Para. 4.2

,

Apol lo P r o g r a m M a n a g erI

% United States wi th in th eSect ion 793 and 794. It sThis document contains informanner !o a n unau?horized perso

N O R T H A M E R I C A N A V I A T I O N , I N C .SPACE and TNFORMATION S Y S T E M S DIVISION


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SIAACI?:and INFORILIATION S I S T E h l S D IV I SI O NI

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3N O R T H A M E R I C A N A V I A T I O N , I N C .

. .

CON TENTS

P a g e1. S C O P E .

1 .1 Objec t ives .2. APPLICABLE DOCUMENTS ,

2 . 1 Speci f icat ions .2.1.1 NASA2 .1 .2 M i l i t a r y .2 .1 .3 C o n t r a c t o r2 . 2 . 1 F e d e r a l .2 .2 .2 M i l i t a r y .2 .2 .3 C o n t r a c t o r

2 .2 S t a n d a r d s .2 .3 D r a w i n g s .2 . 4 Bul le t ins2. 5 Other Pub l i ca t ions .

2.5 .1 NASA2 .5 .2 M i l i t a r y .

2 . 6 P r e c e d e n c e .3. REQUIREMENTS3 . 1 G e n e r a l R e q u i r e m e n t s

3 .1 .1 La u n c h V e h ic l e P e r f o r m a n c e R e q u i r e m e n t s .3. 1. 1 .1 Launch Vehicle At t i tude Control .3 .1 . 1 .2 P rope l l an t Ven ting .3 . 1 . 1 .3 Loads Cr i t e r i a fo r CSM SIVB3. 1. 1. 43. 1. 1.53 . 1 .1 .63 . 1 . 1 .73 .1 .1 .8 C o m m an d a n d S e r v i c e M od ule .3 .1 .1 .9

Adap ter and Ins t rumen ta t ion U n i t .S a t ur n IB P e r f o r m a n c e R e q u i r e m e n t sSa tu rn V P e r f o r m a n c e R e q u i re m e n tsLaunch Vehic le Mechan ica l In t e r f ace sLa u n c h V e h ic l e E l e c t r i c a l I n t e r f a c e sCommand and Service Module SIVBAdapte r ,

...

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- 111 -S i D 63 -313


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-*N O R T H A M E R I C A N A V I A T I O N , I N C . SPACE and 1Nb.ORMATION S YST EM S DIVISIONco- x

P a g e3 .1 .1.1 0 La u n c h Esc a p e S u b sy s t e m . . 173. 1. 1. 11 Command and Ser v ic e Module

S u b sy s t e m . 173. 1. 2 Opera t ion a l Concept . 183. 1. 2. 1 Manning of Fl ig ht . 183 .1 . 2 .2 Onboard Command . 183. 1. 2. 3 Fl igh t Crew 183. 1 . 2 .4 F l igh t T i me Capab i l i t i e s . 183. 1. 2. 5 Ea r t h Land ing . 18

3. 1 . 3 C o m m a n d a n d S e r v i c e M od ule P e r f o r m a n c e . 193. 1. 3 . 1 Boost S tabi l iza t ion . 1 93 . 1. 3 . 2 T r a j e c t o r i e s . 1 9

3. 1 . 4 M i s s i o n P e r f o r m a n c e . 193. 1.4. 1 Fl ight P l an . 193. i . 4. 2 Cont ingencies . 23

3 . 2 Command and Serv ice Module Sy s te m Des ign andP e r f o r m a n c e C r i t e r i a . 253 . 2. 1 G e n e r a l D e s ig n A n a l ys i s C r i t e r i a . 25

3. 2. 1. 1 Limit Condit ions 253 . 2. 1. 2 P e r f o r m a n c e M a r g i ns . 253. 2. 1. 3 P e r f o r m a n c e C r i t e r i a . 263 . 2 . 1 . 4 Command a nd Serv ice ModuleD e s ig n C r i t e r i a . 263. 2. 1. 5 Explosive In i t ia t ors . 273. 2 . 1. 6 E n v i ro n m e n ta l C r i t e r i a . 273 . 2. 2 S t r u c t u r a l S u b sy s te m . 403. 2. 2 . 1 S u b sy s t e m R e q u i r e m e n t s 413. 2 . 2. 2 S u b sy s t e m D e sc r i p t io n . 423 . 2. 1. 7 Weights . 39

3.2 .3 Guidance and Naviga tion Sub sys te m 453. 2. 4 S tab i l i za tion and Con t ro l Subs ys tem 45

3. 2. 4. 1 S u b sy s t e m R e q u i r e m e n t s 453. 2 .4 . 2 Sub syst em Des cr ip t i on . 45

3. 2. 5 S e r v i c e P r o p u l s i o n S u b sy s t e m . 463. 2. 5. 1 S u b sy s t e m R e q u i r e m e n t s 463. 2. 5. 2 Subsys tem Descr ip t ion . 463. 2 . 6. 1 Command Module React ion Co ntrol3 . 2. 6. 2 Serv ice Module Reac t ion Con t ro l

3. 2 . 6 R e a c t i o n C o n t r o l S u b sy s t e m . 47S u b sy s t e m . 47S u b sy s t e m . 47

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- .

P a g e3.2. 7 La u n c h Esc a p e S u b sy s t e m . 483. 2. 7. 1 S u b sy s t e m R e q u i r e m e n t s 48

3. 2. 7, 2 Sub sys tem De scr ipt i on . 513 .2.8 Ea r t h R e c o v e r y S u b sy s t e m 5 23. 2. 8. 1 S u b sy s t e m R e q u i r e m e n t s 5 23. 2. 8. 2 Subsys tem Descr ip t ion . 523 .2 .9 C r e w S u b sy s t e m . 533. 2 .9 . 1 S u b sy s t e m R e q u i r e m e n t s 5 33. 2. 9. 2 Subsys tem Descr ip t ion . 5 43.2 .9 . 3 NASA Furni shed C re w Equipme nt 55

3. 2. 10 Envi ronmen ta l Con t ro l Subsys tem . 573. 2. 10 . 1 S u b sy s t e m R e q u i r e m e n t s 573. 2. 10. 2 Subsys tem Descr ip t ion . 58

3. 2. 1 1 E l e c t r i c a l P o w e r S u b sy s t e m . 603 . 2. 11. 1 S i ~ ~ h s y s t e m-equi rcments 6 03. 2 . 11 . 2 Subsys tem Descr ip t ion . 613. 2 . 12 Communicat ior , Subsystem 5 23. 2 . 12. 1 S u b sy s t e m R e q u i r e m e n t s 6 2

3.2. 12. 2 Subsys tem Descr ip t ion . 633. 2. 1 3 I n s t r u m e n t a t i o n S u b sy s t e m 64

3. 2. 13. 2 Subsys tem Descr ip t ion . 6 43. 2. 1 4 D i sp l a y s a n d C o n t r o l s . 6 4

3. 2. 14. 1 S u b sy s t e m R e q u i r e m e n t s 6 43. 2. 14. 2 Subsys tem Descr ip t ion . 653. 2. 15 En t ry Monito r Subsys tem 653. 2. 15. 1 S u b sy s t e m R e q u i r e m e n t s 6 53. 2 . 1 5 . 2 Subsys tem Descr ip t ion . 6 63. 2 . 16. 1 Subsys tem Requ i r eme nt s 6 63. 2. 16. 2 S u b sy s t e m D e sc r i p t io n . e 66

3. 2. 1 7 Pyro t echn ic Subsys tem and Dev ices . 663. 2. 17. 1 S u b sy s t e m R e q u i r e m e n t s 663. 2. 17. 2 Standard Detona to r Ca r t r id ge . 673. 2. 17. 3 Ele c t r i ca l Power Sourc es 673. 2. 1 7. 4 F i r i n g C i r c u i t Te s t s . 67Serv ic e Module P rope l l an t Di s per sa lS u b sy s t e m . 67

3. 2. 13. 1 Subsys tem Req u i r em ent s 64

3. 2 . 16 Automated Sequence Con t ro l Subs ys tem . . 6 6

3. 2. 1 8

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P a g e3. 3 R e l i a b i l i ty R e q u i r e m e n t s , 673. 3. 1 M i ss i o n S u c c e s s R e l i a b i li t y . 6 7

3. 3. 2 C r e w S a f e ty R e l i a b i li t y . 673. 3. 3 Rel iabi l i ty Appor t ionment * 673. 4 Elec t rom agne t i c Compat ibi l it y . * 683.4. 1 Com mand and Ser vice Module and GSEEq u i p m e n t s . - 6 83 . 4 . 2 Command and Service Module and GSES u b s y s t e m s . . 68

3. 5 In te r changeab i l i ty .3 . 6 Ground Suppor t Equipment .3. 5. 1 Iden ti f ica t ion and T race ab i l i ty .

3 . 6. 1 Suppor t Re quirer l lents3 . 6. 1. 1 Opera t ions Suppor ted3. 6 . 1. 2 Design Concept .3. 6. 1. 3 Command and Serv ice Module

Checkout Concept .3. 6. 1. 4 Sy s te m Checkou t Concep t3. 6. 1. 5 Maintenance Concept

3. 6. 2 Lev el of Suppo rt .3 . 6. 2. 1 Te s t P r e p a r a t i o n a n d A c c e p t an c e

A r e a .3. 6. 2 . 2 House Spacecra f t .3 . 6. 2. 3 Prequa l i f i ca tion F l igh t Drop Te s t

Site3. 6. 2. 4 Whi te Sands M iss i l e Range .3. 6. 2. 5 L a s C r u c e s P r o p ul s i on S y s t e m

Development Faci l i ty3. 6. 2 . 6 En v i r o n m e n t a l Te s t F a z i l i t y .3 . 6. 2. 7 At lan ti c M iss i l e R ange .3 . 6.2.83. 6 . 2. 9

Arnold Eng ineer ing Deve lopmentC e n t e r .M a r sh a l l S p a c e F l ig h t C e n t e r .

3 .7 P e r s o n n e l T r a i n i n g .3 . 7. 1 S u b s y s t e m s T r a i n e r s .

3. 7. 1. 13. 7 . 1. 2 T r a i n e r I t e m s .3. 7. 2 Apollo P a r t T a s k T r a i n e r .

3 . 7. 2. 1 Tra i ner Concep t3. 7 . 2 . 2 T r a i n e r I t e m s .A p ol lo M i s s i o n T r a i n i n g S i m u l a t o r s3. 7. 3. 1 Tr a i n e r C o n c e pt

Tr a i n e r C o n ce p t

3 . 7 . 3

6 869

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7 0. 7 0* 7 1

7 1. 7 1* 7 1* 7 1- 7 2* 7 2

7 2* 7 2* 7 2. 7 3

7 3. 7 37 3

* 7 3. 7 3* 7 3. 7 4 74* 7 4

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N O R T H A M E R I C A N A V I A T I O N . I N C . S I ZCE and I.NFOH11 A T I O N S k S T E h I S DI \ I S I O N

c o mP a g e

3 . 8 Manned Space F l igh t Con t ro l Ce n te r and MannedSpace F l igh t Ne t . . 753. 9 M a t e r i a l s , P a r t s , a n d P r o c e s s e s . 753. 9. 1 Specif ica t ions and Sta nd ard s . 753. 9. 2 Choice of S tandard Mater ia ls , P a r t s ,

3 . 9. 3 N o n s t an d a r d P a r t s , M a t e r i a l s , a n da nd P r o c e s s e s . 76P r o c e s s e s . 763. 9. 3. 1 N ew P a r t s , M a t e r i a l s , a n dP r o c e s s e s . 76

3. 9. 5 F l a m m a b l e M a t e r i a l s 7 63. 9. 6 Toxic Ma te r i a l s 763. 9 . 4 Miniatur izat ion . . 763. 9. 7 Unstab le Mate r i a l s . * 773. 9. 8 Fungus- Iner t Mate r i a l s . . 773 . 9 . 9 M e t a l s . 7 73. 9. 9. 1 Diss imi la r Meta l s . 77

3. 9. 9. Fle c t r i ca l Conduct iv i ty . 773. 9. 10 Lubr ican t s . 773. 9. 11 Specia l Tools . 773. 9. 1 2 Explosion Proof ing . . 773. 9. 1 3 Fai l Safe . . 783 .9 . 14 Conne c to r s . . 783 .9 . 1 5 Ground Support Equipment . 783. 9. 1 6 Name pla tes and P roduc t Mark ings 78

4. QUALITY ASSURANCE PROVISIONS . . 784. 1 G e n e r a l Q u a li ty A ssu r a n c e P r o g r a m . . 78

4. 1. 1 Qual i ty Contr 01 . . 784. 2 Rel iabi l i ty . . 784. 3 Tes t . . 78

4.4. 1 Change Con t ro l . . 814; 4 CGnfigzl?ation Management P r o v i s i o ~ s . 815. P R EP A R A TI O N FOR DELIVERY . . 81

5. 1 P r e s e r v a t i o n , P a ck a g in g a n d Pa c k in g . . 815. 2 Handling . . 81

6. NOTES .6. 1 R e f e r e n c e A x e s

. 81. 81

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ILLUSTRATIONS

F i g u r e123456785,10

1112131 41 516171 81 9202122232 4

Saturn C-IB Conf igura t ion .Satu rn V LOR Conf igura t ionVib ra t ion T ime His to ry - A t m o s p h e r i c F l i g h tVib ra t ion LES - Atmospher i c F l igh t .Vibra t ion CM - Atmospher i c F l igh t .Vibra t ion SM - A t m o s p h e r i c F l i g ht .Vibra t ion SM Adapter - Atmospher i c F l igh tAcous t i c s LES - Atmospher i c F l igh t - F o r w a r d A r e aAcoi i s t ics LES - Atmospher ic Fl igh t - Ski r t A r e a .Acous t i c s CM - A t m o s p h e r i c F l i g h t - I n t e r n a l -Acous t i c s CM - A t m o s p h e r i c F l i g ht - E x t e r n a l -Acous t i c s CM - Atmospher i c F l igh t - I n t e r n a l -Acous t i c s CM - Atmospher i c F l igh t - E x t e r n a l -Acous t i c s CM - A t m o s p h e r i c F l i g h t - C r e w C o m p a r tm e n tAcous t i c s S M - Atmospher i c F l igh t - I n t e r n a lAcous t i c s SM - Atmospher i c F l igh t - E x t e r n a l -Acous t i c s SM/RCS Eng ine & P a n e l - A t m a s p h e r i cAcous t i c s S M - Atmospher i c F l igh t - I n t e r n a lAcous t i c s SM - Atmospher i c F l igh t - E x t e r n a lAcous t i c s Adap te r - Atmospher i c F l igh t - E x t e r n a lAxial A c c e l e r a t i o n - Nominal Satu rn V Boost .Late ra l Acce le r a t ion Dur ing F i r s t Stage BoostL a t e r a l A c c e l e r a t i o n - S-I1 Fligh t a t M a x i m u mL a t e r a l A c c e l er a t io n - S-IVB Flight a t M a x i m u m

. .Forward Xa1060 .Forward Xa1060 .Af tXa1060 .Aft Xa1060 . .-F o r w a r d X a9 10 ,F o r w a r d X a9 10 .F l i g h t .X a 9 i 0 t o Xa8 3 8 .Xa910 to Xa838 .Xa838 to X a722 .

.Gimb a l D ef lec t ionGimb a l D ef lec t ion

P a g e828384858 6878889909192939 495

9 6979 89 9

100101102103104105

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F i g u r e2526272 8293031323334

3536373 83 9404 1424 34 44 54 64 7484 950515 25 35 45556

P a g eVibra t ion CM - Space F l igh t * 106Vibra t ion SM - Space F l igh t * 107I n t e r n a l Eq u i p m e n t U l t i m a te D e s i g n Lo a d D i a g r a m I . * 108I n t e r n a l Eq u i p m e n t U l ti m a t e D e s i g n Lo ad D i a g r a m I1 . 109Vibra t ion LES - High "Qll Abor t . * 110Vibra t ion CM - High "Q" Abor t . * 111Acous t i cs LES - High "Q" A b o r t . 1 1 2

F o r w a r d X a1 06 0 . 113Acous t i cs C M - High "Q" Abor t - I n t e r n a l -Acous t i cs C M - High "Q" Abor t - E x t e r n a l -Acous t i cs CM - High "Q" Abor t - I n t e r n a l -Acous t i cs CM - High "Q" Abor t - E x t e r n a l -

Fo rw ar d of Xa1060 , 114Aft of Xa1060 ' 115Aft of Xa1060 116

A c o u s t ic s C M - High "Q" Abor t - C r e w C o m p a r tm e n t . 117A r e a D e s ig n a ti o ns - Side View . 119A r e a D e s i g n a t i on s - View Look ing Fo rw ar d . 120Command Module Ex t e rna l Dimens ions Including

A b la ti ve M a t e r i a l . 1 1 8

Area Des igna t ions - View Looking Toward LowerE n d of C r e w A r e a 1 21

Serv ice Module Inboard P r o f i l e - View LookingF o r w a r d 1 2 2

Serv ice Module Inboard P r o f i l e . 123Sus ta ined Acce le ra t ion - Eyeba l l s Out . 124Sus ta ined Acce le ra t ion - Eyeba l l s In . 125Sus ta ined Acce le ra t ion - Eyebal ls Down . 126Sa tu rn V Two-S tage Boos t Tra jec to ry - 1 0 0 N M O r b i t . 127Em e r g e n c y C a r b o n D i ox id e L i m i t . 128Te m p e r a t u r e a n d H u m i di ty N om i n al L i m i t . 129

* 130emp per at lire and H.;r;-,idity Er;!ergencTyr LimitW in d S h e a r P r o f i l e . 1 3 1Li n e a r Lo a d D i s t ri b u t i o n for Ma ch 1 . 35 . * 132Gra d ien t of N orm al Fo rc e Coef f ic i en t and Cen te r o f

P r e s s u r e V e r s u s M a c h N u mb er s . 133S a t u r n V , S - l C , E1 Dist r ibut ion . * 134Sa tu rn V, S-11, E1 Dis t r ibu t ion . * 135Sa tur n V, S- IC, KAG Dist r ibu t ion . * 136Sa tu rn V, S-11, KAG Dis trib utio n . 137

.

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F i g u r e P a g e5 7 S a t u r n V , S-IC, Dr y Weigh t Di s t r i bu t i on . . 13958 S a t u r n V , S-IC , Wet Weight Dis t r ibut io n . . 14159 S a t u r n V , S-IC, Fu l l Weigh t Di s t r i bu t i on . . 1 436 0 S a t u r n V , S-11, D ry Weight Dis t r ibu t ion . . 14561 Sa turn V , S-11, Wet Weight Dis t r ibu t ion , . 147

TABLES

T a b l e P a g eI R e f e r e n c e A x e s . . 149

and Water . . 15011 E s t i m a t e s of M e t a b o li c R a t e s , T h e r m a l B a l a n c e s

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N O R T H A M E R I C A N A V I A T I O N , I N C . SIAIcb: and INPWRS1.ATION S Y S T E h l S D I V I S IO N

CON-

1 .1

2.

2 .12 .1 .1

S C O P ETh i s sp e c if i c at i o n e s t a b l ish e s t h e t e c h n i c a l p e r f o r m a n c erequ i r em ent s fo r the deve lopment and des ign of the Apollo(Block I) Command and Serv ice Module (CSM) Sy s te m. TheCSM Sys tem a s d i scuss ed in th i s spec i f i ca t ion i s c o m p r i s e dof a La un ch Esc a p e S u b sy s t e m ( LES ) , a Command Module(CM) , a Se rvi ce Module (SM), a Spacecraf t S- IVB Adapter ,the a sso c ia t e d Ground Suppor t Equ ipment (GSE) , andr e q u i s i te T r a i n e r s . A general conf igurat ion of the Block IC SM a nd La un ch V e h ic l es ( LV ) a r e d e l i n e a te d i n F i g u r e s 1and 2.I n a d d it io n , p e r f o r m a n c e c h a r a c t e r i s t i c s of the LV and theo ther i t em s of Government Furn i shed Equ ipment (G FE ) wi thwhich the de sig n of the CSM Sy ste m i s compat ib le a r especi f ied .Th e b a s i s f o r d e s i g n of t he CSM Sys te m sha l l be a Lunar Orb i tmis s ion w hich may be def ined a s t he Lunar Orb i t Rendezvous(LOR) mis s ion wi thou t the Lunar Excur s ion Module (LE M)in te r f ace . Tha t i s , t he t r an s lun ar in j ec ted g r os s we igh t ofCSM Sys tem sha l l inc lude the p rope l l en t a l lo tm en t r eq u i r edfo r ixancuver ing i f the L,FM we re a t t ached bu t the LEM sub-sy s t e m s , t h e i r r e l a t i o n sh i p w i th t h e CS M su b sy s t e m s , a n d t h efunct ional f low of databe tween the LEM and CSM a r e not included.Objec t ives . -The o bject ive of the CSM i s t o tr a n s p o r t t h r e e m e n t o a l unaro r b i t a n d t o r e t u r n t h e m sa f e ly to e a r t h .APPLICABLE DOCUMENTSThe fo l lowing documents form a pa r t of th i s spec i f i ca t ion tothe ex ten t spec i f i ed he re in :Spec i f i ca t ions . -NASA. -MSFC -PRO C- 158A12 Apr i l 1964

Solder ing e l ec t r i ca l connec to r s (h ighr e l i a b i li t y ) p r o c e d u r e f o r ( a m e n d m e n t sMSC-A SP0 513 of 10 Fe br ua ry 1964)

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S P A C E and INEORhlATION S Y S T E M S DIVISION

*vN O R T H A M E R I C A N A V I A T I O N . I N C .

2 . 1 . 3

2.1.2

MSFC 10M 010716 M a r c h 1961

MSC-EMI- 10A17 Octob er 1963MSC-GSE- 1B1 2 F e b r u a r y 1964

MSC- ASPO -I- 4

Mi l i t a ry . -MIL-1-266002 J u n e 1 9 58MIL-E-6051C17 Jun e 1960

C o n t r a c t o r . -

Envi ronment - p ro t ec t i on W h e n UsingElectr ical Equipment-Within the A r e a sof S a t u r n C o m p l e x e s W h e r e H a z a r d o u sA r e a E x is t; p r o c e d u r e fo rAddendum to MIL-I - 26600, In t e r f e re nceCont ro l Requi re ment s , Ae ro . Equip.Apollo Ground Suppor t Equipm entG e n e r a l E n v i r o n m e n t a l C r i t e r i a a ndT e s t Spec i f i ca ti onApollo Spa cec raf t Ident i f ica tion andTraceab i l i t y Spec i f i ca t i on .

I n t e r f e r e n c e C o n t r o l R e q u i r e m e n t s ,A e rGnaut ica l EquiprxentE l e c t r i c a l E l e c t r o n i c S y s t e m C o m p a ti -b i li t y a n d I n t e r f e r e n c e C o n tr o l R e q u i r e -m e n t s f o r Aeronau t i ca l Weapon Sys t ems ,A s s o c i a t e d S u b s y s t e m s a n d A i r c r a f t .

Nor th Ame r i ca n Avia ti on , In c . , Space and In format ionSys t ems Div i s ion (NPA /S&ID)SID 62- 100017 Sep t em ber 1964

P r e l i m i n a r y G u i da n ce a n d N a vi ga ti onS y s t e m P e r f o r m a n c e a n d I n te r f ac e( P & I )R e q u i r e m e n t s S p e c if i ca t io n s

SID 62-100317 Sep t em ber 1964

P r e l i m i n a r y NASA F u r n i s h e d C r e wE q u i p m e n t I n t e r f a c e a n d P e r f o r m a n c eSpec i f i ca t i ons .

SID 62-100117 S e p t e m b e r 1 9 6 4 F l i g h t R e s e a r c h a n d D e v el o pm e n t(R&D) ns t rumenta t i on Spec i f i ca ti on .SID 63-88117 Sep t em ber 1964

NASA Manned Space F l i gh t Ne t( M S F N ) P e r f o r m a n c e a n d I n t e r f a c e( P & I ) pec i f ica t ion - P r i m a r y

- 2 -SID 6 3 -3 1 3


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SI'ACE and I N F O R M A T I O N S Y S T E M S DIVISION

1 sx

N O R T H A M E R I C A N A V I A T I O N , I N C .

SID 64-1237 Vehicle Model Specificat ion, Ba si c -4 Septe mb er 1964 Block I

2 . 22 . 2 . 1

S t a n d a r d s . -F e d e r a l . -

2 . 2 . 2

2 . 2 . 3

2 . 3

S t a n d a r d A t m o s p h e r e 1 96 2NASA T N D-595M a r c h 1 96 1F e d e r a l S t a n d a r d 20 91 6 D e c e m b e r 1 9 63Mi l i t a ry . -

R e f e r e n c e A t m o s p h e r e F o r P a t r i c kA F BClean Room an d Work S t a ti on Req ui re -m e n t s , C o n t r o l l ed E n v i r o n m e n t s

MIL-STD- 130B24 Sep temb er 1962MIL-STD-7046 October 1959MS 33586A1 6 D e c e m b e r 1 9 58MIL-STD-80327 Janua ry 1964C o n t r a c t o r . -Not appl icab leD r a w i n g s . -ICD 13M2010820 Ju ly 1964ICD 13M501032 8 May 1964ICD 13M201092 4 Ju ly 1964ICD 13M5012329 July 1964

Ident i f ica t ion Mark ing of U . S. M i l i t a r yP r o p e r tyE l e c t r i c a l P o w e r , A i r c r af t ; C h a r a c t e r -i s t i cs and ut i li za t ion ofMe ta l s ; def ini t ions of d i s s i m i l a r

H u m a n E n g i n e e r in g De s ig n C r i t e r i af o r A e r o s p a c e S y s t e m s a n d E q u ip m e n t

" I n s t r u m e n t U n i t t o Spacec ra f tP h y s i c a l R e q u i r e m e n t s I (Sa turn 1B )" I n s t r u m e n t U n i t t o S p a c e c r a f tP h y s i c a l R e q u i r e m e n t s I (Sa turn V)' ' S p a c e c r a f t / QIl- B a l l P h y s i c a lR e q u i r e m e n t s ' (Sa turn 1B )Enve lope L E M S - IVB / I U C1e ar anc e ,P h y s i c a1

d M " T I A L3 - SID 63-31 3


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N O R T H A M E R I C A N A V I A T I O N , I N C . SI'ACK and INE'OIlhl.4TION S YS TEh l S D I V I S I O N

2 . 4

2 . 52 . 5. 1

2 . 5 . 2

2 . 6

ICD 13M50112 "Spacecra f t /"Q"-Ball Ph ys ic al2 2 Ju ly 1964 R e q u i r e m e n t s " ( S a t u r n V)Bul le t ins . -None applicableOther Pub l i ca t ions . -NASA. -NPC 200-22 0 A p r i l 1 96 2 S y s t e m C o n t r a c t s

Q u a li ty - P r o g r a m P r o v i s i o n s f o r S p a c e

Mi l i t a ry . -A F M T C P a m p h l e t G e n e r a l R a n g e S a f e t y P l a n , P r e l a u n c h80-2, V o l . I S a fe t y P r o c e d u r e1 Octo ber 1963A F C R L 6 2 - 899July 1962 V o l s . I , I1 an d 111.

Two Po in t Var i ab i l i ty of Winds,

WADC TR 5 2 - 3 2 1Septe mbe r 1954 1950

Anthropom et ry of F lying Per s onn e l -P r e c e d e n c e . - T h e o r d e r of p r e c e d e n c e i n c a s e of confl ictsha l l be a s fo l lows:

( a ) Th e Def in i t ive C ont rac t , NAS9- 150, dated14 August 1963, Supplem ental Ag ree me nts andContract Change Author izat ions , (SA/ C C A 's )t h e r e t o of d a te p r i o r t o 1 Augus t 1964.

( b ) This speci f icat ion( c ) SID 64-1237, Vehicle Model Specif icat ion -

B a s i c : Block I( d ) O t h e r d oc u m en t s r e f e r e n c e d h e r e i n

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N O R T H A M E R I C A N A V I A T I O N , I N C . SIAACE an d I N F O Rh L 4 T IO N S Y S T E h l S D I V I S I O N

3 . REQUIREMENTSThi s sec t i on con t ains t he pe r fo rm ance and des ign requ i re men t sfo r the CSM System and wi l l enco mp ass the following:a . Defini t ion of m a j o r e l e m e n t s of t he sys t em.b . D e s ig n c o n s t r a i n t s a nd s t a n d a r d s n e c e s s a r y t o a s s u r e

compat ibi l i ty of program hardware .c . The a l loca t ion of performance budgets and spec i f ied

des ign cons t ra in t s .d . Ident i f ica tion of the pr in c ipa l func t iona l in t e r f ace s .e . Ident i f ica tion and us e of the Gov ernme nt Fu rn ish ed

E q u ip m e nt ( G F E ) f o r m in g a n i n t e g r a l p a r t o f t he s y s t e m .3 . 1

3 . 1 . 1

G e n e r a l R e q u i r e m e n t s . - T h e s e g e n e r a l r e q u ir e m e n t s a r ethe col lec t ion of pr in c iple s to which the ba s ic t ec hnica lapproac h of t he CSM sub sys t ems m us t be re spon s ive .a r e th e f i r s t o r d e r c r i t e r i a f r o m w h ic h s u c c e s s i v e d es i g nc r i t e r i a , p e r f or m a n c e m a r g i n s , t o l e r a n c e s , a nd e n v i ro n -men t s sha l l be deve loped .

They

L a u nc h V eh i cl e ( L V ) P e r f o r m a n c e R e q u i r e m e n t s . - P r o p u l s i o ninc re men t s i nvo lved wi th t he boos t phas es of t he m i s s i onwi l l be supp l ied by NASA f urn ishe d Sa tu rn 1B o r S a t ur n Vl aunch vehic les .pa t ible wi th the fol lowing inte rface requi rements .

The CSM s ys t em sha l l be de s igned com -

3 . 1 . 1 .1 Launchveh i c l e At t i t ude Cont ro l . - Th e l imi t cyc l e o r deadband fo r the a t t i tude co nt ro l sub sy s tem of the LV sh a l l bef 1 . 0 degree i n p it ch , ro l l and yaw a t a r a t e no t t o exceed0. 05 d e g r e e s / s e c o n d .

3 . 1. 1 . 2 Pro pe l l an t Venting. - The SIVB prope l l an t ven t ing sha l l becon tinuous and t he t h ru s t gene ra t ed sh a l l no t c ause anymo men t t ha t c annot be c or re c t e d wi th in t he a tt i tude con t ro lsubsy s t em dead band.

3 . 1. 1. 3 Loads C r i t e r i a fo r CSM SIVB Adapte r and Ins t rum enta t i onUnit IV). - T h e f o llo w in g m a x i m u m f l ig h t p a r a m e t e r ssh a l l not be exc eeded on Block I m i s s i o n s .

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3 . 1 . 1 .3 . 1 L oa d P a r a m e t e r s

SShear(lbs.

0 = 6. 9 d e g r e e s2q a = 5072 L b / F t

T r a j e c t o r i e s s h a l l b e s h ap e d su c h t h at t h e s e p a r a m e t e r s a r eno t exceeded . ( se e F igu re 46 )The l imi t a x i a l l o a d s , s h e a r s , a n d b en ding m o m e n t s a t t h eCSM/LV in te r fac e sha l l no t exceed those shown in thefollowing table for conditions of maximum q a :

deg. (fo r f lexible body conditio ns)

PAxia lLoad(lbs.

L oa d P a r a m e t e r sLoads IG-3

I n t e r f a c eAdap te r / I U(Apollo Station 502)

6 3 . 0 - 2 6 9 . 0-I-Moment

( in - lb )M A

2 1 , 8 0 0

hlMoment

AM.( in - lb )

2 60

Moment( in - b)n My

6. 3

Note: M A i s the momen t due to the t r a je c to ry and t ra jec to r yd i s p e r s i o n s . A M Z and A My a r e f ix e d d i r e c t i o nmom ents due to the phys ica l des ign of the vehic le(C G l o c a t i o n s , a s y m m e t r y , e t c . )

3 .1 . 1 .3 .2 B o o s t e r A e r o D a ta. - Loads eva lua ted fo r the max q Q conditions h a l l u s e t h e B o o s t e r n o r m a l f o r c e c o ef fi c ie n t a n d c e n t e r o fp r e s s u r e a s g iven in F igu re 51 , and the no rm al fo rce d i s t r ibu -t ion, fo r the boos te r on ly , a s g iven in F igu r e 52 .

3 . 1 . 1 . 3 . 3 B o o s te r C o n t r o l Sy s t e m C r i t e r i a . - Th e s y s t e m g a in s f o r t h ea u to p il o t a r e d e r iv e d by using a com binat ion of the min imu mdr i f t and min imum load p r inc i p le s having a n aux i l i a ry feed -back loop uti l izing a n a n gl e of a t t a c k o r a n a c c e l e r o m e te rs e n s o r .

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3 . 1. 1 .3 .4 Boos te r S t i f fness . - Dis t r ibu t ions o f E1 a nd KAG fo r theSa tu r n V boos te r a r e g iven in F igu res 53 th ru 56.3 . 1 . 1 . 3 . 5 B o o s t e r We ig ht D i s t ri b u ti o n . - Weight d is t r ibut i ons for theSa tu r n V b o o s te r s t r u c t u r e a n d p r o p el l a nt a r e g i ve n i n

F ig u r e s 5 7 t h r u 6 1.3 . 1 . 1 . 4 S a t u r n IB P e r f o r m a n c e R e q u ir e m e n ts :3 . 1 . 1 . 4 . 1 Pay load Capab i l i ty . - F o r t h e S a t u r n I B m i s s i o n s t h e LVsh al l be capable of in jec t ing 32 , 500 pounds , ba sed on a

8 , 200 pound Launch Esca pe Subsys tem (LE S) , in to a nomina l1 00 n . m . Ea r th o r b i t .

3 . 1 . 1 . 4 . 2 T r a j e c t o r y R e q u i r e m e n t s , S a t u rn I B . - T h e L V s h a l l i n s e r tthe CSM a t cutof f in to the pa r t i c u la r mis s io n des ign t r a -jec to r y wi thin the a cc u r ac ie s de f ined by the fol lowing f l igh tp a r a m e t e r s :E c c e n t r i c i t y , e , *O . 00725S e m i m a j o r a x i s , a . * l o . 70 n a u ti c a l m i l e sAscend ing node , *0 .210 de g r ee sIn c lin a ti on , * O . 0 83 9 d e g r e e sTr ue ano maly of theascending node *O. 8 30 d e g r e e s( I f appl icable for thep a r t i c u l a r m i s s i o n )

3 . 1 . 1 . 5 S a t u rn V P e r f o r m a n c e R e q u i r e m e n ts . -3 . 1 . 1 . 5 . 1 Pay load Capab i l i ty . - F o r t h e S a t u r n V m i s s i o n s t he L V

sha l l be ca pable of in jec t in g 9 0 , 0 0 0 pounds , b as ed on a8,2 00 pound LES and a 2 4 , 500 pound LEM in to a t r a ns l un a rt r a j e c t o r y of the f ree re tu rn type hav ing a nomina l vacuumper i gee a l t i tude of 2 1 n. m . w i th n o m id c o u r s e c o r r e c t i o n sr e q u i r e d to a c c o m p l i s h t he t r a j e c to r y.

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N O R T H A M E R I C A N A V I A T IO N , I N C . SPACE and INYORMATION S Y S T E M S DIVISION

CON- -4rn3 . 1 . 1 . 5 . 2 I r a e cto ey R 2quir err, er,t sa . P a r k i n g O r b i t . - The LV sha l l i n s e r t t he CSM a t cutoff

in to the pa r t i cu la r m iss ion des ign t r a j ec to r y fo r the pa rk -ing orbit within the ac cu ra ci es defined by the fol lowingfl ight par am ete r s :Ec c e n t r i c i t y , e , +O. 00725S e m i m a j o r a x i s , a, * l o . 7 0 n a u t i c a l m i l e sAs cending node, *O . 210 degreesInclinat ion, *O . 0839 degreesTr u e a n o m a ly o fthe ascending node * O s 830 degreesp a r t i c u l a r m i s s i o n )(I f app l icab le f c ? r the

b . M i s s i o n s . - The LV sh al l injec t the CSM a t cutoff into thep a r t i c u l a r m i s s i o n d e s i g n t r a j e c t o r y wi th in t h e a c c u r a c i e sdefined by the fol lowing o rb i t a l pa r am ete r s :

J,Ec c e n t r i c i t y , e , f .

Ascending node, f : d e g r e e sIncl inat ion , f : d e g r e e sTrue anomaly o fthe as cen ding node * ::d e g r e e s(If appl icable fo r thep a r t i c u l a r m i s s i o n )

3. 1. 1. 6 Launch Vehicle Mechanical In ter faces . -3. 1 . 1. 6 . 1 P h y s i c a l I n t e r fa c e s

a . CSM SIVB Adapter / IU In te r f ace . - The CSM SIVBAdapter shal l s t ructura l ly and funct ional ly adapt theServ ice Module t o the Launch Vehicle . In the ar z a of

* ."_I V ~ L &ii a55igll v&aesm i s s io n a n d w i t h t h e AV budg et es tablished for inidcourse cor rect ion . (Ref . Para. 3. 1.1.8.3)

thesc ~ z i ~ ~ e t e r sh a t ar e consistent with the ta r ge t ing r equi r ements of a lunar

SID 63-313


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/-SPACE and INPOR%I.%TION YST Ehl S DIVISION

aN O R T H A M E R I C A N A V I AT I O N , I N C .

in t er f ac e wi th the Launc h Vehicle , the design of the Adap-t e r and the des ign o f the IU sh a l l m e e t t he r e q u i r e m e n t sof ICD's 13M20108 (Saturn IB) "Ins t rum ent Unit toS p a c e c r a f t P h y s i c a l R e q u i r e m e n t s " ( o r i g i n a l i s s u e ) ,13M50103 (Saturn V ) " Ins t rum ent Unit t o Space cra f tP h y s i c a l R e q u i r em e n t s " ( o r i g i n a l i s su e ) . R e q u i r e m e n t sesta bl i s hed by ICD 13M50123 "Envelope, LEM ISIVBIIUC l e a r a n c e , P h y s i c al " ( o r i g i n a l i s s u e ) w i l l b e m e t a sr e q u i r e d f o r th e S a t u r n m i s s i o n s i nv o lv e d.Note: Whi le the ef fect iv i ty of thes e do cume nts i s l imi ted

to mis s ion s A201 and A501, the des ign r eq u i r e -me n t s es t ab l i s hed the re in p rov ide a base l iner e f e r e n c e f o r a l l B l o ck I Satu rn IB and Sa tu rn Vm i s s i o n s .

b . "Q" Bal l t o CSM In te r f ac e . - Th e des ign of the "Q"-balland the design of upper end of the bal l as t enc losu resha l l me e t the r equ i r em ent s ICD's 13M20109 (Sa tu rn IB )I I Spa c e c r af t / Q - B a11 P hy s i c a1 Re qui r em en s I (o r g n a 1i s su e) and 13M50112 (Saturn V ) "Spacecra f t / "Q"-Bal lP h y s i c a l R e q u i r e m e n t s " ( o r ig i n a l i s su e ) .Note: Whi le the ef fe ct iv i ty of the se do cum ents i s l imi ted

to mis s ion s A201 and A501 , the des ign r equ i r e -me n t s es t ab l i s hed the re in p rov ide a base l iner e f e r e n c e f o r a l l B l o ck I Satu rn IB and Sa tu rn Vm i s s i o n s .

3. 1. 1. 6 . 2 CS M SIVB Adap te r / IU In te r f ace Com par tme n t . -a . Boos t Phase Ven t ing . - During the boost phase the

Serv ice Module , A dap te r , I U a n d SIV B f o r w a r d sk i r tsha l l be ven ted to a tmosp here v ia ven t s to be loca ted onthe SIVB between 122 and 130 inc he s af t of the Adapter /I U i n t e r f a c e .200 s q . i n c h e s .

T o t al ve nt c r o s s - s e c t i o n a l a r e a s h a l l b e

b. P u r g e R e q u i re m e n t s . - P r o v i s i o n s sh a l l b e i n cl u de d i nthe design of the vehic le for a ga s purge of the Adap ter /IU i n t e r f a c e c o m p a r t m e n t . Th e p u r g e g a s sh a l l b ein t roduced th rough the um bi l i c a l s i n the Serv i ce Module ,Adap te r and I U and sha l l be exhaus ted v ia the boos tphase ven t s in the S IVB. The des ign sh a l l be compat iblew i th a n a i r p u r ge f o r th e c o n t r o l o f t e m p e r a t u r e a n dwork ing cond it ions ins ide the co mp ar tm en t and wi th aG N2 p u r g e w h e n a n e x p lo s i o n h a z a r d p o t e n t ia l l y e x i s t s .

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N O R T H A M E R I C A N A V I A T I O N , I N C . SPA C E and I N F O R h l A T I O N S Y S T E M S D I V I S I O N'dCON- a.*. .I

c . Lower Adap te r Access P rov i s ions . - P r o v i s i o n s sh a l lbe in corpo rated in the desig n of the I U for ins ta l la t ionof p la t fo rms r eq u i r ed fo r acc es s to the lower LEM ar eaand low er A dapter mounted- CSM eq uipment duringground checkout and se rvic in g operat ions .fo rm s a r e to be designed and provided by the MSFC.Thes e p la t fo rms sha l l a l s o be des igned such tha t theywil l provide se lected bas e ( leg) a t tac h points and wi l lsuppor t the ver t ica l loads only f rom auxi l iary two manp l a t f o r m s ,

These p la t -

3 . 1. 1 . 7 Launch Vehicle Ele ct r i cal In ter fa ces . -3 . 1 . 1 . 7. 1 Adap te r / IU In te r f ace P rov i s ion . - Three type PTOOSE-24-61s

e le c t r i ca l con nec to r s sha l l be p rov ided in the Adap te r fo rel ec tr ic al mating of CSM and Launch Vehicle. The connectorssha l l be mounted to a brac ket a t tach ed to the Adapter s t ru ctu reand located 25 inch es above the SLA/IU in ter fa ce , 45 deg ree sf r o m t he - Z axis toward the tY axis (CSM axe s, Table I ) .

3. 1. 1. 7. 2 "Q" B a l l I n t e r f a c e P r o v i s i on s . - Wiring sha l l be providedf ro m the MSFC fu rn i shed "Q" ba l l t o the Adap te r/ IU in te r -fac e . Wir ing sha l l be term ina ted wi th a ME414-0095-0062o r equivalent connector a t the "Q" bal l in ter face and one ofthe above type PTOOSE-24-61s conn ector s a t the Ada pter /I U i n t e r f ace . The in te r face between Launch Vehicle equip-me nt and the CSM port ion of the Laun ch Vehicle EDS re la te dto the "Q" ba l l s igna l s i s con ta ined in Paragraph 3 . 1. 1. 7 . 5. 2. 1,a9 (3), ( f ) .

3. 1. 1. 7. 3 Power In te r f ace . - Elec t r i ca l i n t e r f ace s be tween CSM andLaunch Vehicle sha l l be designed in such a man ner that the rewill be no exchange of e le c t r i ca l power be tween CSM andLaunch Vehicle .

3. 1. 1 . 7 . 4 S igna l In te r f aces . - For e l e c t r i ca l s igna l in t e r f a ces , adequatee le c t r i ca l i so la t ion sha l l be p rov ided in the in t e r f ace des igns o that the ef fect iveness of any s igna l cro ssi ng the in ter fa cewi l l not be dete r iora te d .

3 . 1. 1. 7. 5 Launch Vehicle Em ergency Detect ion Sy stem (LV-EDS). -The LV-EDS i s a syst em which i s operat ive dur ing boostf l ight in both the Saturn LV and the CSM s ys te m.i s t o de tec t c r i t i ca l condi tions a r i s ing f rom mal func tionswithin the L V and au tomati ca l ly t r an sm i t a s igna l to the LES

I t s purpose

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N O R T H A M E R I C A N A V I A T I O N , I N C . SPACE and INFORhlATION SY STEMS DIVISION.. -r,'.

a . Swi tch power to o r f rom the LV-EDS sys te m.

to in i t i a t e ab or t ac t ion o r to p rov ide in fo rm at ion to the CSMc r e w t o i n d ic a t e t h a t a n a b o r t m a y b e r e q u i r e d . Th i s sp e c i -f icat ion i s concern ed only wi th that por t ion of the LV-EDSwhich i s con ta ined in the CSM (h ere a f t e r r e f e r r e d to a s LV-EDS) and i t s re la t ions hip wi th the por t ion of the LV-EDSwhich i s con ta ined in the Sa tu rn LV. Whe re r e f e ren ce i sma de to the LV por t ion of the LV-EDS, i t i s s o i nd ica ted .Since the CSM s ys te m wi l l be engaged in miss ion s involvingboth Saturn IB and Saturn V l aunch veh ic l es , t he pe r fo rm anc eand in te r f ace r equ i r em ent s fo r bo th those veh ic les a r ei n cl u de d i n t h i s sp e ci fi c at io n . Th e se r e q u i r e m e n t s a r e c o m -mo n to bo th veh ic l es excep t where ind ica ted o therwise .

3 . 1 . 1 . 7. 5 . 1 P e r f o r m a n c e R e a u i r e m e n t s . - The LV-EDS contained in theCS M sy st em wi l l provide the fo llowing capabi l i t ies .

3 .1 .1 .7 .5 .1 .1 Ast ronau t Di sp lays .and o ther CSM su bsy s tem s , the LV-EDS wi l l d i sp lay c r i t i ca lcondit ions to the c re w of the CSM.

- I n r e sp o n se t o s i g n al s f r o m t he LV3.1 .1 .7 .5 .1 .2 As t ronau t Con t ro l s . - The CSM wi l l i ncorpora te p rov i s ions

fo r as t ro nau t c ont r o l of the LV -EDS in both the CSM and theLV. Th e se c o n t r o l s w i l l p e r m i t t he a s t r o n a u t to :

b . En a b l e o r d i s a bl e t h e a ut o m a ti c a b o r t c i r c u i t r y o rce r t a in por tions of tha t c i r cu i t ry in the LV.

c . Manua l ly in i t i a te an ab or t sequence wi th the LES , o r ,a f t e r LES j e t t i son , the SM propu l s ion su bsy s tem and ,con curr ent ly , com man d LV act ive engine cutof f.

3 .1 .1 .7 .5 .1 .3 Automat ic LV-EDS Funct io ns. - The LV-EDS wi l l a l soautomat ical ly accompl ish the fo l lowing funct ions wi th in theCSM.a . Enab le the au tomat i c ab or t c i r c u i t ry a t t he ins t an t o f

l i f t - off.Det erm ine throug h m aj or i ty voting logic the val id i ty ofa n a u t o m a ti c a b o r t s i g n a l p r e se n c e i n t he C S M / LV i n t e r -f a c e a b o r t c i r c u i t r y b e f o r e t r a n sm i t t in g a n a b o r t c o m m a n dto the LES.

b.

c

-

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..&N O R T H A M E R I C A N A V I A T I O N , I N C .

CON-c. Pro vid e an indicat ion to the LV-GSE of an "unsafe"

condit ion in the LV-EDS pri or to l i f t -off . Unsafe beingdef ined as:which would produce ab or t ac t ion i f t he au tomat i c abor tc i r c u i t r y w e r e e n ab le d a t t h a t t i m e .

"at tempt ing to comm and an abor t to the LES

d. Disab le , in the CSM, the au tomat i c abor t c i r cu i t ry a tthe instant of LES separat io n .

e . Ini t iate the LES abort and shut down the engines onactive LV stage upon a va l id com mand f rom the CSM/LVi n t e r f ac e a bo r t c i r cu i t ry

3 .1 .1 .7 .5 .2 Func t iona l In t e r f a ces . -3 .1 .1 .7 .5 .2 .1 Launch Veh icle In te r f aces . - Inter cha nge of LV-EDS sign alshetween t h e CSM and the LV wil l be a s shown below. The

power sourc e to opera te these s igna l s s ha l l be a s ind ica ted :a . Launch Vehicle t o Comm and and Service Module Signals . -

(1 ) Automati c Abort C i r c u i t ry . - L o ss of power in twoout of 3 of the CSM/LV inter face automa t ic ab or tc i r cui t s shal l cau se ab or t ac t ion to be taken by theLES. CSM power shal l be used for th is c i r cui t ry .

(2) Automatic Enabling of Auto Abor t C i r cu i t ry a tLi f t -o f f . - A dual redundant s ig nal f rom the LV-IUto the CSM sha l l cause the au tomat i c ab or t c i r c u i t ryin the CSM t o be enabled, i . e . , to be swi tched in toa s ta te of operat ional rea din ess . CSM power shal lbe used fo r th i s c i r cu i t ry .

( 3 ) Dispiay C i r c u i t s . - C M displa i s will be act ivateda s shown below on rece ipt of s igna l s f ro m the LV.Th e se d i sp l ay c i r c u i t s a r e n o r m a l l y d e - en e r g iz e dp r i o r t o s i g na l t r a n sm i t t a l .

Y

(a) Engine Sta tus S ignals . - A d i sc r e t e s i g n al f r o mthe LV-IU to the CM wil l indic ate the non-thrust ing s ta tus of e a c h of the act ive LV engines .Eight s ignal paths w i l l be provided on Satu rn IBmiss ions fo r use dur ing SIB s t age burn and1 s ignal path fo r SIVB stage burn . On Saturn V~ i s s i c n c , s igna l pa ths wi l l h e p r o v i d e d f o ruse during SIC and S-I1 stage burn and one signal

- 1 2 -SID 63 -3 13


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SPACE and INPORSI .4TION SYS TEh lS D I V I S I O N-,*N O R T H A M E R I C A N A V I A T I O N , I N C .- path for SIVB stage burn .d i f ferent s ta ges on each vehic le sha l l u t i l izec o m m o n c i r c u i t r y .fo r th i s c i r cu i t ry .

The s ignals for theCSM power shal l be used

(b) Exce ssive Rate S ignal . - A d i sc r e t e s i g n a l fr o mthe LV-IU to the CM wil l indic ate t ha t the LVr a t e l imit in any of the pi tch, ro l l or yaw planeshas been exceeded .fo r th i s c i r cu i t ry .

CSM power shal l be used

(c) Launch Vehicle Guidance Fa i lu re S ignal . - Adis cre te s ignal f rom the LV-IU to the CM wil lindicate that the LV guidance sy ste m has fa i ledand that at t i tude con t ro l i s l o s t , (Ra te con t ro lwi l l still be opera t ive ) .used fo r th i s c i r cu i t ry .

CSM power sh al l be

(d) Abor t Req uest S ignal . - A d i sc r e t e s i g n a l f r o mthe LV-IU to the CM wil l indicate that e i the rthe Range Safety Off icer has t ra nsm it te d aDe st ru ct and Engine Cutoff com man d to the LVor tha t Launch Con t ro l Cen te r (LCC) i s indi -ca ting an abor t nece ss i ty . CSM power sha l l beu se d f o r t h is c i r c u i t r y .

(e) Li f t -of f S ignal . - A d i sc r e t e s igna l wi l l bet ran sm it te d f r om the LV-IU to the CM toind icatethat l if t-off h as occ ur re d .u se d f o r th i s c i r c u i t r y .

CSM power sha l l be

( f ) Angle of Att ack Signa l. - An analog s igna l wi l lb e t r a n sm i t t e d f r o m t h e "Q " -b a ll /C S M i n t e r -face to provide a cont inuous readout of ana e r o d y n a m i c p a r a m e t e r w h i c h i s a fu nction ofangle of a ttack . The s ig nal f ro m the "Q"-bal l

- 13 -SID 63-313


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N O R T H A M E R I C A N A V I A T I O N . I N C .

i n t e r face w i l l be a s ingl e s i gna l r epr e sen t i ngthe combined Pi tch and Yaw vec tor s to give atotal angle of a t tac k funct ion readou t .d i sp l ay pa r am e te r wi l l be d i f fe ren t i a l p re s su reac ro ss the "QlI-bal l on the LES .sha l l be used fo r t h i s c i r cu i t ry .

TheLV power

(8) S-I1 S tage Fu e l P re s s u re S igna l (On Sa turn VMiss ions Only) . - An analog sig nal wil l bet rans mi t ted f r om the LV-IU to provide a con-t inuous readout of s-I1 f u el ta n k p r e s s u r e .power sha l l be used fo r t h i s c i r cu i t ry .

L V

(h ) SIVB Stage Fue l Pressure Signa l (On Sa turn VMiss ions Only) . - An analog sign al wil l bet rans mi t ted f r om the LV-IU to provide a con-t inuous readout of SIVB fue l t ank pr es su re .LV power sha l l be used fo r t h i s c i r cu i t ry .

( i j S-I1 Stage Second Pla ne Sep ara t io n Signa l (OnSaturn V Miss ions Only) . - A di sc re t e s i gna lfr om the LV-IU wil l indicate that S-I1 secondplane sepa ra t i on (S -I1 af t sk i r t ) ha s o ccur red .CS M power sha l l be used for th i s c i r cui t ry .

b . Co mm and and Service Module to Launch Vehic le Signa ls . -

(1 ) Launch Vehicle Engine Cutoff C irc ui t ry . - An abo r tcomm and t ransmi t t ed t o e i t he r t he LES o r SM pro-pu l s ion sys t em s (a f t e r LES j e t t i son) wi l l c ause anengine cutoff s igna l to be t ran sm i t te d f r om the CSMto the LV. This s ign al wi l l co ns ist of los s of powerin a t l e a s t two ou t of t h ree ene rg i zed c i rcu i t s c r os s in gthe CSM/L'v' i n t e r face .fo r t h i s c i r cu i t ry .

LV power sha l l be used

- 1- - 14 -SID 63 -313


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SPACE and INFOR?,I;ZTION S Y S T E M S DIVISION

\ iN O R T H A M E R I C A N A V I A T I O N , I N C .

.( 2 ) Ast ronau t Manua l Con t ro l Ci r cu i t r y . - Upon as t rona u t

ini t iat ion of the following functions, sig na ls wil l bet r ans mi t t e d to the LV as ind ica ted .

Two Engine Out Auto-A bort Disable. - Whenthe as t ron au t com man ds th is funct ion , a s ignalwi l l be t ran sm it te d f ro m the CM to the LV-IU.The in t e r f ace c i r cu i t ry s ha l l cons i s t of t r ip l er edundan t wi r e pa ths which become e nerg i zedwhen the d isabl ing s ignal i s t r a n sm i t t e d . LVpower sha l l be used fo r th i s c i r c u i t r y .

LV Excessive Rates Auto-Abor t Disable . -When the as t ro nau t com man ds th i s funct ion , as igna l sha l l be t r an smi t t ed f rom the CM to theLV-IU. The in t e r f ace c i r c u i t r y sha l l cons i s tof t r ip l e redundant wir e paths which beco meenerg ized when the d i sabl ing s igna l i s t r a ns -mi t t ed . LV power s ha l l be used fo r th i s c i r cu i t ry .

( 3 ) LV-EDS.Unsafe Signal . - Pr io r to l i ft -of f , t he CMwill supply a s ign al to the LV-IU ( for subsequen tac t ion in the LV-GSE re le ase l adder to p reven tl i ft -off ) in the event the LV-EDS ci rc ui t ry i s in an"unsafe" condit ion.th i s c i r cu i t ry .

LV power sh al l be used for

3 . 1. 1. 7 . 5. 2 LV-EDS/CSM SCS/CSM G& N Int er fa ces . - In addit ion to thed i sp lays which a r e p rov ided fo r s igna l s f ro m the LV /CSMin te r f ace , t he fo llowing par am ete r s wi l l be d i sp layed fo rdetect ion of cr i t i ca l condi t ions ar i s ing f ro m LV malfunct ions ,The se d ispla ys wi l l be provided by the CSM SCS, the s igna lsfo r which wi l l be in tur n provide d by the CSM G & N s u b s y s t e m(opera t ing in the m oni to r mod e) a s d esc r i bed in S ID 62-1000 ,G & N Per fo r ma nce and In te r f ace Spec i f i ca tion .

- 15 -SID 63-313 4 # M t B i W I A L


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3 .1 .1 .83 .1 .1 .8 .1

3 .1 .1 .8 .2

a . A tt it ud e E r r o r . - A continuous readout of vehicle attitudee r r o r sh a l l be p r o vi de d.i t wi l l be ne ces sa r y tha t the CSM G&N subsys tem bepr og ra mm ed p r io r to f light in consonance wi th the p lannedLV p i t c h p r o g r a m f o r f i r s t s t age boos t .

F o r the provis ion of th is readout ,

b . To ta l At t itude. - A continuous readout of vehicle totala t t i tude sha l l be provided.

c . Angu lar Ra tes . - A continuous readout of vehicle angularra te s in each of the Pi t ch , Yaw and Rol l p lanes s hal l beprov ided .

Command and Service Module .Command Module (CM). - The CSM sha l l include a re co ve r -ab le CM. This module shall contain the communicatio n, nav i-gat ion , guidance, cont ro l , comput ing, d lspiay equipment , e tc . ,requ i r ing cre w mode select ion . In addi tion , o ther equipmentr equ i r ed dur ing nomina l o r emergen cy Ear th l and ingphas es shal l be included in the CM.fea ture s which a l low ef fective cre w obser vat io n wi th a f ie ldof view for general observation.sha l l a llow ac ce ss fo r main tenance p r io r to Ear th l aunch .The CM sha l l provide for suf f ic ient s to rag e of e xper imen talmeasurement equ ipment as spec i f i ed in SI D 62 -1001, Fl ightR & D Inst rumentat ion Speci f icat ion .

This module sh all includeEquipment a r r angement s

a . Housing. - The CM s h a l l h ou se t h r e e c r e w m e m b e r sdur ing the l aunch , t r ans lunar , l una r o rb i t , t r a nse ar tha nd e n t r y p h a se s ,

b. En t ry and Ear th Land ing. - The CM shal l be the en t ryand Ea r th landing vehic le for both nominal and em erg enc ym i s s i o n p h a se s .

c . I n g r e s s a n d Eg r e s s . - The s i d e i n g r e s s a n d e g r e s s h a tc hto the CM shal l be used during countdown o r re co ver y.No prov i s ions sha l l be made fo r ex t r a -ve h icu la r ac t iv i tyduring f l ight .

Service Module (SM). - An unman ned SM will be provided fora l l miss ions . Th is unmanned module sha l l con tain s t o re s andsy s t e m s w h ic h d o n ot r e q u i r e c r e w m a i n t e n an c e o r d i r e c topera t ion , and which a re no t r equ i r ed by the CM af t e r se pa ra -t ion f rom the SM. The SM sha l l house all propu l s ion sub-

4 . ..**dns000

!?mD

18017016015014013012011010090

ACOUST ICSCOMMAN D MODULEHIGH "Q" ABORT

X 106aCOMMAND MODULE

i i . 2 2 2. 4 45 90 i 8 0 355 71C 1. 4K2. 8K 5. 5K22.4 45 90 180 355 710 1.4K 2. 8 5.6 11.2OCTAVE BAND FREQUENCIES - CPS

F i g u r e 3 3 . Acous t ic s CM - High "Q" Abor t - E x t e r n a l - F o r w a r d of X1060-* - 114 - SID 63 -313


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N O R T H A M E R I C A N A V IA T IO N , I N C . SPACE and I N .FO R MA TI 0N SY STEMS D I V I SI O NCON

U$?G

AC OU S T IC SCOMMAND MODULE

HIGH "Q" ABORT

C O M M A N DMODULE

22.4 45 90 180 355 710 1.4K 2.8 5.6 -11 .2OCTAVE BAND FREQUENCIES-CPS

F i g u r e 35. Acous t i cs CM - High "Q" Abor t - E xt e rna l - Aft of Xa1060

- 116 - SID 63 -3 13


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N O R T H A M E R I C A N P V I A T I O N , I N C . SPACE and INFORhlATION S Y S T E h l S DIVISION

v,LuI-3Z

r:H(I]44idPQ)wxIr:0

.r(4Jidka,4Q)u

SID 6 3 - 3 1 3


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N O R T H A M E R I C A N A V I A T I O N , I N C SPACE an d IN F O R M A TIO N S Y S T E M S D IV IS IO N

hN+22v

- 127 . -W awmemnSID 63-313


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N O R T H A M E R I C A N A V I A T I O N . I N C SPACE and INFORMATION S Y S T E M S D I V I S I O N

160

150

140

130

120110

100

90

80

7060

50

40

30 0 10 20 30 40 50VAPOR P R E S S U R E , rnrn Hg

F i g u r e 48. T e m p e r a t u r e a n d H u m i d i t y N o m i n a l L i m i t

- 129SID 6 3 - 3 1 3


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N O R T H A M E R I C A N A V I A T I O N , I N C . SPACE and INFORMATION S Y S T E M S DIVISION

i

- 1 3 3 - SID 6 3 - 3 1 3

kQ)nE4i

mka,PE

z

ka,ce,L)c,

4cdkEz"


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N O R T H A M E R I C A N A V IA T IO N , I N C . SPACE an d INFORMATION SYST EM S DIVISION

110

100

90

80

..W 50LL-Iv,(3nZm

40W

30

20

10

014.0 12.0 10.0 8.0 6.0 4.0 2.0 0

BODY STATION (IN.) XFigure 53 . Saturn V, S-IC, E l Distribution-

\6

134SID 63- 313


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N O R T H A M E R I C A N A V I A T I O N , I N C . SPACE and INFORMATION SYSTEMS DIVISION

SATURN V LAUNCH VEHICLEs-ICFROM STA-115.5 TO STA 1541.O

110

IO0

90

80

7 0X

50v,v,wLLL LZ

5; 40-Lv,

30

20

10

14.0 12.0 10.0 8.0 6.0 4.0 2.0 00BODY STATION (IN.) X

Figure 55 . Saturn V I S-IC, KAG Distribution

136 SID 6 3 - 3 1 3 -


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OPERATIONAL SATURN V LAUNCH VEHICLEWET WEIGHT DISTRIBUTIONALONG THE LONGITUDINAL AXISFROM STA-115.5 TO STA 1541

6000

5000

4000

3000

2000

1000

BODY STATION IN.) XF i g u r e 58. S a turn V, S-IC,W e t Weight Distr ibut ion

- 141,142 -SID 63-313


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N O R T H A M E R I C A N A V I A T IO N , IN C . SPACE and INFORMATION S Y S T E M S DIVI

cr)I0

XcZsvi

OPERATIONAL SATURN V LAUNCH VEHICLEWET WEIGHT DISTRIBUTIONALONG THE LONGITUDINAL AXISs-I1FROM STA 1541.0 TO STA 2519.0

S-IVB i-NTERSTAGEFROM STA 2519.0 TO STA 3222.5INSTRUMENT UN IT

BODY S?AT!ON (!N XSaturn V, S-11, Wet Weight Distr ibu tionigure 61.

- 147,148 -SI D 63-313


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* / ) cN O R T H A M E R I C A N A V I A T I O N , I N C . SIAACI.: andJ Np(,)RILIATION S Y S T E h l S DIVISIONYW

Table 2. E s t i m a t e s of Metabol ic Rate ,T h e r m a l B a l an c e a n d W a t er

Gener a l Requi r ements f or Apollo Cr ew M emberC o m m a n d M o d u l e C o i n i n an d M o d u l e

Routine Fligh t Emerg ency Decompress ionPer Man Per Day Per Day

H e a t O u t p u t Btulbl bBtu

11,2001.84

12,0001.97xygen

C a r b o n D i o x i d e 2.122,800

2.273,000

L a t e n t H e a t(sweat)

Bt u 1,310 7,230

S e n s ib l e H e a t 7,090 1,870Urinary Loss 1,200 1,200

apollo command and service module system specification block 1 26 august 1964

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