Apollo Operations Handbook CSM Spacecraft 012

8/8/2019 Apollo Operations Handbook CSM Spacecraft 012

1/1007


2/1007


3/1007

* SM2A-03-SC012

12 NOVEMBER 1966

APOLLO OPERATIONS HANDB00kCO MM AN D A N D SERVICE MODULE

SPACECRAFT 012

C o n t r a c t N A S 9- 1 5 0E x h i b i t I;P a r a g r a p h 10. 3 tifl .

0

\ THIS P U B L I C A T I O N S U P E R S E D E S SM 2A -O 3_ SC O 12 D A T E D I16 S E P T E M B E R 1966.LPREPARED BY NORTH AMERICAN AVIAT ION, INC .SPACE A N D INF OR MA TIO N SYSTEMS DI VI SIO NTRAINING AND SUPPORT DOCUMENTATIONDEPARTMENT 671

A C R E W A B B R E V I A T E D C H E C K L I S T , S M 2 A - 0 3 - S C 0 1 2 / CL, ISP U B L I S H E D AS A S E P A R A T E D O C U ME N T .

P U BL I SH E D U N D E R A U T H O R I T Y OF T HE N A T I O N A L A E R O N A U T I C S A N D S PA CE A D M I N I S T R A T I O N

* I' t1SID 65-1317


4/1007

SM2A- 03-SCOlLAPOLLO OPERATIONS HANDBOOK

NOTE:The portion of the text alfrcted by the current chanRcs isindicated by a \enical l ine an the outer marlins of the page.LIST OF EFFECTIVE PAGES

TOTAL NULIBER O F PAGES I N THIS PUBLICATION IS 816,CONSISTING O F THE FOLLOWING:P a g e P a g eTi t l eA thru Ei thru x i i1 - 1 t h r u 1-202-1 t h r u 2 - 22.1-2.2-2 . 3 -2.4-2.5-2.6 - 2.7-

t h r u 2 . 1-10t h r u 2. 2-48t h ru 2 . 3-72t h r u 2.4-38t h r u 2 . 5-44t h r u 2. 6-48t h r u 2. 7-4 8

2.8- t h r u 2.8-70L. 9- 1 t h r u 2.9- 382 . 10-1t h r u 2. 10-102 . 1 1 - 1 t h r u 2. 1 1 - 6 3 - 1 t h r u 3-2124 - 1 t h r u 4-505-1t h r u 5-206-1t h ru 6-527-1t h ru 7-28-1t h r u 8 - 2 A- 1 t h r u A - 6

CHANGE INFORMATION

Thi s handbook i s sub jec t t o con t inuous change o r r ev i s ion , on a p r i o r i t yb a s i s , t o r e f l e c t c u r r e n t en g i n ee r i ng o r m i s s i o n c h a n g e s , o r t o i m p r o v e c on te nto r a r r a n g e m e n t .Li s t of Effec t ive P ag es , and by the fo l lowing me an s :The con ten t and the changes a r e accoun ted fo r by the above

Re cor d of Publ ica t ion:i s s u e is l i s ted on page B as a r e c o r d of all ed i t i ons .

The publ ica t ion da te of each bas i c i s s ue and each change

Page Change Da te :da t e .

Each page in t h i s handbook has spa ce fo r en t e r ing a changeThe l a t e s t pub l ica ti on da t e wi ll be en t e r e d in t h i s sp ace each t im e a page

is changed f ro m the bas i c i s su e .

*The asterisk indicates pager changed. added. or dclctrd by the current change.M a n u a l s w i l l b e d i s t r i b u t e d as d i r e c t ed by t h e N A S A A po l lo P r o g r a m O ff ic e . A l l r e q u e s t s f o rm a n u a l s s h o u l d be directed to th e N A S A A po l lo S pa c e c r a H P r ogr a m Of f i ce a t H ous ton , Te xa s .

A


5/1007

s l2A 0 3 -s 0 1 2A P O L L O O P E R A T I O N S HANDBOOK

RECORD O F PUBLICATION

This i s su e of the Apollo Op era t ion s Handbook,Spa c e c r a f t 0 12, dated 12 November 1966, c ons t i t u t e sa revi s io n of the handbook, dated 1 6 Se p t e mbe r 1 9 6 6 .Subs e que nt c ha nge s ma y be i s s ue d t o ma i n t a i n i n f o r -ma t i on c u r r e n t w i th s pa c e c r a f t c on f i gu r at i on t h roughcomple t ion of the miss io n . Thi s reco rd wi l l r e f l ec tthe publ ica t ion da te of any re l eas ed ch anges .

M i s s i o n B a s i c Date l 2 1966 Change Date Page B / C


6/1007

.


7/1007

S.M2A -03-SCO 1 2A P O L L O OPERATIONS HANDBOOK

LATE TECHNICAL CHANGES

The i t e m s l i s t ed below rep res ent t e chnica l changes which have been approved toolat e for inclu sion in the 12 Novembe r 1966 pr int ing of the Apol lo Op erat ion s Handbook.Source

MCRA1735MCR1591REV 3 .F E OM-53025( 10 - 13 -66)

MCRA1733( 1 0 - 1 1- 66 )

Descr ip t ion of ChangeChange S / M RCS fue l f r om b l ended hyd r a z i nemi x t u r e t o monome t hy l hyd r a z i neAddi t ion of inv er te r sync hron izer power pane lwh ic h p r ov i de s c i r c u i t b r e a k e r s f o r t he c on t r o lof power t o the phase sync hron izer un i t.T h i s is a nome nc l a t u r e c o r r e c t i o n f o r t heS-Ban d swi tch on the MDC pane l s No. 13, 2 3and 26.changes ." P T T " , " O F F " a n d "VOX". The s wi t c h i snow marked "OFF" , "OFF" a nd "T / R" .

Th i s c ha nge i s r e q u i r e d due t o w i r in gThe S - Ba nd s wi t c h wa s ma r ke d

Modif icat ion of Cre w Couch Lockouts . Th isMCR re mov es the lockout so lenoid ac tu a tora n d w i r e h a r n e s s f r o m t h e X - X a x i s s t r u tlockout mechani sm.l oc kout me c ha n i s m a s s e mb l y t o f i x i n t helocked posi t ion. T h e swi tc h on pane l No. 9a n d t h e w i r e h a r n e s s a s s e m b l y o n t h e s t r u t swi l l be r e move d .

Add an a d a p t e r t o t h e

Section Affected2 . 5

2 , 3

2 . 8 a nd 3

M i s s i on Ba s i c Da te 12 Nov 1966 Change Date Pa ge D


8/1007

s .\12A -0 3 -sc 0 1 2APO LLO OPERAT IONS HANDBOOK

SYNOPSIS O F SIGNIFICANT CHANC ES

This tabula t ion does not l i s t a ll changes , add i t i ons , , an d /o r de l e t i ons i n t he handhook.Its p u r p o s e i s t o a s s i s t t he r e ade r i n de t e rmin ing the s ign i f ican t t echn ica l changes i n eachs y s t e m .

PAR T I. TECHNIC AL CHANGESHand bookSect ion( )Aff e c te d

1L

Desc r ip t ionUpda ted lockout me chan i sms on shock s t ru t s .Upda ted f o rwa rd ha t ch cove r .Rev i sed RCSC c i r cu i t d i ag ram to i nc lude en t ry ba t t e rybackup power t o py ro bus .H2 p u r g e l i n e h e a t e rF u e l cel l H2 and 0 2 reac tant shutof f va lves holdingvo l t age con t ro lC r y o g e n i c s y s t e m r e s p o n s e a n d o p e r a t i o nRev i sed , upda ted , and a s s emb led end- to -end c i r cu i ta nd s y s t e m d i a g r a m s . A dd ed e l e c t r i c a l p o w er d i s t r i b -u t ion d i ag rams and power r equ i r emen t s .o p e r a t i n g r a n g e s a n d p a n e l r e f e r e n c e s t o m e a s u r e m e n tl i s t s .

Added

Added t abu la r da t a fo r co lo r mar k ings con ta ined onind ica to r d i sp l a ys and upda ted a r t .Added typ i ca l cha r t s f rom MMDB t o d e t er m i n e S / Cc o n s u m a b l e d a t a .Added data on S / C a t t i t ude con t ro l s ,Updated SPS Del ta V and Eng ine Gim ba l Angle cha r t s .

HandbookS y s t e m ( )A f f e c t ed

~~

GENGENSE Q

E P SE P S

E PSP R O P

S P S , E P Sand ECSRCS, SP Sa n d E P SR C SsPS

Miss ion Bas i c Da te l 2 1966 Change Date Pa ge


9/1007

. SMZA -03-SCO 12A P O L L O OPERATIONS HANDBOOK

FOREWORDThis handbook and i ts c o nt e nt s a r e r e s t r i c t e d t o th e r e q u i r e -

me n t s f o r Spa c e c r a f t 012 . It p r e s e n t s , i n o ne d oc u m en t , d e s c ri p t i o nsof the spacecra f t s ys te ms and equipment , and l i s t in gs of the f ligh tc r e w ope r a t i ona l p r oc e du r e s ne c e s s a r y f o r t he s a f e a nd e f f i c ie n tfunct ion of the spa cec raf t throughout i ts p l anned mi s s i on . Th i shandbook i s de s i gned p r i m a r i l y f o r u s e by t he fl i gh t c r e w, a nds e c onda r i l y f o r u s e by t he mi s s i o n fl i gh t c on t r o l l e r s , f l igh t p l a nne r s ,a nd t r a i n e r o p e r a t o r s .

NASA comments o r sugges ted chan ges to th i s handbook shouldbe addre sse d to the F l igh t P lanning Sec t ion , FCSD, MSC, OfficeCode C F 32, Tele phon e HU3-4271.


10/1007


11/1007

SM2A -03-SCO 12APOLLO OPERATIONS HANDBOOK

T A B L E O F C O N T E N T S

Se c t i on T i t l e1 GENERAL INFORMATION.

1 . 11 . 1 . 11 . 1 . 21 . 1 . 2 . 11 . 1 . 2 . 21 . 1 . 2 . 31 . 1 . 2 . 41 . 1 . 2 . 51 . 1 . 2 . 61 . 1 . 2 . 71. 1 . 2. 81 . 1 . 2 . 91 . 1 . 31 . 1 . 41 . 1 . 51 . 21 . 2 . 11 . 2 . 21 . 31 . 4

Spacecra f t 012 Conf igura t ion .LE S A s s e m b l y .Command ModuleF o r w a r d C o m p a r t m e n t .C r e w C o m p a r t m e n t .S/ C Con t r o l s a nd Di s p l a ysC / M M e c ha n ic a l C o n t r o l sCr e w Equ i pme n t and Equ i pme n t Ba ysFood and Water .W a s t e M a na ge me n t .Su v v a1 E quipm ent .Aft Compar tmentServ ice Module .Spa c e c r a f t LE M Ada p t e r .S p a c e cr a f t S y s t e m s .Launch Vehic le Conf igura t ion .S- 1B Boos t e rS-IVB Second Stage .Mission 209A Weight Status .Pos t l anding and Reco very

.

2 SYSTEMSDATA .2 .12 . 1 . 12 . 1 . 22 . 1 . 32 . 1 . 42 . 22 . 2 . 12 . 2 . 22 . 2 . 2 . 12 . 2 . 32 . 2 .3 . 12 . 2 . 3 . 22 . 2 . 3 . 32 . 2 . 42 .2 . 52 .2 . 5 .12 . 2 . 5 . 2

Guidance and Control .Sys tem s In te r face , Guidance and Cont ro lCoa s t i ng F l i gh t .Powe r e d F l i gh t .At mos phe r i c F l i gh t .Guidance and Naviga t ion Sy s te ms ( G & N )In t roduc t ion .Func t i onal De s c r i p t i on .Ope r a t i ona l M ode s .M a j o r Compone n t / Subs ys t e m De s c r i p t i onI ne r t i a l Subs ys t e m .Opt i c a l Subs ys t e m ,Comp u t e r Subs y s t e mPe r f o r ma nc e a nd De s i gn Da t aOpe r a t i ona l L i mi t a t i ons a nd Re s t r i c t i onsS IC Att i tudeIMU Opera t ion .

P a g e1 - 11 - 11 - 11 - 4 1 -6 1 - 61 - 61 - 6

1 - 121 - 151-151 - 151 - 151-161-161-161 - 161-191-191-191-19

2- 12 . 1 - 12 . 1 - 12 . 1 - 12 . 1 - 22 . 1 - 22 . 2 - 12 . 2 - 12 .2 - 12 .2 - 7

2 .2 - 112 . 2 - 1 12 .2 - 132.2-162 .2 - 402.2-402 .2 - 402 . 2 - 4 1

. . .M i s s i on Ba s i c Da t e l 2 1 9 6 6 Cha nge Da t e Pa ge 111


12/1007

SMZA-03-SCO12A P O L L O OPERATIONS HANDBOOK

Sec t ion T i t l e P a g e2 .2 -412 . 2-412 . 2 - 4 52. 2-46

2. 3-12. 3-12 . 3 - 32 . 3 - 32 . 3 - 72 . 3 - 8

2 .3 -422 .3 -442 . 3 - 4 52 . 3 - 4 82 .3 -512 .3 -532 . 3 - 5 32 . 3 - 5 4

2 . 2 . 5 . 32. 2 . 62 . 2 . 72 . 2 . 82 . 32 . 3 . 12 . 3 . 22 . 3 . 2 . 12 . 3 . 2 . 22 . 3 . 2 . 32 . 3 . 32 . 3 . 3 . 12 . 3 . 3 . 22 . 3 . 3 . 32. 3. 3. 42 . 3 . 42 . 3 . 4. 12 . 3 . 4 . 22 . 3 . 4 . 32 . 3 . 4 . 42 .3 .4 . 52 . 3 . 4 . 62 . 3 . 4 . 72. 3.4. 82 . 3 . 4 . 92 .3 .4 . 102 . 3 . 4 . 112 .3 . 52 . 3 . 62 . 3 . 6 . 12 . 3 . 72 . 42 . 4 . 12 . 4 . 22 . 4 . 2 . 12 .4 .2 . 22 . 4 . 2 . 32 . 4 . 2 . 42 . 4 . 2 . 52 . 4 . 2 . 62 . 4 . 2 . 72 . 4 . 2 . 82 . 4 . 2 . 92 . 4 . 2 . 102 .4 .3

Opt i c s Opera t ionT e l e m e t r y M e a s u r e m e n t s .G & N P o w e r C o n s u m pt i o n .In t e r f ace S igna l sS tab i l i za t ion and Con t ro l Sys t em (SCS)In t roduc t ionFunc t iona l Desc r ip t i on .Cont ro l Capab i l i t i e sApol lo Re fe ren ce Axes .S ub s y s t e m sF l i g h t C o n tr o l P r o f i l e s .A s c e n t .C o a s ti n g F l i g h t ( E a r t h O r b i t a l) .P o w e r e d F l i g h t ( E a r t h O r b i t al ) .E n t r y ,M a j o r C o m p o n e n t / S u b s y s te m D e s c r i p t i o n .R a t e G y r o A s s e m b l yA t ti tu d e G y r o A c c e l e r o m e t e r A s s e m b l yPi tch , Rol l , and Yaw E l e c t r o n i c C o n t r o lA s s e m b l i e s .A u x i li a r y E l e c t r o n i c C o n t r o l A s s e m b l yDisp l ay and At t i t ude Gyro A cce l e ro me te r As*semblyE l e c t r o n i c C o n t r o l A s s e m b l yRota t ion Co n t ro l sT r a n s l a t i o n C o n t r o l sF l i g h t D i r e c t o r A t t it u d e I n d ic a t or .At t i tude Se t /Gimb a l Pos i t i on Ind ica to r .Veloc ity Change Ind ica to rE l e c t r i c a l P o w e r D i s t ri b u ti o nP e r f o r m a n c e a nd D e s i g n D a t aOpera t iona l L imi t a t i ons and Res t r i c t i o ns .S /C At t i t ude ChangeT e l e m e t r y M e a s u r e m e n t sS e r v i c e P r o p u l s i o n S y s t e m (SPS) .Func t iona l Desc r ip t i on .M a j o r C o m p o n e n t / S u b s y s te m D e s c r i p t io n .P r e s u r z a t io n S u b sy s te mP r o p e l l a n t S u b s y s t e mBiprope l l an t Va lve Assemb ly .Engine In j ec to r .Abla t ive Combus t ion Cha mb er .Nozz le Ex tens ionF l igh t C ombus t ion S t ab i li t y Moni to r (FCS M)SPS E l e c t r i c a l H e a t e r s .T h r u s t Mo un t A s s e m b l i e sProp e l l an t U t i l iza t i on and Gaug ing Subs ys t em (PUGS) .P e r f o r m a n c e a nd D e s i g n D a t a

.

2 . 3 - 5 52 . 3 - 5 62 . 3 - 5 62 .3 -572 .3 -572 .3 -612 . 3 - 6 52 . 3 - 6 62 .3 -672 .3 -672 .3 -672 .3 -672 . 3 - 7 1

2 . 4 - 12 . 4 - 12 . 4 - 22 . 4 - 22 . 4 - 62 . 4 - 72 . 4 - 92 .4 -92 .4 -92 .4 -9

2 . 4 - 1 12 . 4 - 1 12 .4 -182 .4 -30

M is s ion Basic Date l 2 1966 Change Date P a g e iv


13/1007

SM2A -03-SCO12APOLLO OPERATIONS HANDBOOK

Sec t ion T i t l e P a g e2 .4 .3 . 1 Des ign Da ta2 . 4 . 3 .2 P e r f o r m a n c e D a t a .2.4. 3. 3 Pow er Consumpt ion Da ta .2 . 4 . 3 . 4 SPS E l e c t r i c a l P o w e r D i s t r i bu t io n .2 . 4 . 4 O p e r at i o na l L i m i t a t i o n s a nd R e s t r i c t i o n s .2 . 4 . 5 T e l e m e t r y M e a s u r e m e n t s2 . 5 Reac t ion Con t ro l Sys t em (RCS) .2 . 5 . 1 I n t r o d u c t i o n2 . 5 .2 S / M RCS Func t iona l Desc r ip t i on .2 . 5 . 3 S / M R C S M a j o r C o m p o n e n t / S u bs y s t e m D e s c r i p ti o n .2. 5 .3 .12 . 5 . 3 . 2 P r o pe l la n t S u b s y s te m2 . 5 . 3 . 3 E n g i ne A s s e m b l i e s .2 . 5 . 3 . 4 P r e s s u r e V e r s u s T e m p e r at u r e M e a su r in g S y s te m .2 . 5 . 3 . 5 E n g i ne T h r u s t in g L o g i c .2 . 5 . 42. 5 .4 . 1 Des ign Da ta2 . 5 . 4 . 2 P e r f o r m a n c e D a t a .2 . 5 . 4 . 3 P o w e r C o n s um p t i on D a t a S / M R C S a nd G / M R C S .2 . 5 . 4 . 42 . 5 . 5 . S/ M RCS Opera t iona l L imi t a t i ons and Res t r i c t i o ns .2. 5 .62 .5 .7 C / M RCS Func t iona l Desc r ip t i on .2 . 5. 8 C / M RCS Majo r Componen t s /S ubsys t em Desc r ip t i on .2. 5. 8. 12 .5 .8 . 2 P rope l l an t Subsys t em2 . 5 . 8 . 3 E n g in e A s s e m b l y2 . 5 . 8 . 4 P r o p e l la n t J e t t i s o n .2 . 5 . 9 C / M R C S P e r f o r m a n c e a nd D e s ig n D a t a .2. 5 .9 . 1 Des ign Da ta2 . 5 .9 . 2 Pe r fo rm ance Da ta .2. 5 .9 . 3 Powe r Consumpt ion Da ta .2 . 5 . 1 0 C / M R C S O p e r a t i o na l L i m i t a ti o n s a nd R e s t r i c t i o n s .2. 5. 10. 1 C / M RCS E l e c t r i c a l P o w e r D i s t r i bu t i on2 . 5 . 1 1 C / M R C S T e l e m e t r y M e a s u r e m e n t s .2 . 6 E l e c t r i c a l P o w e r S y s t e m (EPS) .2 .6 . 1 In t roduct ion2 .6 . 2 Func t iona l Desc r ip t i on .2 . 6 . 2 . 1 E n e r g y S t o r a g e .2 .6 .2 . 2 Pow er Gene ra t ion .2 . 6 . 2 .3 P o w e r C o n v e r s i on .2 . 6 . 2 . 4 P o w e r D i s tr i b ut i o n .2 . 6 . 32. 6 . 3 . 1 Cryo genic Stora ge .2. 6 . 3 . 2 Ba t te r i es .2 .6 . 3 . 3 Fue l Ce l l Pow er Plants .2 . 6 . 3 . 4 I n v e r t e r s .

P r e ssur za t ion Subsys t em

S / M R C S P e r f o r m a n c e a nd D e s i g n D a ta

S / M R C S E l e c t r i c a l P o w e r D i s tr i b ut i onS / M R C S T e l e m e t r y M e a s u r e m e n t s

P r e s s u r i z a t i o n S u b s y s te m

Majo r Component Subsy s t em De s c r ipt ion .

2.4-302 . 4 - 3 32 .4 -332 .4 -352 . 4 - 3 52 . 4 - 3 5

2 . 5 - 12. 5-12. 5-12 . 5 - 42 .5 -72. 5-82 .5 -9

2 .5 -132.5-152. 5-162.5-162. 5-182.5-182 .5 -192.5-192.5-192.5-232 . 5 - 2 42 . 5 - 2 72. 5-282 .5 -302 .5 -342.5-392.5-392.5-412 .5 -412.5-412 .5 -412 .5 -41

2.6- 12 .6 -12.6-12 .6 -12 .6 -22. 6-22 . 6 - 22 .6 -52 . 6 - 52 . 6 - 6

2 .6 -122.6-17

Miss ion Bas i c Da te l 2 1966 Change Date Pa ge


14/1007

SM2A-03-SCO 1 2APOLLO OPERATIONS HANDBOOk

Sect ion2 . 6 . 3 . 52 . 6 . 3 . 62 . 6 . 42.6. 4. 12 . 6 . 4 . 22 . 6 . 52.6 . 5 . 12. 6. 5. 22 . 6 . 62 . 72 . 7 . 12 . 7 . 22 . 7 . 32 . 7 . 3 . 12 . 7 . 3 . 22 . 7 . 3 . 32. 7. 3 . 42 . 7 . 3 . 52 . 7 . 3 . 62 . 7 . 3 . 72 . 7 . 42 . 7 . 4 . 12 . 7 . 4 . 22 . 7 . 4 . 32 . 7 . 4 . 42 . 7 . 4 . 52 . 7 . 4 . 62 . 7 . 4 . 72 . 7 . 4 . 82 . 7 . 52 . 7 . 5 . 12 . 7. 5 . 22 . 7 . 5 . 32 . 7 . 5 . 42 . 7 . 5 . 52 . 7 . 62 . 82.8. 12 . 8 . 22 .8 .2 . 12 . 8 . 2 . 22 . 8 . 2 . 32. 8. 2. 42 . 8 . 32 . 8 . 3 . 12 .8 . 3 . 2

T i t l eB a t t e r y C h a r g e r .Pow e r Di s t r i bu t ion .Pe r f o r ma n c e a nd De s ign Dat a .AC and DC Data .P o w e r R e q u i r e m e n t s .Ope r a t i ona l L i mi t a t i ons a nd Re s t r i c t i onsF u e l C e l l P o w e r P l a n t s .Cr yoge n i c S t o r a ge Subs ys t e m .T e l e m e t r y M e a s u r e m e n tsEnv i r onme n t a l Con t r o l Sys t e m ( ECS) .In r od uc t 1onFunc t i ona l De s c r i p t i on .M a j o r Compone n t / Subs ys t e m De s c i p t i onOxygen Supply SubsystemP r e s s u r e S ui t C i r c u i t S u b s y st e m .C a b in P r e s s u r e a nd T e m p e r a t u r e C o n t ro lW a t e r - Gl yc o l Coo l a n t Subs ys t e m .Water Supply Subsys temECS- W a s t e M a na ge me n t S ys t e m I n t e r f a c eE l e c t r i c a l P owe r Di st r i bu t ion .Pe r f o r ma n c e a nd De s i gn Da t aM e t a bo l ic D a t a .Oxygen Supply Sub sys t emP r e s s u r e S u it C i r c ui t S u b s y s te m .C a b in P r e s s u r e an d T e m p e r a t u r e C o n t r o lS u b s y s t e m .W a t e r - Gl yc o l Coo l a n t Subs ys t e m .Water Supply Subsys tem .W a s t e M a na ge me n t Sys t e m .ECS Powe r Cons umpt i on Da t a .Ope r a t i ona l L i mi t a t i ons and Re s t r i c t i onsE C S C au t io n P l a c a r d sECS Caut ion Notes .E C S G e n e r a l D a t aCa b i n De pr e s s u r i z a t i on Ra t e s .C a b in R e p r e s s u r i za t i o n R a t e s .T e1em e t y iMea su r e me n t sTe l e c ommuni c a t i on Sys t e m .In t roduc t ionFunc t i ona l De s c r i p t i on .Voi ce C ommuni c a t i ons .Da t a Ope r a t i onsTrac king and RangingUnif ied S-Band O pera t io nsM ajo r Component/ Subs ys t e m De sc r ipt onI ns t r ume n t a t i on Equ i pme n t Gr oup .Voice and Data Equipm ent Group .

Subs ys t e m .

P a g e2.6-222 .6 - 252 .6 - 302.6-302.6-3.42 .6 - 36

, 2 . 6 - 3 62 .6 - 382 .6 - 39

2 . 7 - 12 . 7 - 12 . 7 - 22 . 7 - 32 . 7 - 32 . 7 - 7

2 . 7 - 1 32 . 7 - 1 72 .7 - 242 .7 - 262.7-282 .7 - 312.7-312.7-312 . 7 - 3 22 . 7 - 3 22 . 7 - 3 22 . 7 - 3 32 .7 - 332 .7 - 332.7-382 . 7 - 3 82 .7 - 382 .7 - 392 .7 - 392 .7 - 392 . 7 - 4 4

2 . 8 - 12 . 8 - 12 . 8 - 22 . 8 - 22 .8 - 6

2.8-102 .8 - 122 .8 - 132 .8 - 142 . 8 - 1 7

Miss io n Bas ic Date l 2 1966 Change Date Pa ge v i


15/1007

SM2A -03-SCO 1 2APOLLO OPERATIONS HANDBOOK

Sect ion Ti t l e P a g e2 . 8 . 3 . 32 . 8 . 3 . 42 . 8 . 3 . 52 . 8 . 42 . 8 . 52 .8 . 5 . 12 . 8 . 5 . 22 . 8. 5 . 32 . 8 . 5 . 42 . 8 . 62 . 92 . 9 . 12 . 9 . 22 . 9 . 2 . 12 . 9 . 2 . 22 . 9 .2 . 32 .9 . 2 .42 . 9 . 32 . 9 . 3 . 12 . 9 . 3 . 22 . 9 . 3 . 32 . 9 . 3 . 42 . 9 . 42 .9 . 4. 12 . 9 . 52 . 9 . 62 . 1 02 .10 .12 . 1 0 . 22. 10.32 . 10.3. 12 . 10 .42. 10.4. 12 . 1 0 . 52 . 10.5. 12 . 1 0 . 62 .112 .11 .12 .11 .22 .11 .32 . 11 .42. 11. 52 . 1 1 . 5 . 12 . 11 .62 . 11 .6 . 1

R F El e c t r on i c s Equ i pme n t Gr oup .Antenna Equipment Group .El e c t r i c a l Pow e r Di st r i bu t ion .Pe r f o r ma n c e a nd De si gn Da t aOpe r a t i ona l L i mi t a t i ons a nd Re s t r i c t i o nsAntennasData S torage Equipment .Unif ied S-Band System .Ge ne r a lT e l e m e t r y M e a s u r e m e n t sSe que n t ia l Sys t e m s .In t roduc t ionFunc t i ona l De s c r i p t i on .Sequent ia l Event s Cont ro l Sys tem (SECS)E m e r g e n c y D e t ec t i on S y s t e m .L a u n c h E s c a p e S y s t e m .Ea r t h La ndi ng Sys t e m .M a j o r Compone n t / S ubs ys t e m De s c ri p t i onSe que n t ia l Eve n t s Con t r o l Sys t e m .Eme r ge nc y Det e c ti on Sys t e m .Ea r t h La nd i ng Subs ys t e m .Pe r f o r ma n c e a nd De si gn Da taP o w e r R e q u i r e m e n t sOpe r a t i ona l L i mi t a t i ons a nd Re s t r i c t i onsT e l e m e t r y M e a s u r e m e n t sCaut ion and Warning Sys tem (C&WS)Int roduc t ion .Func t i ona l De s c r i p t i on .M a j o r Compone n t / Subs ys t e m De s c r i p t i onEl e c t r i c a l Powe r Di s t r i bu t i on .Pe r f o r ma n c e a nd De si gn Da ta .C&W S Powe r Cons umpt i on Da t a .Ope r a t i ona l L i mi t a t i ons a nd Re s t i c i onsC&W S Ge ne r a l Da t a .T e l e m e t r y M e a s u r e m e n t s .M i s c e l l a ne ous Sys t e ms Da ta .In t roduc t ionCl oc ksD i gi t al E v e nt T i m e r s .A c c e l e r o m e t e r ( G - M e t e r ) .Command Module In te r ior -Light ingFunc t i ona l De s c r i p t i on .Command Module U pr ight ing System .Func t i ona l De s c r i p t i on .

L a u nc h E s c a p e S y s t e m . 9 .

.

3 CONT ROLS AND DISPLAYS .3 .1 Con t r o l s / Di s p l a ys Loc a t o r I ndex .

2.8-422 .8 - 572 . 8-622 . 8 - 6 22 . 8 - b 72 . 8 - 6 72 . S-672 . 8 - 0 82 . 8 - 6 82 .8 - 69

2 . 9 - 12 . 9 - 12 . 9 - 12 . 9 - 12 .9 - 4

2 .9 - 102 . 9 - 1 12 . 7 - 1 42 . 9 - 1 42 . 9 - 2 42 . 9 - 3 22 . 9 - 3 32 . 9 - 3 32 . 9 - 3 52 . 9 - 3 52 . 9 - 3 62 . 1 0 - 12 . 1 0 - 12 .10 - 12. 10-32 . 1 0 - 32. 10-32 . 10-32 . 1 0 - 32 . 1 0 - 3

2 .10-102 . 1 1 - 12 . 1 1 - 12 .11 - 12 .11 - 12 . 1 1 - 12 .11 - 12 .11-22 .11 - 22 .11 - 2

3-13 - 3

Mis sio n Bas ic Date 12 Nov 1966 Change Date Pa ge v i i


16/1007

SM2A-03-SCO 12APOLLO OPERATIONS HANDBOOK

Sect ion Ti t l e4 PERFORMANCE

Int roduc t ion .Cr e w Di s p l ay I n s t r ume n t M a r k i ngs a nd Ac c u r a c y. 14 . 1 . 14 . 1 . 24 . 1 . 34 . 1 . 44 . 1 . 54. 1 . 64 . 1 . 74 . 24 . 2 . 14 . 2 . 24 . 2 .34 . 2 . 44 . 34 . 3 . 14 . 3 . 24 . 3 . 34 . 4

Da t aSe r v i c e P r opu l s i on Sys t e m I nd i c a t o r s .Re a c t i on Con t r o l Sys t e m I nd i c a t o r sE l e c t r i c a l Powe r Sys t e m I nd i c a t o r s .Env i r onme n t a l Con t r o l Sys t e m I nd i c a t o r s .T e l e c om m u n i c a ti o n S y s t e m M e t e r s .Se que n t ia l Sys t e m s I nd i c a t o r sM i s c e l l a ne ous I nd i c a t o r s .Cons uma b l e Re qu i r e me n t sS / M RCS Pr ope l l a n t Cons umpt i on Da t aC / M RCS Pr ope l l a n t Cons umpt i on Da t aSPS Pr ope l l a n t Cons umpt i on Da t a .EPS an d ECS Cons umpt i on D a t a .RCS and SPS Thr us t i ng Da t a .RCS Tr a ns l a t i on Con t r o l ..RCS Rotat ion Cont ro lSPS E n g in e T h r u s t P e r f o r m a n c e .S / C Ope r a t i ona l Cons t r a i n t s a nd L i mi t a t i ons

4 . 4 . 1 Ope r a t i ona l Cons t r a i n t s .4 . 4 . 2 Ope r a t i ona l L i mi t a t i ons .

5 EXP ERIM ENTS AND SCIENTIFIC EQUIPM ENT DATA

5 . 15 . 1 . 15 . 1 . 25 . 1 . 2 . 15 . 1 . 2 . 25. 1. 2.35 . 1 . 2 . 45 .25 . 2 . 15 . 2 . 1. 15 . 2 . 1 . 25 . 2 . 1 . 35 . 2 . 1 . 4

In t roduc t ionScien t i f i c Equipment .Medic a l Data Acquis i t ion Sys tem (MDAS)E l e c t r i c a l C a b l e s a nd A d a p t e r s .Oc t opus Ca b l e .C o b r a C a b l e T - A d a p t e r .PGA and CWG El e c t r i c a l Ada p t e r Ca b l e sHa r d wa r e P owe r a nd S i gna l Ca b l e sMedica1 E x p e r i m e n t sI n - F l igh t Ex e r c i s e r ( M - 3A) ( M 003) .Equ i pme n t De s c r i p t i on .E x p e ri m e n t P r o c e d u r e s .C r e w m a n P a r t i ci p a t i on .R e c o v e r y R e q u i r e m e n t s .

5 . 2 . 2 I n - F l i gh t Phonoc a r d i og r a m ( M - 4A) ( M 004) .5.2. 2. 1 Equ i pme n t De s c r i p t i on .5 . 2 . 2 . 2 E x p e ri m e n t P r o c e d u r e s .5 . 2 . 2 . 3 C r e w m a n P a r t i ci p a t i on .5 .2 . 2 .4 R e c o v e r y R e q u i r e m e n t s .5 . 2 . 3 Bone Deminer a l i za t i on (M-6A) (M006) .

Pa ge4- 14 - 14- 14- 34-4 4 - 5

4-11 4- 134-15 4 - 16 4 - 18 4-18 4 - 2 5 4-27 4-30 4-34 4 - 34 4-34 4-39 4-394-394-43

5 - 1 5- 15- 15- 15- 15-5 5-5 5-7 5-75 -7 5-7 5 -7 5 -9 5- 10

5- 105-105- 105-11 5-1 15- 11 5-11

Miss io n Bas ic Date 12 Nov 1966 Change Date Page v i i i


17/1007

~

S M 2 A -0 3-SC 0 12APO LLO OPERA TIONS HANDBOOK

Sect ion Ti t l e5 . 2 . 3 . 15.2 . 3 . 25 . 2 . 3 . 35 . 2. 3. 45 . 2 .45 . 2 .4 . 15 . 2 . 4 . 25 . 2 .4 .35 . 2 . 4 . 45 . 2 . 55 .2 . 5 . 15.2 . 5. 25 .2 . 5. 35 .2 . 5 . 45 .2 . 65 . 2.6 . 15 . 2 . 6 . 25. 2. 6. 35 . 2 . 6 . 45 . 35 . 3 . 15 . 3 . 1 . 15 . 3 . 1 . 25 . 3 . 1 . 35 . 3 . 1 . 45 . 3 . 25 .3 . 2 . 15 . 3 . 2 . 25 . 3 . 2 . 35 . 3 . 2 . 45 . 45 . 4 . 15 . 4 . 1 . 15 . 4 . 1 . 25 . 4 . 1 . 35 . 4 . 1 . 4

Equ ipmen t Desc r ip t i on .E x p e r i m e n t P r o c e d u r e s .C r e w m a n P a r t i c ip a t i o n .R e c o v e r y R e q u i r e m e n t s .Human Oto li t h Func t ion (Ves t ibu l a r E f f ec t s )(M-9A) (M009) .Equipmen t Desc r ip t i on .E x p e ri m e n t P r o c e d u r e s .C r e w m a n P a r t i c ip a t i o n .R e c o v e r y R e q u i r e m e n t s .Cytogene t i c B lood S tud ie s (M-11 ) (M ol l )Equ ipmen t Desc r ip t i on .E q u i pm e n t P r o c e d u r e s .C r e w m a n P a r t i c i p a t io n .R e c o v e r y O p e r a t i o n sCar dio vas cul ar Ref lex Condi t ioning (M-48 ) (M048)Equ ipmen t Desc r ip t i on .E x p e ri m e n t P r o c e d u r e s .C r e w m a n P a r t i c i p a ti o n .R e c o v e r y R e q u i r e m e n t s .Sc ient i f ic Expe r i men t s .Synop ti c Te r r a i n Pho tograph (S -5A) (S005)Equ ipmen t Desc r ip t i on .E x p e r i m e n t P r o c e d u r e s .C r e w m a n P a r t i c i p at i o n .R e c o v e r y R e q u i r e m e n t s .Synopt ic Weat her Photogra phy (S-6A) (S006) .Equipmen t Desc r ip t i on .E x p e r i m e n t P r o c e d u r e s .C r e w m a n P a r t i c ip a t i o n .R e c o v e r y R e q u i r e m e n t s .T e c h n ic a l E x p e r i m e n t s .In - F l igh t Nephe lome te r (T -3 ) (T003)Equ ipmen t Desc r ip t i on .E x p e r i m e n t P r o c e d u r e s .C r e w m a n P a r t i c i p a t io n .R e c o v e r y R e q u i r e m e n t s .

.

.

.

.

6 CREW PERSONAL EQUIPMEN T .In t roduct ionC r e w C o m p a r t m e n t C o n fi g ur a ti o n and C r e wE n v i r o n m e n t

6 . 16. 2 M i r r o r s6 .2 . 1 I n t e r n a l V ie wi ng M i r r o r s ( C F E ) .6 . 2. 2 E x t e r n a l V ie wi ng M i r r o r s ( C F E ) .6 . 3 Crew man Opt i ca l A l ignmen t S igh t (COAS) .6 . 3 . 1 O p e r a t i o n a l U s e

P a g e5-115 - 1 1 5-125 -125- 125- 125 -125 -135-135 -135-135 -13 5 -145 - 1 4 5 - 1 45 -14 5-15 5 -155 - 1 5 5-16 5-16 5 -165 -16 5 -16 5 - 1 75 -17 5-175 -175-175 - 1 7 5-185 -185 -185-185 -185-19

6 - 16- 16-1 6-2 6 -2 6 -3 6 - 4 6 -5

~~

Bas ic Da te l 2 1966 Change Da te Pag e ix M i s s i o n


18/1007

S M Z A - 0 3 - sc 0 12APOLLO OPERATIONS HANDBOOK.

Sect ion- Ti t l e P a g e

6 -6 6 - 6 6 -6 6 -6 6 -7 6 - 8 6 -9 6 -9 6 -9 6 -9 6 -9 6 -9 6 -12

6 - 1 2 6 -12 6 - 1 3

6 . 46 . 4 . 16 .4 . 1 . 16 .4 . 1. 26 . 4 . 1. 36 . 4 . 1 . 46 .4 . 1 .56 . 4 . 26 . 4 . 2 . 16 . 4 . 2 . 26 . 4 . 36 . 4 . 3 . 16 . 56 . 5 . 16 . 5 . 26 . 66 . 6 . 16 . 6 . 26 . 76 . 7 . 16. 7. 26 . 7 . 2 . 16 . 7 . 2 . 26 . 7 . 36 .7 .3 . 16 . 7 . 3 . 26 . 7 . 3 . 36 . 7 . 3 . 46 . 7 . 3 . 56 . 7 . 46 .7 .4 . 16 . 7 . 4 . 26 . 7 . 4 . 36 . 7 .4 . 46 . 7 . 4 . 56 . 7 . 4 . 66 . 7 .4 . 76 . 86 . 8 . 16 . 8 . 1. 16 . 8 . 1 . 26 . 8 . 1 . 36 . 8 . 1 . 46 .96 .9 . 16 . 9 . 26 . 9 . 3

S p a c e Su it A s s e m b l y ( G F P ) .Space Su it Off o r Sh i r t s l eev e Env i ronm en tC o n s ta n t W e a r G a r m e n t .F l i gh t C o v e r a l l sComm unica t ions Soft Ha t .C o n s ta n t W e a r G a r m e n t E l e c t r i c a l A d a p te rE lec t r i ca l Umbi l i ca l " S leep" Adap te r .Space Suit On Envi ronm ent .P G A U n p r e s s u r i z e d o r V e n ti l at e d .P GA P r e s s u r i z e dPGA Desc r ip t i onPGA ComponentsPGA StowageT or so and Glove Stowage .Helm e t S towage .PGA Connect ing Equipmen t .P r e s s u r e G a r m e n t A s s e m b l y ( P GA ) E l e c t r ic a lA d a p t e r ( G F P ) .Oxygen Hose (Um bi l i ca l ) (GF P) .C r e w C o u c he s .C r e w C ou ch S t r u c t u r eCr ew Couch Pos i t i onsOccupied Pos i t ions .Unoccupied Po sit onsCre w Couch Componen t Desc r ip t i on .H e a d r e s t .B ack r e s tA r m r e s t s .S e a t P a n an d F o o t r e s tC r e w C o u ch P a d sMechan ica l Ad jus tmen t s .H e a d r e s t A d j u s t m e n tsA r m r e s t A d j u st m e n tsSea t Pan Ad jus tmen t Di r ec t ions .F o o t r e s t an d F o o t s t r a p A d j u s t m e n t s .D-Ring Handle Extens ionDocking Pos i t ion Adjus tment .Shou lde r S t r a p Ad justmen t .C r e w m a n R e s t r a i n t sHigh G-Load Re s t r a in t s .C r e w m a n R e s t ra i n t H a r n e s s .W e i g h t l e s s R e s t r a i n tGuidance and Navigat ion Sta t ion Res t ra in tC r e w m a n S l e ep i ng R e s t r a i n t s .F l i g h t D at a F i l e ( G F P ) .C o m m a n d e r ' s F l i g h t D a t a FileS e n i o r P i l o t ' s F l i g h t D a t a F i l eP i l o t ' s F l i gh t D a t a File .

.

.

.

6-13 6 -136 - 1 3 6-146 -156-15 6 - 1 6 6 -17 6 - 1 7 6 -186-18 6 - 1 86 -196 - 1 9 6-196-196 -216 -22 6-22 6-22 6 - 2 36 -23 6 -23

6 - 2 3 6 - 2 4 6 - 2 5 6 -26 6 -27 6 - 2 86 -28 6 -29

' l 2 1966 Change Da te Pag e XM i s s on Bas i c Da te


19/1007

Sh12A-03-SC012APO LLO OPERA TIONS HANDBOOK

Sec t ion6. 106. 10. 16 . 10. 26 . 10 .36 . 1 0 . 46 .10 . 56 . 1 0 . 66 . 1 0 . 76 . 1 0 . 86 . 1 0 . 96 . 10. 106. 10. 116 . 1 0 . 1 26. 10. 136.10. 13 . 16 .10 . 13 . 26 . 10. 146 . 10. 14. 16 . 116 . 126 . 12. 16 . 12 . 26 . 12. 2 . 16 . 1 2 . 2 . 36. 136 . 13. 16 .13. 26 . 1 3 . 36 . 1 3 . 46. 13 . 56 . 146 . 1 4 . 16. 14. 1. 16 . 14. 1 . 26 . 14. 1 . 36 . 1 4 . 1 . 46. 14. 1. 56 . 1 4 . 26 . 14. 2.16. 14 .2 .26 . 14. 2. 36 . 1 56 . 15. 16 . 15 .26. 15 .3

6. 1 2 . 2 . 2

~~

Ti t l eCrew man In -F l igh t Too l Se t and W orkshe l f (G FB)Torque W rench (Too l A) .Adap te r Hand le (T oo l E) .1 0 - In c h D r i v e r ( T o o l H ) .4 - In c h D r i v e r ( T o o l L ) .E m e r g e n c y W r e nc h ( T o o l B ) .T-Hand le (Too l C ) .End Wrench (Tool F ) (2 )5 / 3 2 - I n c h S h o r t D r i v e r ( T o o l J )4- Inch Torq ue Se t Dr ive r (Too l R)In -F l igh t Too l Se t Te the rD-Ring Extens i on Handle (Tool N )Opera t iona l UseStowageIn-Fl ight Tool Set Stowage Pouch and Tool SetD r a w e rMisce l l aneo us S towage .W o rkshe l f AssemblyUsage .Dr ink ing W ate r Subs ys t emFood .U s eStowageL E B F o o d Stowage Compar tmen t .R H E B A u x i li a r y F o od C o m p a r t m e n t D r a w e rLHEB Food S towage Compar tmen tP e r s o n a l H yg ie n e ( G F P ) .Cleans ing of T e e t h - O r a l H y gi en e A s s e m b l yWet Cleans ing Cloth .Dry Clean ing C lo th .Towel sT i s s u e D i s p e n s e r s .Medica l Supp l i e s (GFP) .Moni tor ing EquipmentCl in i ca l Phys io log ica l Moni tor ing Ins t ru men t Sc tP e r s o n a l B i o m e d i c a l S e n s o r s I n s t r u m e n t A s s e m b l yB i o m e di c a l P r e a m p l i f i e r I n s t r u m e n t A s s e m b l y .B i o i ns t r um e n t a ti o n A c c e s s o r es KitP e sonal Radia t ion Dos i m e e r sM e d i c a l K i t ( G F P ) .Packag ing .StowageMedica l Kit Addi t ional Usage .S u r v i v a l K i t ( G F P ) .StowageSurv iva l K it Con ta ine r O pera t ion .Conten t s o f t he Surv iva l K i t s .

.

. ...

.

.,

.

P a g c6-306-31 6 -31 6 -3 16 -31 6 -31 6 -32 6 -326-32 5 -326-326 -326 - 3 2 6 -32 6 -35 6 -35 6 -356 - 3 6 6 - 3 7 6 - 3 8 6 -38 6 -38 6 -38 6-396-396 -39 6 -39 6-40 6 -40 6 - 4 1 6 -41 6-41 6 -41 6 -416 -42 6 -426-42 6 -43 6 -43 6 -44 6 - 4 4 6 - 4 4 6 - 4 4 6 - 4 4 6 -46 6 -46

Mis s ion Bas i c Da te 12 Nov 1 9 6 6 Change Date Pag e x i


20/1007

SM.! -4 0 3 - S C 0 2APO LLO OPERATIONS HANDBOOK

Se c t i on T i t l e Pa ge6 . 1 5 . 4 Descr ip t ion and Use of Surv iva l Ki t Components . 6-47 6 . 15 .4 . 1 Li f e r a f t s 6-47 6 . 1 5 . 4 . 2 B e a c o n / T r a n s c e i v e r . 6-47 6 . 15 .4 . 3 Sur v i val L i gh t s ( 2 ) . 6-48 6 . 1 5 . 4 . 4 Sur v i va l G l a s s e s ( 3 ) . 6-48 6 . 15 .4 . 5 Surv iva l Knives ( 2 ) . 6-49 6 . 1 5 . 4 . 6 W a t e r C a n s ( 3 ) . 6-49 6 . 15 .4 . 7 Desa l t ing Ki t s ( 2 ) P l u s T a b l e t s ( 1 6 ) . 6-49 6 . 1 5 . 4 . 8 Eme r ge n c y M e d i c al Su r v i va l K i t . 6-496 . 1 5 . 5 S e a W a t er P u m p ( C F E ) . 6-49 6 . 16 Stowage 6-50

7 SYSTEM SCHEMATICS . 7- 1

Miss i on Bas ic Date 12 Nov 1 9 6 6 Change Date Page x ii


21/1007

SM2A - 0 3 - S C O 12APOLLO OPERATIONS HANDBOOK

t

GENE RAL INFORMATION

SECTION 1GENERAL INFORMATION

INTRODUCTION.This se c t ion conta ins informat ion re la t ing to the Xpol lo s pa ce cra f t 012

conf igura t ion , and a descr ip t io n of the launch vehic le and boos ter us ed forthe mi s s ion .

1 . 1

1 . 1 . 1

SPACEC RA F T 0 12 CONFIGURA TION.Spacecraf t 012 ( f igu re 1 -1 ) con for ms to a Block I CSM configurat ion

cons i s t i ng of a l aunch e scape sy s t em (LES) a s se mb ly , command modu le( C / M ) , s e r v i c e m o du le ( S / M ) , and the sp ace c ra f t l una r excur s ion modu leadap te r (SLA). Th i s spacec ra f t , de s igned fo r an ea r t h o rb i t a l mi s s ion ,does not conta in a luna r module (L M) wi th in i t s adap ter .of the launch vehic le used wi th spacec raf t 012, re fe r to parag raph 1 . 2 )

( F o r a d e s c r i pt i o n

NOTE The Block I conf igura t ion mi ss i on s for the Apol lopr og ra m provide the fo l lowing:0 Command modu le and se rv i c e modu le deve lopment fo r

e a r t h o r b i t a l m i s s i o n s0 Demons t r a t i on of sy s t e ms ope ra t iona l capab i l i t i e s

inc luding a l l types of ab or ts , l a nd a n d w a t e r r e c o v e r y ,Sa tu rn IB and Sa tu rn V opera t ion and capabi l i ty , ands y s t e m s o p e r a t io n d u r i n g e a r t h o r b i t

0 Development of qual i f ied te am s for checkout , launch,manned space f l ight ne twork ( MS F N) , r ecove ry , andf l ight analys is .

LES ASSEMBLY.T h e L E S a s s e m b l y ( f igu re 1 -1) p rov ides t he means fo r s epa ra t i ng the

C / M f r o m t h e l au n ch v e h ic l e d u r i ng p a d o r s u b o r b i ta l a b o r t s .cons i s t s of a Q-ba ll i n s t rumen ta t ion a s s em bly (nose cone ) , ba l l a s t com -p a r t m e n t , c a n a r d s u r f a c e s , p i tc h co n t r o l m o t o r , t o w e r j e t t is o n m o t o r ,l aunch e scape mot o r , a s t ru c tu ra l sk i r t , an open- f r ame tower , and a boos tp ro t ec t ive cove r (BPC) .which enc loses t he rocke t mo t o r s , i s se cu re d to the upper por t ion of the towe

T h i s a s s e m b l y

T h e s t r u c t u r a l s k i r t a t t h e b a s e of t he h o u si n g,

SPACECRAFT 012 CONFIGURATIONMiss ion Bas ic Date l 2 N o v 1966 Change Date Page 1 -1


22/1007

SMZA -03-SCO12APOLLO OPERATIONS HANDBOOK

GENER AL INFORMATION

Q-BALL (NOSE CONE)PITCH CONTROL MOTOR

JETTISON MOTOR

LAUNCH ESCAPE MOTOR

STRUCTURAL SKIRT

LAU NCH ESCAPE TOWER

TOWER ATTACHMENT (4)

C O W N O MODULE

C/M TO S/M FAIRING

SERVICE MODULE

EP S RADIATORECS RADIATOR

SPACECRAFT LEMADAPTER (SLA)- S f 5 ENGINE EXPANSION NOZZLE

S I A PANEL JUNCTIO N(BETWEEN FWD A N D A f lPANELS)

5-IVB INSTRUMENT UNIT( S H W N AS REFERENCE)

F i g u r e 1-1. Sp ac ec raf t 012 Configurat io n (Sheet 1 of 2 )SPACECRAFT 012 CONFIGURATION

Miss ion Bas ic Date 12 Nov 1966 Change Date P a g e 1 - 2


23/1007

s1M2L1-03-sc012AP OL LO OPERA TIONS HANDBOOK

ASens ingi s no t r e qu i r e d , t he I l I U i s p l a ce d i n s t a ndby ope ra t i on t o c ons e r ve e l e c t r i c a lpower .a l s o be p l a c e d in s t a ndby ope r a ti on t o c ons e r ve e l e c t r i c a l powe r .guidance a nd navigat ion funct ion i s t o be r e s t o r e d , t he I l l U and -AGC a r ereac t iva ted , wi th the .AGC us in g the l a s t computed ve loc i tv as the ba s i s forfur the r veloc itL computa t ions , New posi t iona l da t a mus t be acqui re d i r o mopt ica l s igh t ings or LISFN t h r ough t e l e me t r y o r vo ic e c ommuni c a ti ons .

The -AGC i s used m or e ex tensivelx . than the IUU , howev er , i t wil lI\ hen t h e

In i t i a l pos i t ion and a t t i tude informat ion a s wel l as per iodic upda t ing o it h i s i n f o r ma t i on i s made through use of the opt i c s .by the naviga tor m aking two o r m o r e l a n d m a r k a n d / o r s t a r s i g h t in g s .s i gh t i ngs a r e ma de by a cqu i r i ng t he s t a r - l a ndm a r k wit h t he SCT a nd l o r SXT.When the v iewed objec t i s cen te re d , a ma r k c omma nd i s i n i ti a t ed . The -AGCr e a d s t he op ti c s a ng l e s , 1 1 , lU a n g l e s , and t i me , in conjunc t ion wi th in te rna lp r og r a ms , to de t e r mi ne t he s pa c e c r a f t pos it i on. Th i s pos i t ion i n fo r ma t i ona nd t he s pa c e c r a f t ve l oc it y a r e u s e d t o c ompu t e a n e s t i ma t e d t r a j e c t o r y .The ac tu a l t r a jec tor :. i s c ompa r e d wi th p r e v i ous t r a j e c t o r \ . da t a t o ge ne r a t et he t r a j e c t o r y e r r o r , i f a n y, f o r f u r t h e r re f e r e n c e . O p t i ca l m e a s u r e m e n t sa r e a l s o u s e d i n a l i gn ing t he IXIU t o a s pe c i fi c r e f e r e n c e o r i e n t a t i on.

Th i s i s a c c ompl i s hedThe

T h e I MU ( f i gu r e 2 . 2 - 2 ) c on t a i ns t h r e e i ne r t i a l r a t e i n t e g r a t i ng gy r os( I R I G s ) , t h r e e a ngu l a r d i f f e r e n t i a t i ng a c c e l e r ome t e r s ( -ADAS), and t hr eepul sed in tegra t ing pendulous acc e l e ro me te rs (PIP-As). The IRIGs , PIP-As,and one -ADA a r e moun t ed o n t he s t a b l e p l a t f o r m wh i c h is gimbaled to p r o -v ide th ree degrees of f reedom .the middle g imbal .the IRIGs and - l D - A s in conjunc t ion wi th e lec t roni c s t ab i l i za t ion loops .d i sp lac ement of the p la t form is sen sed by the IRIGs which produce outputs igna l s repres enta t iv e of the magni tude and d i re c t io n of d i s p l a c e me n t .AD-As s e ns e t he d i s p l a c e me n t r a t e a nd pr oduc e ou tpu t r a t e c on t r o l s i gna lst o ma i n t a i n c o r r e c t s t a b i l i z a t i on loop c on t r o l r e s pons e .s igna l s a r e appl ied to se rv o am pl i f i e r s , which condi tion the s igna l s to dr iveg i mba l t o r que mo t o r s .p l a t f o r m o r i e n t a t i on by dr iv ing the g im bals un t i l the l R I G s i gna l s a r e nu ll e d.

The two remain ing -AD.As a r e moun te d onThe s t a b l e p l a t fo r m i ne r t i a l r e f e r e nc e i s ma i n t a i ne d 12)--An!-

TheThe IRIG and -4D.A

T h e g i m b a l t o rq u e m o t o r s t h e n r e s t o r e the in i t i a l

GUIDANCE AN D N.4VIG-4TIOK SYSTEll2 . 2 - 3M i s s i on Ba s i c Da te 12 ~ O V966 Change Date Pa ge


80/1007


81/1007

IIIIIIIIIIIIIIIII

VISUAL%E: 4 4 -UNDM A RK SA N D H O R IZ O NI X U N N I O N

NOTES: I . AG C inpuh a d utpub s h o r n arepment at variRn times, depcdinpupan m o de of opemtion, but no tconcurrently.

2. There caponenh are phpicallymounted om th e I M U but i l lvr tmteda hown for clar i ty .

M A NUA Li M O DE S I G NA UIRUNNIONDRIVE

S C A N N I N GTELESCOPEAND SEXTANT

COUPL lNGDI S P UY IUNIT TRUN NION DRIVE SIGNALS

SHAFT

I

A ! SHAFT CRIVE SIGNALCIOUPLINGSHAFT DRIVE DlSPuySIGNAL UNlT

(*) A ND (-) XA V E L O Cl l Y 1

DRNE I UPLINK DATA FROM MSFN1 Y G T A L

- -DRIVE SIGNAL

ATTITUDEIMPULSECONTROL

THRUST C O W M STO REACTIONCONTROL SYSTEM

I

M O L L 0GUIDANCECOMPUTER

IMP

MUOS-MUOS

+XC(A


82/1007


83/1007

IM U INNER GIMBALc

ANALOGCONVERTER

INNER GIMB4LRESOLVER SIGNALIGIMBAL INNER IMBAL DIFFERENCEPOSITION COUPLING SIGNAL

UNIT'OMMANE DI S P UY 1

ANGLE SIGNALS

CRIVE SIGNAL"

FROM MSFN-D l S P U Y A N D COMMANDSEYBOARD(2 LOCATIONS)

L * MO DE S I G N A U-ANGLE SIGNALS IDRIVE SIGNALS($ A N D (-) YAVELOCITY I

(*) A N D (-)XAVELOC ITY I

M O L L 0GUIDANCECOMPUTER

' O S I T I O N CO M M A M S . 4 IMU/CDU

I I1 1 TO NNERSHAFT ANG LE G I M M LI J

C O A E EALIGN..Y-IRIG TORQUE AM PY-IWG TORQUECALIBRATION GENERATOR

A U G N M OD E -NL Y ) M IDDL E G I W A LRESOLVER SIGNALI U/CD UAU MIDDLE GIMBAL' COMMANDS--

I Ii 1 I TO MIDDLESHAFT AN GLE G l M M L C OA RS

Z-IRIG TORQUEA L I G N N A P

Z-IRIG TORQUEGENERATOR TO OUTERGIMBAL COARS

COMMANDS(IS5 FINEA L I G N M O DEO NL Y ) -MU OUTER GIM BALQSlTlON COMMANDS I A U G N AMPOUTER G lM M LRESOLVER S IG NA L-I

Y A W ~ I T C HRESOLVER(GIMBALA X E S TON A V BASEA X E S )

3T FIXEDRESOLVER( N A VEASE AXESTO S/CAXES)

S/C BODAN D OFATTITUDE

OFFSETATTITUD

S/C BODERROR S)S/C W DATTITUD(FMDISPLAY SIGNAL 16X-OFFSET ROLL ERROR S IG NA

1 b SHAFT ANGLE JDO W NL IN KTO MSFN+ ATA TERNARYSWITCH AN D X-IRIG TORQUEX-IRIG TORQUE CALIBRATION GENERATOU

COMMANDS(ISS FINEA U G N M O D E O NL Y )I SPS E N G I N E ON/OFF COMMANDS

1


84/1007


85/1007

PITCH Ac M)DY PITCH ATTITUDE I , ORRECERROR SIGNAL II

I11IIFUNCTIONS OF INNERA N D MICDLE GlMeALS) I IYAW I

I IiE R R C X SIGNAL

EC AI AI I

BODYYAW ATTITWE ! IIIGNU(FUNCTIONS OF INNER,MIDDLE, AN D OUTERGIMALS)

BE4 SIGNALS

fAW ATTITUDECORRECTION SIGNALS

REACTIONC O M R O LSYSTEM

t

STABLE MEMBERI l h l h I C D r,.. . . , ,

SU

OUGIM

GIMWL RESOLVERANGLE SIGNAL TOFLIGHT DIRECTORAll ITUDE INDICATOR

MIDDLE G I h U A L q

SIGNALSTCH GIMBALO M M A NCS1 YAW GIM BAL SERVICEPROPULSIONSYSTEMOMMANDS

THRUST ON/OFF

IAUXILIARY C0MMAN)s

II ECA-I

(+) AN D (-) 2(+) AN D (-1 X(+) AN D (-) Y

VELOCITY CHAIGE SIGNALSVELOCITY CHANGE SIGNALSVELOCITY CHANGE SIGNALS

*


86/1007

,A,.:, &. :. ' . '-. . ,. ,


87/1007

SMZA -03-SCO 12APOLLO OPERATIONS HANDBOOK

YSTEMS DATA

ITORQUE MO TO R DRIVE SIGNAL I

Figure 2. 2 - 2 . G & N Sys tem Funct ional Block Diagram

GUIDANCE AND NAVIGATION SYSTEMBasic Date' . l 2 1966 Change Date page2 . 2 - 5 1 2 . 2 -M i s s i on


88/1007


89/1007

SM 2 A -0 3 - SC0 1 2APOLLO OPERATIONS HANDBOOK

SYS TEMS D.4T-4The op t i cs p r ov i de a c c u r a t e s t a r a nd l a ndma r k a ngu l ar me a s u r e -

Sightings a r e acc ompl i shed by the naviga tor us ing the SXT ande n t s .SCT.hand cont ro l l e r o r manual ly us ing a un iver sa l too l , as des i re d .a x e s a r e p a r a l l e l .a s d e s i r e d .ma te 6 0-deg ree f ie ld of view.t o a c q u ir e a nd c e n t e r s t a r s o r l a n d m a r k s p r i o r t o S X T us e .provi des 28-power mag nif ica t ion with a 1. 8-d egre e f ie ld of view.SXT has two l ines of s igh t , enabl ing i t to me as ur e the included anglebe tween two objec t s . Thi s re qu i re s two l ines of s igh t which enable thetwo v iewed objec t s to be super impose d . F o r a s t a r - l a n d m a r k s i gh t i ng ,the l and mark l ine of s igh t i s c en te red a long the SX T shaf t ax i s .imag e i s moved toward the l and mar k by ro ta t ing the shaf t and t runnionaxes unt i l the two v iewed objec t s a re su per imp osed . The shaf t andt runnion angles a re rep ea ted by the opt i c CDUs. When the naviga tor i ssa t i s f i ed wi th image pos i t ion s , he i s su es a ma rk com mand to the -4GC.The -4GC reads the opt ics CD U a ng l e s , I M U CDU angles , and t im e , andcompu tes the posi t ion of the sp acecraf t .on s t o r e d s t a r a nd l a ndma r k da t a wh ic h ma y a l s o be u s e d by the .AGC tor e que s t s pe c i f i c s t a r s o r l a ndm a r ks f o r nav i ga t ional s i gh t i ngs . Two o rm o r e s i gh t i ng s , on t wo o r m or e di f f e re n t s t a r s , mus t be t a ke n t o pe r f o r ma comple te pos it ion de te rmina t i on .

The opt i cs a re pos i t ioned by dr ive mo tors comm anded by the opt i csThe shaf tT r unn i on a xe s ma y be ope r a t e d i n pa r a l l e l o r o f f s e t ,

The SCT is a unity power ins t rum ent provid ing an approx i -I t i s u s e d t o ma ke l a ndma r k s i gh t i ngs a nd

The SXTThe

T h e s t a r

The AGC bases the computat ion

2 . 2 . 2 . 1 Opera t iona l Modes .The G&N s ys t e m i s ope r a t e d i n s i x ba s i c ope r a t i ona l mode s .

Selec t ion of any one mode is acco mp lish ed manual!y by the f l ight crew o rautomat ica l ly by the ACC. The ba s i c mode s a r e a s f o ll ows:

00 Zero encode0 Coa r s e a l i gn0 Fi ne a l i gn0 Att i tude control0 E n t r yThe sys tem conf igura t ion nec ess ary to opera te in an) - of the modes i s

Xloni tor ( in i t ia t ed by S C S mode se lec t ion)

es tab l i shed by re lay swi tch ing.The moni tor mode i s used a t launch, asce nt , and dur ing orb i t unt i l

CSM/S- IVB s e pa r a t i on , t o p r ov i de f li gh t pa th da t a f o r c r e w d i s p l a ys .c oa r s e a l i gn, f ine a l i gn , a nd z e r o e nc ode mode s a r e u s e d t oa l ign the IX lU af te r s t andby per iods o r to acqui re a new s tab le p la t formor ien ta t ion . The at t i tude cont ro l mode provid es for spacec raf t a t ti tudecont ro l and navigat ion computa t ions to mea sur e pos it ion and ve loc i ty .en t r y mode provides cont ro l of the spac ecraf t l if t vec tor dur ing en t rypha s e .

The

The

C U IDA N CE 4ND N AV IG=Z TION SY T E11Miss ion Bas ic Date l 2 Nov l966 Change Date Pag e 2 . 2 - 7


90/1007

SMZA-03-SCO 2APOLLO OPERATIONS HANDBOOK

SYSTEMS DATA

The ISS and CSS wi l l be op e ra t ed in on -s t andby cyc l e s t o conse rveThe OSS is shu t off

e l e c t r i c a l p o w e r.a tu r e , and the CSS main ta ins AGC t iming funct ions.when not in us e .subsys t ems , s t andby i s n ot c o n s i d e r e d a s b a s i c m o d e .

Dur ing s tandby opera t ion , the ISS main ta ins IMU t emp er -Since s t andby ope ra t ion t ime va r i e s fo r ea ch of t he

2 . 2 . 2 . 1. 1 Moni tor Mode,Dur ing p re l aunch ope ra t ions , t he G & N s y s t e m i s a l igned to t he des i r ed

l a u nc h r e f e r e n c e a t t it u d e a n d g y r o c o m p a s s e s t o m: i n t a in t h i s a t t i t ude .Approx ima te ly 3 minu tes p r io r t o l aunch , t he gy r o compass ing i s s t oppeda n d th e s y s t e m b e c o m e s i n e r t ia l l y r e f e r e n c e d .mon i tor in g the f l ight pa th angles by dr iv in g the Ine r t ia l Coupl ing DisplayUnit s ( ICDUs) t h rough p rog ram med a t t i t ude changes .com pare d wi th t he IMU g imba l ang le s t o p roduce f l ight pa th e r r o r s igna l swh ich a r e d i sp l ayed by the FDAI e r r o r need le s .wi th r e spe c t t o t he IMU or i en t a t i on , i s displayed by the FDAI bal l .(P re l au nch FDAI r ead ings a r e 164. 76-degree ro l l , 58 .3 0-deg ree p i tch , and9. 69-d egree yaw, wi th res pe ct to the navigat ion axi s symb ol ,o r b i t i n s e r t i o n i s 0-deg ree ro l l , 310. 5-deg ree p i tch , and 0-deg ree yaw,as sum ing a 180-degree ro l l ha s been pe r fo rm ed and launch pad 3 7 i s u s e d . )Dur ing boos t p r io r t o l aunch e scape tower (L ET ) e t t i son , t he AGC d i sp laysthe fol lowing:

Upon lift-off the ACC beg insThe ICDU angl es a r e

To ta l spac ec ra f t a t t i t ude ,

Display a t

REGISTER 1 - Ine r t ia l fl ight pa th angle ; iner t ia l ve loc ity wi th re spe ctt o l o c a l h o r i z on t a l i n d e g r e e s .

REGISTER 2 - Iner t i a l ve loc i ty in f t per s e c .REGISTER 3 - Alti tude above launch pad in naut ica l mi l es ( N M s )

Upon rece ip t of LE T j e t t i son s igna l s t he d i sp l ays change t o the fol lowing:REGISTER 1 - P r e d i c t e d G s f o r f r e e - f a l l a n d e n t r y a t 6 0 - d e g r e e

bank angle .REGISTER 2 - Alti tude of per ige e above the mean equ ator ia l radius

in NMs.REGISTER 3 - Time of f ree- fa l l t o 300, 000 i t above mean equa to r i a l

r ad ius i n minu te s and seconds .This d isplaye d data provid es the f l ight c rew wi th suf f ic ient informat ion tomake ab or t o r con tinue dec i s ions ; however , i f t ime i s not cr i t ica l , thedecis ion i s mad e by the f l ight c re \v and MSFN jo in t ly .

GUIDANCE AND NAVIGATION SYSTEM*2 . 2 - 8Miss ion Bas i c Da te l 2 Nov l 9 6 6 Change Date Page


91/1007

S.Lf2-A -0 3 - SC U 1 2APO LLO OPERATIONS HANDBOOK

SYSTEMS DXT.42 . 2. 2 . 1.2 Ze ro Encode ; \lode.

The z e ro encode mode enab le s co r r ec t ion of t he CDC da t a s to r ed in-4GC. Th is mode i s u s e d t o e n s u r e t h a t t h e r e f e r e n c e a n g le s c o nt a in e d i nthe CDU reg i s t e r s of the XGC co rre spo nd wi th the ac tua l CDU angles .i s accompl i shed by d r iv ing the CDUs to ze ro , then c le ar ing the -4GC C D Ur e g i s t e r s .r eg i s t e r s t o ma in t a in co r r ec t CDU ang le s by coun t ing pu l se s f r om the CDL'd ig i t a l encode r s .

Th i sTh i s s t a r t s t he -4GC CDU reg i s t e r s a t ze ro and enab le s t he

2 . 2 . 2 . 1 . 3 Co ar se -Align l lod e .The c oa r se a l i gn mode enab le s s t ab l e p l a t fo rm a l ignmen t t o witb. in

F r e r e q u i s i t epp rox ima te ly 3 degre es o f a des i r e d p l a t fo rm o r i en t a t i on .in fo rma t ion to accompl i sh coa r se a l i gnmen t cons i s t s oi t he des i r ed p l a t t o rnio r i en t a t i on and p re sen t spacec ra f t a t t i t ude .

The des i r ed p l a t fo rm o r i en t a t i on ang le s a r e computed b y an a1:gn-m e n t p r o g r a m e x e c ut e d bb- he -4GC.c ra f t a t t i tude immedia t e lb - p r i o r t o coa r se a l i gnmen t b\-making two o rm or e s igh t ings on s t a r s o r l andm arks . Upon comple t ion of the s igh t ings .the =IGC re ad s the opt ic angles and com pute s the g imb al angles necessar !:to a t ta in the des i re d p la t form or ienta t ion . The -1GC genera tes dri1.es igna l s t o pos i ti on the CDU res o lv e r s t o the r equ i r ed g imba l ang le s . TheI l IL-CDU reso lve r e r r o r s igna l s , gene ra t ed by r epos i t i on ing the CDUs ,a r e app l i ed t o the g imba l t o rque se r vo am ps Ivh ich d r i l - e t he g imba l t o rquemo to r s t o pos i ti on the p l a t fo rm to t he des i r ed o r i en t a t i on .

The nav iga to r de t e rm ines t he spac e -

(1

The s table p la t for m or ie nta t ion wi l l normal l>- be suc h tha t the X-axisl i e s a lo rlg the spacec ra f t t h r us t vec to r du r ing a l l powered phases , excepta sce n t , and a long the spacec ra f t s t ab i l i t y axis dur ing en t ry .

2 , 2 . 2 . 1. 4 Fi ne -Align l io deThe f ine a l i gn mode c omple t e s s t ab l e p l a t fo rm o r i en t a t ion to t he

r e q u i r e d d e g r e e of a c c u r a c y .s igh t ings , u s ing on -boa rd da t a and the op t i c s t o acqu i r e t he des i r ed s t a r s .Upon rece ip t of the optic ang les the -4GC co mp ute s the I l 1 U a n g l es n e c e s -sa ry t o comple t e the a l i gnmen t .repea ted by the ine r t ia l CDUs which a r e mon i tored by the .AGC t o de terr r . inethe ac tua l I;\\IU or ienta t ion .an) - e r r o r be tween the ac tua l I l l K or i en t a t ion and the de s i r e d o r i en t a t i on .Thes e t o rqu ing pu l se s a r e app l ied t o t he [RIG torquing coi l s . The IRIGs inconjunct ion wi th the s tabi l iz a t ion loops , repo s i t ion the s table p la t forni unt ilt he des i r e d o r i en t a t ion i s a t t a ined . Upon comple t ion of f ine a l ignment . theIMv/CD U r eso lve r s igna l s and the s t ab i l i za ti on loop s igna l s a r e a t nu ll .

T h e n a v ig a t or m a k e s tw o o r m o r e s t a r

In the f ine a l ign mod e, the I l l U a n g l e s a r eT he =\GC gene ra t e s t o rqu ing s igna l s t o cance l

T h e s!-stem coni igura t io n requi red fo r f ine a l ign mode a l so appl iesI X l U r e s o l v e r s i g n a l s t o th e S CS a s a p p a r e n t a tt i tu d e e r r o r s i g na l s .p r e ve n t t h e s e s i g n a l s f r o m a p p e a r i n g a s a c t u a l s p a ce c r a f t a tt i tu d e e r r o r sthe SCS mus t be ope ra t ed in an SCS mode which r e j ec t s G &K der i rred s ign als

T o

GUIDXKCE AKD iULAVIG-ATIOK SYSTELI2 . 2 - 9Mi ss on Bas i c Da te 1 2 Nov 1966 Change Date Pag e


92/1007

SMZA-03-SC012APOLLO OPERATIONS HANDBOOK

SYSTEMS DATA

2 . 2 . 2. 1. 5 Att i tude Contro l Mode.The a t t i tude con t ro l mode p rov ides s pace c ra f t a t t i t ude change sens ing ,

gene ra t e s e r r o r s igna l s fo r spacec ra f t a t t i t ude con t ro l , ve loci ty changes ignal s for updating AGC veloci ty inform at ion , and s ig nals fo r t iming SPSe n g in e t h r u s t t e r m i n a t i o n c o m m a n d s .

Dur ing spacec ra f t a t t i t ude con t ro l , t he IMU g imba l r e so lve r s s ense anydispla cemen t of the spac ecra f t wi th res pec t to the s table p la t form or ienta t iona n d p r od u c e c o r r e s p o nd i n g e r r o r s i g n a l s .d i r ec t ly t o t he SCS-FDA1 ba l l f o r e r r o r d i sp l ay and to the i ne r t i a l CDUre so lv e r s . The IMU-CDU e r r o r . s i gna l s a r e d i sp l ayed on the IMU con t ro lpane l , r e so lved in to spacec ra f t axe s , and app l i ed t o the SCS. If the e r r o rs i g n a ls i n d ic a t e a n a t ti t u de e r r o r l a r g e r t h a n th e s e l e c te d d e a d ba n d ,a p p r o p r i a t e RCS eng ines a r e f i r ed and the des i r ed s pacec ra f t a t t i t ude i sr e s t o r e d .

T he e r r o r s i g n a l s a r e a p p l ie d

F o r d e l ta V m a n e u v e r s , t h e G & N sys t em p rov ides a t t i t ude con t ro l ,velocity change se ns ing , and total velocity change contr ol by generat ingt h r u s t t e r m in a t i o n c o m m a n d s . P r i o r to t h r u s ti n g , t h e IiMU i s a l igned so tha tthe s t ab l e p l a t fo rm X-ax i s i s pa ra l l e l t o t he t h ru s t vec to r . The XGC d e t e r -mine s t ime- to - ign i t i on and to t a l veloci ty change des i r ed , and pe r fo rm s modever i f ic a t ion rout ine s . At igni t ion t im e the AGC f lashes the D S K Y d i sp l ays t othe cr ew fo r in i t ia t ion of ignit ion (manua l DSKY en t ry i s r e q u i r e d ) .thrus t ing , the CDU appl ie s attitude e r r o r s i g n a l s t o the SCS.s igna l s a r e app l i ed t o t he RCS eng ines ; however , p i t ch and ya\v e r r o r s igna l sa r e app l i ed t o t he SPS engine g imba l s r a the r t han RC S engines .e n s u r e s a l ig n m en t of t he t h rus t vec to r t h rough the spacec ra f t cen t e r -o f -g r a v i ty a nd a b n g th e c o r r e c t t r a j e c t o r y . T he P I P A s o n t h e st a b l e p l at f o rmsen se the ve loc i ty changes and apply propor t ional output s ignals to the -4GC.The I G C computes and upda te s spacec ra f t ve loci ty , and counts down a prese tcounter xvith the P I P A s igna l s .t e rmina t ion s igna l i s gen e ra t ed and app l i ed t h rough the S C S e l e c t r o n i c s tothe SPS engine .

DuringR ol l e r r o r

Th i s

IVhen the counter reaches zero , a thrus t

2 . 2 . 2 . 1 . o E n t r y .The en t ry mode p rov ides fo r gene ra t ion of a t t i t ude e r ro r and s t ee r ing

The s te er in g s ign als pro\ - ide for cont ro l ofs ign als , sens in g of dece lera t ion , and computa t ion of ve loc ity changes dur ingthe ent r>-phase o f the mi s s io n .the spac ecr af t l i f t \ -ec tor through the SCS, to inhibit excessi lre G-loadingsand hea t bui ldup, and to con tro l the f l ight path to enable landing a t a p r e -s e l e c t e d s i t e . -4t ti tude e r r o r s igna l s a r e appli ed to the FD-AI a t ti tu d e e r r o rneed le s .

En t ry conf igu ra t ion i s s im i l a r to at t i tude c ont ro l lv ith the except ionstha t t he ro l l r e sp onse t ime i s r ed uced , one s tep of ax i s r e so lu t ion i s notneeded, and the XG C wi l l p roduce s t ee r in g s igna l s to the S C S by d riving therol l CDU. F r o m in i t ia t ion of ent ry mode unt i l 0. 05G swi tching, ro l l , p i tch ,

GUIDANCE AKD N A V I G A T I O N SYSTEMMiss on Bas i c Da te l 2 19b6 Change Date p a g e 2 .2 -10


93/1007

SiM2A -0 3-SCO 12APOLLO OPERATIONS HANDBOOK

SYSTEMS DAT-I

and yaw er r o r s igna l s provide a t t i tude cont ro l . Upon 0 . OJG swi tch ing , thepi t ch and yan- e r ro r s ign a l s provide d i sp lay only. Pr io r to en t ry , the IMUX- a x i s i s a l i gne d a l ong t he s p a c e c r a f t e n t r y ve loc it y ve c t o r . Th i s a l i gnme n te l im ina t es the need for naviga t ion base- to - spa cecra f t body ax i s reso lu t ion .De c e l e r a t i on i s sensed pr ima r i ly by the IMU X-axi s PIP-A, al though changesi n l i ft ve c t o r o r i e n t a t i on c a us e s ome l a t e r a l m ove me n t wh ic h i s s e ns e d bythe Y a n d / o r 2 PI PXs . The ou t e r g i mba l , o r r o l l , 1X r e s o l ve r i s c onne ct e dto the 16X reso lver in the RO LL CDU, gi l- ing a 16 : l i ncr eas e in a t t i tudee r r o r s igna l and reduc ing the respon se t ime of the ro l l channe l.\vi11 produce steering signals by execut ing a prog ram me d l if t vec tor downe n t r y ( t o e n s u r e c a p t u r e ) , 180-deg ree ro l l to l i f t \vector up , then gener a tefur th er s t eer ing s igna l s \vi th respe c t to G f o r c e s , hea t bui ldup, and rangeneeded .CDU r e s o l \ - e r e r r o r i s gen erat ed and routed to the SCS for FD-41 disp1a)-an d/ or RCS engine cont ro l . The en t ry may be per form ed manual ly \vi th thepilo t f l \- ing to the s t ee r ing s igna l s a s d i sp layed on the FD-AI, o rau tom at ic a l ly\ \ -i th the -AGC steer i ng s ig nals ro uted to the ro l l RCS engines fo r spac ecra f tcon tr 01.

The -IGC

These s t ee r ing s ig na l s a r e routed to the ro l l CDU lvhere an IMU-

2 . 2 . 3 iM-AJOR COM POiV EST/ SUBSYST EhI DESC RIPTIO N2 . 2 . 3 . 1 Iner t i a l Subsys t em.

The funct ion of the ine r t i a l sub sys t em i s t o provide a s pa c e - s t a b i l i z e dIt i s c ompos e d of t he i ne r t i a l me a s u r e me n t un i t ( I M U) , t he na v i ga -

iner t i a l r e fe r ence f ro m which \ .- eloc i ty changes and a t t i tude changes c an bes e n s e d .t i o n b a s e ( S B ) , pa r t s of the pon.er and ser vo ass em bl y (PS-A), pa r t s of thecont ro l and di sp lay pane l s , and three coupl ing d i sp lay uni t s (CDUs) .

2 . 2 . 3. 1 . 1 Sa\ - iga t ion Base .The navigat ion base ( N B ) i s t he r i g i d , s uppo rt i ng s t r uc t u r e nh i c h

mounts the IMU and opt ica l ins t ru men ts .i n s t a l l e d t o cl o s e t o l e r a nc e s to provide ac cur a te a l ignment of the equipmentmounted on i t .

The S B i s ma nuf a c t u r e d a ndIt a l so prov ides shock mount ing for the IMU and opt ic s .

2 . 2 . 3 . 1 . 2 Iner t i a l Measurement Uni t .The i ne r t i a l m e a s u r e me n t un i t ( I MU) i s t he ma i n un i t of t he i ne r t i a l

s u b s y s t e m .conta in ing t hree iner t i a l r e fe ren ce in t egra t ing g) -ros ( IRIGs) , th r ee pul sedi n t e g ra t i ng pe ndu lous a c c e l e r om e t e r s ( P I P - I s ) , a nd t h r e e a ngu l a r d i f f e r e n t i -a t i ng a c c e l e r om e t e r s ( -I DAS). The s t a b l e me mb e r i t s e l f i s machined f roma sol id block of bery l l i um xvith holes bo red f or mount ing the PI PX s, IRIGs,and one of the thre e .ADXs. Thre e g imba l and s ix in te rg i mbal assem bl i es ,\ vh ic h hous e t o r que m o t o r s a nd r e s o l ve r s , a r e a l s o pa r t of t he I M Ua s s e m bl y ,toge ther \ I- ith prea mpl i f i e r s and g imbal -mounted e le c t ro nics .sho\vs h o w - the IRIGs and the PIPA s a re mounted re la t i ve to each o ther ont he s t a b l e me m be r ( o r i nne r g i mba l ) .

It i s a three-de gree-of - f re edom s tab i l i zed p la t form assembl ) . ,

F i g u r e 2 . 1- 2The three g imbal axe s . about lvh ich- eac h of the gimba ls rot ate , a r e als o shoxvn.

GL'ID-ASCE .IND SXV IGXT ION SYST EM2 . 2 - 1 1M i s s i on Ba s i c Dat e l 2 N O V 1966 Change Date Pa ge


94/1007

SMZA-03-SCO 12APO LLO OPERATIONS HANDBOOK

SYSTEMS DATAThe s table p la t form a t t i tude i s mainta ined by the IRIGs, ADAs, s tab i -l i za t i on loop e l ec t ron i c s , and g imba l t o rque moto r s . Any d i sp l acemen t ofthe s t ab l e p l a t fo rm o r g im ba l ang le s i s sen se d by the IRICs and ADAs, whichg e n e ra t e e r r o r s i gn a ls . IR IG e r r o r s i g n a l s a r e r e so lved and ampl i f i ed a tthe IMU and appl ied to s tabi l iza t ion loop e lec t ron ics .s igna l s a r e sum med wi th the IRIG e r ro r s igna l s . The r e su l t an t s i gna l i scond i ti oned and app l i ed t o t he g imba l t o rque mo to r s , wh ich r e s to re t hed e s i r e d a t ti t ud e .

ADA-produced e r ro r

The s t ab l e p l a t fo rm p rov ides a space - r e f e r enced moun t fo r t h r eePIPAS, which se nse ve loc i ty changes . The PIP As ar e mounted or thogonallyto sense the ve loc i ty changes a long a l l t h r e e axes . Any t r ans l a t i ona l fo rceexpe r i enced by the spacec ra f t cause s an acce l e r a t i on o r dece l e r a t i on n7hichi s s ensed by one o r mor e P IPAs .propo r t ional to the magni tude and d i rec t ion of ve loc i ty change. Th i s s igna l ,in the form of a p ulse t ra in , i s appl ied to the AGC.s ignal to update the \ reloc ity inform at ion and a ls o gene ra te s ignal s to torqueeach PIPA du cosyn back to nul l .

Each P IPA gene ra t e s a n ou tput s igna lThe AGC will use the

T he t e m p e r a t u r e of the IRIGs and PIPAs i s mainta ined wi th in requi redlim its du ring both standb)- and opera t ing mo des of the IMU.pe ra tu re con t ro l sys t em con ta ins c i r cu i t s t o supply no rma l p ropor t i onalt emp era t u re con t ro l n5 th t he capab i l it y of backup o r emerge ncy con t ro l i ncas e of a propor t ional cont ro l mal funct ion . The propor t ional tem per a tu recon t ro l c i r cu i t i s t he p r i i na r) - mea ns of main tainin g the IRIG and PIP=\t em pera tu re and p rov ides t he mos t accu ra t e con t ro l .aL-a ilable when e i the r the propor t ional o r aut o-o verr ide mode i s se l ec t edwith the I M U TE MP MODE se l ec to r swi t ch .oiFerride mode i s to pro\ - ide autom at ic swi tching f ro m tha t mode toe m e r g e n q - c o n tr o l if t h e r e i s a mal func t ion in t he p ropo r t i ona l con t ro lc i r cu i t . If a mal func t ion occur s i n t he p ropor t iona l mode , the switching toeme rgen cy con t ro l mu s t be pe r fo rmed manua l ly . I n the' p ropor t i ona l mode ,t h e t e m p e r a t u r e i s con t ro l led by the p ropor t i ona l t empe ra tu re con t ro lbr idg e and i s 'mainta ined a t 135kO. 5 F . IVhile in the em erg enc l- mo de, i t i scont ro l led bb- the mer cu ry t he rm ost a t and i s held \\.ithin * 3 " F .

The IMU tem-

Thi s type of con tro lisThe purpose of the auto-

The backup t emp era tu re con t ro l and ind i ca to r c i r cu i t is intended foruse i n t he e \ - en t t he p ropor t i ona l con t ro l f a i l s .f o r t h is s y s t e m a r e t h r e e PIPA i ndi cat ing sens o r s ( connec t ed in s e r i e s ) ands ix IRIG sens ing e l em en t s ( connec t ed in s e r i e s ) in t\vo sepa r a t e b r idges .Th i s sys t em can ma in t a in t he t emp era tu re t o n .i th in *1 "F .ope ra t ion , an a l ar m indica t ion i s not a \ ra i lable to the as t ro naut b ecause ofmodi f i ca ti ons t o the t empe ra tu re a l a rm ampl i f i e r c i r cu i t .

The con t ro l s ens ing e l emen t s

In th is mode of

2 . 2 . 3. 1 . 3 Coupling and Display Units .Th ere a r e i i \ -e CDL's mou nted belo\v the IiMU con trol panel a t the lowerequipment ba l- .

r ema in ing C D U s function u.ith the OSS.d e s c r i b e d i n p a r a g r a p h 2 . 2 . 3 . 2 .iden tical and ma)- be interc hang ed. DisplaJ- dia ls on the fron t panel of eachpro\-ide a b-digit read out . Posi t ionin g of the ICDUs is acc om plis hed by the-4GC. Eac h ICDU conta ins a l / - l - speed, 1 /2- spe ed, 1-spe ed, and lo-s pee dres o l \ - e r , the func t ions o i which depend upon the ISS mode of o perat ion.angu la r movemen t s of t he r e so lv e r s a r e conve r t ed i n to d ig i t a l s i gna l s bl- ad ig i t a l encode r , p roc es se d by encode r e l ec t ron ic s , and route d to -1GCreg i s t e r s \ vhi ch ma in t a in cu r r en t ICDU ang le s fo r u se a s des i r ed .

Three CDUs funct ion a s part of the ISS, Xvhile the twoThe th ree i ne r t i a l CDUs ( ICDUs) a r eThe opt ic CDUs (OCDUs) a r e

The

The XGC~ ~ ~ ~~ ~~~~

GUIDXKCE AND N--IVIGATIOS SYSTEMp a g e 2 . 2 - 12Miss ion Bas i c Da te l 2 1966 Change Date


95/1007

SMZA-03-SCO 1 2AP OL L O OPERA TIONS HANDBOOK

SYSTEMS DATAcomman ds CDU movem en t s by app ly ing d ig i t a l d r ive co mmands to d ig i t a l -t o - ana log conve r t e r s . The d r ive s ign a l s a r e conve r t ed f ro m d ig i t a l t o ana logand applTed to CDU moto r dr i ve am pl i f ie rs which pos i t ion the C bU s. -1 - speed and 1 6 - speed r e so lv e r s func t ion a s rec e i \ - ers of s ignals prod uced b\ -1 - speed and 16 - speed r e so lv e r s moun ted on the IMU.r e s o l v e r s a r e u s e d t o z e r o t h e C DU s a n d t h e 1 1 4 - sp e e d r e s o l v e r s a r e n otu s e d .mot o r d r ive s igna l s o r space c ra f t a t ti t ude e r r o r s igna l s , depending upon ISSmode of ope ra t ion . The IMU ou te r g imba l 1 - spee d r e so lve r s igna l s a r eapp l i ed t o the ro l l CDU 16- sp eed r e so lv e r t o i nc re ase r o l l con t ro l r a t e sdur ing en t ry .

TheThe 1 /2-s pee d

The r e s o lve r s p rovide i npu t s igna l s t o s e l ec to r c i r cu i t s \ vhi ch p rovide

2 . 2 . 3 . 1 . 4 Po \ve r and Se rv o Assembly - .

2 . 2 . 3.2

The po \ver and se rv o a s sembly (PSA) , l oca t ed ju s t belo\v the d i sp l ayand con t ro l pane l i n the l o lve r equ ipmen t bay , s e rv es a s a cen t r a l moun t ingpoint for m os t of the G&N ele c t ro nic uni t s su ch a s power suppl ies anda m p l i f i e r s .pulse s to the IMU in ca se of a n AGC t iming malfunct ion .r emovab le t r ay s moun ted ad j acen t t o each o the r and connec t ed to a junctionbox.connection: one for module- to-mo dule connect ion , anot her for module - to-junct ion box connect ion , and a th i rd for module connection to a 38-pinfem ale te s t p lug on the f ro nt of the PSA t r a y .

It a l so con ta ins t he backup e l ec t ron ic s u sed to supp ly timingIt c o n s i s t s of 10

The PS X t r ay s u t i l ize t h r ee wi r ing ha rn es s es t o p rov ide e l ec t r i ca l

Op t i ca l Subsys t em.The op t ica l subsys t e m is used fo r t ak ing p rec i se op t i ca l s i gh tings once l e s t i a l bod ie s and fo r t ak ing f i xes on l andm arks .f o r aligning th e IMU and fo r de ter min ing the posi t ion of t he spacec ra f t .sys t em inc ludes t he nav iga tiona l ba se , two of the f ive CDU s, p ar ts of thepower and se r vo a s sem bly , con t ro l s and d i sp l ays , and the op t i c s , I vhi chinclude the scanning te lesco pe (SCT) and the sext ant (SXT) .

Opt i c s .

These s igh t ings a r e u sedThe

2 . 2 . 3. 2 . 1The op tics con sis t of the SC T and the SXT mounted in txvo prot rudi ngtubu la r s ec t ions of t he op t i ca l base a s sem bly .a r e a l i gned pa ra l l e l t o each o the r and a f fo rd a comm on l i ne -o f- s igh t ( L OS )t o s e l e c t e d t a r g e t s .be of fse t depending upon mode of oper a t ion .

The SCT and SXT sha f t axesThe t runn ion axes may be pa ra l l e l o r t he SCT ax i s may

The sex t an t i s a h igh ly accu ra t e op t i ca l i n s t ru men t capab le of m ea su r -Angular sigh ting s of tn.0 ta rg et sng the inc luded angle be tween two tar get s .a r e m a d e t h ro u gh a f i xed bea m sp l i t t e r and a m o v a b le m i r r o r l o c at e d i n t h esex tan t head .28X magnificat ion.5 7 d e g r e e s LOS f r o m th e s h a f t a x i s .t r unn ion ax i s i s tw ice t ha t of the LOS r e q u i r e m e n t d ue t o m i r r o r r e f l e c ti o n\vh ich doub le s any angu la r d i sp l acemen t i n t runn ion ax i s .

The sex tant lens prov ides 1 . 8-d egr ee t r ue f ie ld of v ie \ r \r i thT h e m o v ab l e m i r r o r i s c ap a bl e of s ight ing a ta rg e t toThe mec hanic a l accura c l - of the

The scanning te lescope i s s i m i l a r t o a theodoli te i n i t s abi l i ty toaccu r a t e ly me asu re e l eva t ion and az imuth ang le s of a s ing l e t a rge t u s ing a ne s t a b l is h e d r e f e r e n c e .1X magnif ic a t ion . The te les cope a llon .able LOS e r r o r s a r e 1 minute of a r cr m s i n e l e v a t io n w it h m a x i m u m r e p e at a b il i ty of 1 3 a r c i s e c o n d s a n dapprox ima te ly 40 a r c l s e c o n d s i n s h a f t a x i s .

The lens es provide 60-d egre e tr ue f ield of \ -le\\-a t

GUIDANCE AND NAVIGATION SYSTEM2. 2-13Mis sion Bas ic Date 12 Nov 1 9 6 6 Change Date Page


96/1007

SMZA -0 3-SCO 12APOLLO OPERATIONS HANDBOOK

SYSTEMS DATA2 . 2 . 3 . 2 . 2 Coupling Display Units.

The funct ion of he OCDUs i s to pos i t ion and r epea t ang l es of the SC T andSXT shaf t and t runn ion axes . The OCDUs a r e s im i la r to the ICDUs, bu t mayno t be in te r changed due to in te rna l mechan i ca l d i f fe rence s a l lowing h igherOCDU r a t e s . Eac h OCDU has a 6-d ig i t d i sp lay re adou t and can be pos i t ionedau tom at ica l ly by AGC comm and .s igna l by a d i g i ta l e n c o d e r , p r o c e s s e d b y e n c o d e r e l e c t r o n i c s , a n d r o ut e d toa n AG C r e g i s t e r .a n a l o g c o n v e r t e r , c o n v e r t e d t o a rep r esen ta t iv e ana log s igna l , and app l iedt o a mo t o r d r i v e a m p l i f i e r i n t h e S XT . R e s o l v e r s i n t he S XT f un ct io n a st r an sm i t t e r s to CDU reso l ve r s which rece ive the pos i tion s igna l s and applyt h e c o mma n d e d a n g l e s t o t h e C DU mo t o r d r i v e a mp l i f i e r s t o po'sition theCDU motor .

CDU a n g l e s a r e c o n v e r t e d t o a d ig i t a lAGC pos it ioning com mand s a re app l ied to a d ig i t a l - to -

Trunn ion CDU 1 / - l- speed and 16 -speed r eso lve rs func t ion a s r ece ix re r sand p rov ide d r ive s igna l s to the t runn ion CDU mo tor .r e s o l v e r s wh ic h d r i v e t h e CDU r e s o l v e r s a r e 1 - s p e e d a n d 6 4 - s p e ed r e s p e c -t ively , probiding a 1 :4 SXT t runn ion to CDU t runn lon ra t io . Visua l r eadou tso n t h e t r u n n i o n d i s p la y d i a l s a r e t h u s f o u r t i me s t h e t r u n n io n a n g le a n d tn.0t i m e s t h e s tar l ine -o f - s igh t an g le f ro m ze ro posi t ion .r e s o l v e r , i n c o nj un c ti on wit h t he c o s e c a n t a mp l i f i e r , p r o v i de s a v a r i a b l ega in comput ing re so l ve r which i s use d in the RESOLVED mode of oper at lon.T h e 1 - s p e e d r e s o l v e r i s n ot u s e d i n th e t r u n n io n CDU.

The SXT t runn ion

The 1 /2 - speed

Shaf t CDU 1 / 2 -s pee d and 16-speed re so l ve r s func tion a s r e c e i v e r s a ndproduce d r i ve s igna l s to the sha f t CDU mot or .t r a n s m i t t e r s a r e a l s o 1 / 2 - s p e e d a n d 1 6 -s p e e d r e s o l v e r s , a ff or di ng a 1 : lra t io ; thus , the d i sp lay d ia l s p rov ide d i r ec t r ead ou ts of the sha f t ang les .T h e 1 - s p e e d r e s o l v e r r e s o l v e s p o l a r c o o r d i n a t e s i nt o r e c t a n g u l a r c o o r -d ina tes fo r tne PESOLVED mo de of ope ra t ion .no t used in the shaf t CDU.

SXT reso l \ve r s used a s

T h e l i - l - s p e e d r e s o l v e r i s

2 . 2 . 3. 2 . 3 Op e r a t i o n a l Mo d e s .Opt ics pos it ion ing i s acco mpl i sh ed au tomat ica l l ) - by the XGC orma n u a l l y by t h e c r e w.t ion of the ZER O OPTICS, MANUAL, o r COM PUTER mode s on the O P T I C Spane l .

Ov e r a l l mo d e c o n t r o l i s e s t a b l l s h e d by c r e n . s e l e c -

ZERO OPTICS mode enab le s au tom at ic d r ive of the SXT shaf t andt r u n n io n mo t o r s t o z e r o . T h i s i s a c c o m p l i s h ed by applying the SXT resol \ . -erou tpu t s igna l s to the input of the SXT motor d r ive am pl i f i e r s .s i g n a l s a r e appl ied t o the CDU and SCT res ol ve rs which fol lon. the SXT shaf ta n d t r u n ni o n a x e s t o z e r o .r e g i s t e r s a r e c l e ar e d .m a nu a 11>-.

The d r iveAf t e r 60 seconds, the AGC opt ics posi t ionThis mo d e ma y b e s e l e c t e d by AGC p r o g r a m o r

MANUAL mo de enabl es posi t ioning cont rol of the opt ic s by ma n u a lmanipu la t ion of the op t ic s hand con t ro l l e r . The hand control ler is m e c h -a n i z e d s u ch t h a t , r i g h t- l e f t mo v e me n t g e n e r a t e s s h a f t c o mm a n d s , a ndup-down movem ent gen era tes trunn ion comm ands . Hand con t ro l l e r d r i \, er a t e s a r e s e l e c t e d by t h e p o s it i o n of the CONTROLLER SPE ED sn . i tch .

GUIDANCE AN D NAVIGATION SYSTEM2 . 2 - 1 4Miss io n Bas ic Da te l 2 1966 Change Date Pa ge


97/1007

SiM2A-0 3 - S C O 12APOLLO OPERATIONS HANDBOOK

SYSTEMS DATA..Pos i t i ons HI, hlED, and LO cont ro l the ampl i tude of the dr ive s igna l to thehand cont ro l l e r . Hand c on t r o l l e r d r i ve s i gna l s a r e a pp l ie d t o the SXTshaf t and t runnion dr ive amp l i f i e r s th rough the CONTROLLER MODE swi t chfo r se lec t ion of DIRECT or RESOLVED mode . In DIRECT mode , the imagemot i on i s p r e s e n t e d i n a po l a r c oo r d i na t e r e f e r e nc e f r a m e : i n RESOLVEDmode , t he i ma ge mo t i on i s presente d in a rec tangu lar coord ina te re fe renc ef r a m e .

In DIRECT mode , shaf t commands move the image in a c i rc u l a r pa tharound the center of the f ie ld of view.in a s t ra igh t l ine ac ro ss the cent e r of the f i e ld of view. The angularor ien ta t ion of the t runnion commanded s t ra i ght l ine movem ent i s a func tionof the shaf t angle ; ther e fore , d i rec t i on of image c io i rem ent wi th re sp ec tto the d i rec t ion of hand con t ro l l e r movem ent i s a l s o a funct ion of shaf tangle . The ra te of image movem ent , fo r shaft com man ds , i s a func t ionof t runnion angle , where in increas ing t runnion angles resu l t in incr eas i ngi ma ge move me nt r a t e s .

T r unn i on c omma nds d r i ve t he i ma ge

In RESOLVED mode , shaf t commands move the image l e f t - r igh t inI ma ge move me n t i s i n t he s a m e d i r e c t i on a s ha nd c on t r o l l e r move -

a s t ra ight l ine .l ine .ment and the ra te of movem ent i s c ons t an t f o r va r y i ng a ng l e s .

Trunnion comman ds move the image up-down in a s t ra igh t

In COMPUTER mod e , the XGC pos i t ions the opt i cs to a s t a r o r l and-ma r k de t e r mi ne d by AGC p r og r a mmi ng . Th i s mode i s per fo rmed by anXGC rout ine which i s ca l l ed up au tomat ica l ly by var ious a l ignment pro-g r a m s .o r by t he c r e w. If the t a r ge t s t a r o r l a ndma r k i s not s el ec te d by .AGCprog ramm ing , the c rew m akes a DSKY ent ry def in ing e i ther the l a t i tude ,longi tude, and al t i tude for a l a ndma r k o r t he s t a r code f o r a s t a r . TheAGC de te rmines the spacecraf t a t t i tude by moni tor ing the ICDUs, andc ompu t e s t he a ng l e s ne c e s s a r y t o d r i ve t he op t i c s t o the de s i r e d t a r ge t .(I f t he a ng l e s ne c e s s a r y t o a c qu i r e t he t a r ge t a r e beyond t he c a pa b i l i t i esof the opt ics , t he AGC f l ash es the DSKY di sp lays . ) When the neces sar ya ng l e s a r e c ompu t e d , t he AGC d i s p l a ys t he de s i r e d s ha f t a nd tr unn i onangl es on the DSKY and ini t i a tes OCDU dri ve to thes e angl es . When theAGC has comple ted dr iv ing the CDUs, the c re w checks the DSKY-disp layedangles aga ins t the 6-d ig i t CDU disp lay s and the SCT counte r s . The creLvt he n l oc a t e s a nd i de n t i f ie s t he t a r ge t i n t he SCT, e na b l e s ma nua l c on t r o l ,and comple tes the s igh t ing,func t ions , i f de s i r e d , by t he AGC p r og r a m .

The t a r ge t s t a r o r l a ndma r k m a y be de fi ne d by AGC p r og r a m mi ng

The AGC c a n a l s o pe r f o r m z e r o op t i c s

The SC T t runnion may be opera ted in th re e a l t e rna te mo des , wi thr e s p e c t to the SXT trunn ion, The SL-qVE TELE SCO PE swlt chenables c rew se lec t ion of ST-AR LOS, L.4KDM-lRK LO S O " , o r O F F S E T25" . The ST-lR LOS posi t ion i s norma l ly used In th i s pos i t ion , the SCTt runnion i s slaved to the SXT trunnion. The LANDMARK LOS 0" posi t ion,appl i es a f ixed vol tage t o the SCT trunnion posi t ion loop causi ng i t to nul la t z e r o .

a s d e s i r ed .

Th i s ho l ds c e n t e r o i the SCT 6 0 " f l e ld of view pa ra l l e l to the

GU ID-AN E -lND N XVIG =\TION SY T E X I .p a g e 2 . 2 - 1 5M i s s i on Ba s i c Dat e l 2 l 966 Change Da t e


98/1007

SMZA -03-SCO12A P O L L O OPERATIONS HANDBOOK

SYSTEMS DATA

2 . 2 . 3. 3

SXT landm ark l ine of s ight .vol tage t o the SCT t runnion pos i t ion loop, caus ing i t to null a t 25 de gre esoff -center . Thi s holds th e SCT field of view s o t ha t t he SXT l andm ark l i neof s ight r em ain s v is ib le whi le sweeping the SCT sha f t t h rough 360 deg ree sof rotat ion, p rov iding a n approx ima te 110-degree total fie ld of view ,

T h e O F F S E T 2 5 " posi t ion appl ies a f ixed

C o m p u t e r S u b s y s t e m .The com pute r su bsys t em (CSS) cons i s t s of the Apollo guidance com-

pu te r ( AGC ) and two display and keyboard panels (DSK Ys) .one DSKY ar e loca te d a t the lowe r equipment bay.loca ted on the main d isplay console . The AGC mounts one sw i tch on thef ro nt panel which appl ies pa r t ia l or fu l l power to the comp uter to enables tandbv o r fu ll opera t io n of the CSS. Al l o th er XGC con t ro ls and d ispl aysa r e l oca t ed on the DSKYs .howe ver , the d isplay s on the DSKY in the lower equipment bay ar e mo reex tens ive ,

The AGC andThe other DSKY i s

The keyboa rds on the DSKYs a re smi l i a r ;

2 . 2 . 3 . 3 . 1 Xpollo Guidance C omp uter .The .Apollo guidance computer (-AGC) i s a d ig i ta l computer us ing a

Input da ta i st w o - p a r t r op e c o r e m e m o r y .va r ious da t a t o p rov ide c on t ro l and computa t ion func t ions .r e c e i v e d f r o m t h e c r e w , ISS, OSS, iMSFN, and o the r spacec ra f t sys t ems .T h i s d a t a i s p r o c e s s e d by v a r i o u s p r o g r a m s to provide outputs to thec r e w , ISS, OSS, MS F N, and o the r spacec ra f t sy s t e ms in t he fo rm ofcommands and d i sp l ays .co ns ist of th e fol lowing:

(See f igu re 2 . 2 - 3 . ) The AGC p r o c e s s e s

The co nt ro l funct ions per for me d by the AGC

0 Align the I h I U s t ab l e p l a t fo rm.e Posi t ion the opt ics for navigat ion s ight ings .0 Command r eac t ion con t ro l sys t em eng ine f i r i ngs t o ma in t a in

speci f ic a t t i tude .0 Reques t i n i ti a t ion and comm and t e rmina t ion of s e r v i c e

p ropu l s ion engine f i r i ng s .0 Prov id e synchron iza tion pu l se s t o t he cen t r a l t iming equ ipmen t .0 C o m m a n d t e l e m e t r y t r a n s m i s s i o n to AlSFN.0 Command ISS moding.0 Command OSS moding.

The r e f e r e nce da t a u sed to gene ra t e con t ro l s may be acqu i r ed ex t e rna l lyo rgenera ted wi th in the ; IGC.t he c r ew us ing the DSKYs, by MSFK v ia t e l eme t r ) , or by an AGC p r o g r a m .

Ini t ia t ion of the cont r o ls may be acco mpl is hed by

~ ~ ~

GUIDANCE .AND NAVIGATION SYSTELLIPage 2 . 2-16Miss ion Bas i c Da te 1 2 N0.J 1966 Change Date


99/1007

SM2A - 0 3 - S C O 12APOLLO OPERATIONS HANDBOOK

DA T A INI N P U TDSKYS (CREW)I S S M O D E SOSS A N G L E SMESC (EVENTS)

SYSTEMS DATA

CE NT RA LPROCESSOR

M E Y O R YI I

FIXEDE R A S E - IABLE I A

PARITY FAILv

SCS MODESTELEMETRY

I N H I B I T / E N A B L E D O W N L I N K-S-IVB I N S T U N I T - I II ITIMING (REAL TIME) TO A 1

TO A L L S E CT I O NS

I =,SKY SI LISSODESa CONTROLOSS M O D E S 8 CONTROL- OUTPUT SPS E N G I N EI F P S A EFERENCE

S E CT I O NS

SM-2A-827

F i g u r e 2 . 2 - 3 . AGC Funct ional Block Dia gramComputa t ions a r e pe r fo rme d to gene ra t e t he p rop e r con t ro l comma nds ,ma in t a in navigat ion pa r am e te r s , and comple t e va r ious o the r ope ra t i onsu n

Date post:	09-Apr-2018
Category:	Documents
Upload:	bob-andrepont
View:	226 times
Download:	2 times

Apollo Operations Handbook CSM Spacecraft 012

Documents