Ap Operations Handbook CSM SC 012 1966.pdf

7/23/2019 Ap Operations Handbook CSM SC 012 1966.pdf

1/849

SID 65-1317

APOLLO

OPERATIONS

HANDBOOK

COMMAND AND

SERVICE

MODULE.

SPACECRAFT 012

Prepared Under Direction

of

FLIGHT CREW SUPPORT DIVISION

NASA-MSC MISSION OPERATIONS BRANCH

/-

N O R T H

SPACE and

A M E R I C A N

INFORMATION

A V I A T I O N , INC.

SYSTEMS DIVISION

I


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NOTE: The portion of

the t ex t

alfrcted

by

the current chanRcs

i s

indicated

by a

\enical l ine

an

the

outer

marlins of the

page.

LIST OF

EFFECTIVE

PAGES

TOTAL

NULIBER

O F PAGES I N THIS PUBLICAT ION IS

816,

CONSISTING OF THE

FOLLOWING:

P a g e P a g e

Ti t le

A thru E

i th ru x i i

1 - 1 t h r u 1-20

2-1 t h r u

2 - 2

2.1-

2.2-

2 . 3 -

2.4-

2.5-

2. 6-

2.7-

t h r u 2 . 1-10

t h r u

2. 2-48

t h ru 2 . 3-72

t h r u 2.4-38

t h r u

2 .

5-44

t h r u 2. 6-48

t h r u 2. 7-48

2.8- t h r u 2.8-70

L. 9- 1 t h r u 2.9- 38

2 . 10-1t h r u 2. 10-10

2 .

1 1 - 1

t h r u 2. 1 1 - 6

3 - 1 t h r u

3-212

4 - 1 t h r u 4-50

5-1

t h r u

5-20

6-1t h ru 6-52

7-1

t h ru 7-2

8-1t h r u 8 - 2

A-

1

t h r u

A - 6

CHANGE INFORMATION

This handbook is sub jec t to con t inuous change or rev i s ion , on a p r i o r i t y

b a s i s , t o r e f l e c t c u r r e n t en g in e er in g o r m is s io n c h a n g e s , o r to imp ro v e c on ten t

o r a r r a n g e m e nt .

Lis t of Effec t ive P age s , and by the fo llowing me an s :

The con ten t and the changes a r e accounted fo r by the above

Reco rd of Publ ica t ion :

i s s u e is l is ted on page B as a record of all ed i t ions .

The publication date of each bas ic i s sue and each change

Page Change Date :

da te .

Each page in th is handbook has spa ce fo r en t e r ing

a

change

The la tes t pub l ica t ion da te wi l l be en t e red in th is sp ace each t im e a page

is c ha n ge d f r o m th e b a s ic i s s u e .

*The

asterisk

indicates

pager

changed. added.

o r

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 a s d i r e c t ed

by

t h e N A S A A p o ll o P r o g r a m O ff i ce . A l l r e q u e s t s f o r

m a n u a l s s h o u l d

be

d i r e c t e d to t h e N A S A A p o l l o S p a c ec r a H P r o g r a m O f f i c e a t H o u s t o n , T ex as .

A


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A P O L L O OPERATIONS

HANDBOOK

LATE TECHNICAL CHANGES

The i te m s l i s ted below rep res en t te chn ica l changes which have been approved too

lat e for inc lusio n in the 12 Novembe r 1966 prin ting of the Apollo Opera tio ns Handbook.

Source

M CR

A1735

MCR

1591

RE V 3 .

F E O

M-53025

( 10 - 13 -66)

MCR

A1733

( 1 0 - 1 1 -6 6 )

Descr i p t ion of Change

Change

S / M

RCS fu e l f r o m b len d ed h y d ra z in e

mix tu re to mo n o me th y lh y d ra z ine

Addi t ion of inv er t e r sync hro n ize r power pane l

wh ic h p ro v id e s c i r c u i t b re a k e r s fo r th e c o n t ro l

of power to the phase sync hron ize r un i t.

T h i s is a n o m e n c l at u r e c o r r e c t i o n f o r t h e

S-Ba nd switch on the MDC pane l s

No.

13 ,

2 3

and 26.

changes .

" P T T " , " O F F " a n d "VOX". T h e s wi tc h is

n ow ma r k e d

"OFF",

"OFF" a n d "T /R" .

T h i s c h a n g e i s r e q u i r e d due t o w i r in g

T h e S -Ba nd s wi tc h wa s ma rk e d

Modification of Cr ew Couch Lockouts . Th is

MCR re mov es the lockout so leno id ac tu a tor

a 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 t

lockout mechanism.

loc ko ut me c h a n i s m a s s e mb ly to f ix in th e

locked posit ion. T h e switc h on pane l No. 9

a 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 th e s t r u t s

wi l l b e r e m o v e d .

Add

a n

a d a p te r t o t h e

Section Affected

2 . 5

2 , 3

2 . 8 a n d 3

Miss i on Bas ic Da te 12 No v 1966 Change Date Pa ge D


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APOLLO OPERATIONS HANDBOOK

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

S e c t io n T i t l e

1 GENERAL INFORMATIO N.

1 . 1

1 . 1 . 1

1 . 1 . 2

1 . 1 . 2 . 1

1 . 1 . 2 . 2

1 . 1 . 2 . 3

1 . 1 . 2 . 4

1 . 1 . 2 . 5

1 . 1 .

2 . 6

1 . 1 . 2 . 7

1. 1. 2.

8

1 . 1 . 2 . 9

1 . 1 . 3

1 . 1 . 4

1 . 1 . 5

1 . 2

1 . 2 . 1

1 . 2 . 2

1 . 3

1 . 4

Spacecr a f t 012 Configura t ion .

LES

A s s e m b l y .

Command Module

F 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 Co n t ro l s a nd D is p la y s

C / M M e c ha n ic a l C o n t r o l s

Cre w E q u ip me n t an d E q u ip me n t Ba y s

Food and Wate r

.

Wa s te Ma n a g e me n t .

Su

v v a1 Eq uipm ent

.

Aft Co mp a r tme n t

Ser v ice Module

.

S p a c ec r a f t L E M A d a p t e r .

S p a c e cr a f t S y s t e m s

.

Launch Vehic le Configura t ion .

S -1 B Bo o s te r

S-IVB Second Stage .

Mission 209A Weight Status .

Pos t land ing and Recover y

.

2 SYSTEMSDATA .

2 .1

2 . 1 . 1

2 . 1 . 2

2 . 1 . 3

2 . 1 . 4

2 . 2

2 . 2 . 1

2 . 2 . 2

2 . 2 . 2 . 1

2 . 2 . 3

2 . 2 .3 . 1

2 . 2 . 3 . 2

2 . 2 . 3 . 3

2 . 2 . 4

2.2. 5

2 .2 . 5 .1

2 . 2 . 5 . 2

Guidance and Contro l

.

S y s t e ms In te r fa c e , Gu id a nc e a nd Co n t ro l

Co a s t in g F l ig h t .

P o we re d F l ig h t .

Atmo s p h e r ic F l ig h t .

Guidance and Naviga t ion Sy s te ms ( G & N )

In t roduc t ion .

F u n c t io n al De s c r ip t io n .

Op e ra t io n a l Mo d e s .

Ma jo r Co mp o n e n t /S u b s y s te m De s c r ip t io n

In e r t i a l S u b s y s te m .

Op t ic a l S u b s y s te m ,

Co mp u te r S u bs y s t e m

P e r fo rma n c e a n d De s ig n Da ta

Op e ra t io n a l L imi ta t io n s a nd R e s t r i c t io n s

S I C Att i tude

IMU Op e ra t io n .

P a g e

1 - 1

1 - 1

1 - 1

1 - 4

1 -6

1 - 6

1 - 6

1 - 6

1 -1 2

1 - 1 5

1-15

1 - 1 5

1 -1 5

1-16

1-16

1-16

1 -1 6

1-19

1-19

1-19

1-19

2- 1

2 . 1 - 1

2 . 1 - 1

2 . 1 - 1

2 . 1 - 2

2 . 1 - 2

2 . 2 - 1

2 . 2 - 1

2 .2 -1

2 .2 -7

2 .2 -1 1

2 . 2 - 1 1

2 .2 -1 3

2 .2-16

2 .2 -4 0

2 .2-40

2 .2 -4 0

2 . 2 - 4 1

. . .

Mis s io n Ba s ic Da te l 2 1 9 6 6 Ch a n g e Da te P a g e 111


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Sec t ion T i t l e

P a g e

2 .4 .3 . 1 Des ign Da ta

2 . 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 tr i b ut i o 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 s

2 . 5 Reac t i on Con t ro l Sys t em (RCS)

.

2 .5 .1 In t roduc t i on

2 . 5 . 2 S / M RCS Func t i ona 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 .1

2 . 5 . 3 . 2 P r o pe l la n t S u b s y s te m

2 . 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 . 4

2 . 5 .4 . 1 Des ign Da ta

2 . 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 . 4

2 . 5 . 5 . S/ M RCS Ope ra t i ona l L imi t a t i ons and Res t r i c t i ons

.

2. 5 .6

2 .5 .7 C / M RCS Func t i ona l Desc r ip t i on

.

2 . 5. 8 C / M RCS Ma jo r Componen t s /S ubsys t em Desc r ip t i on

.

2. 5. 8.

1

2 .5 .8 . 2 P rope l l an t Subsys t em

2 . 5 . 8 . 3 E n g in e A s s e m b l y

2 . 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 ta

2 . 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 tr i b ut i on

2 . 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 ion

2 .6 . 2 Func t i ona 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 i on

.

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 . 3

2 . 6 . 3 . 1 Cryo genic S tora ge

.

2 . 6 . 3 . 2 Ba t t e r i e s

.

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 s

sur

za t i on 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 on

S / M R CS 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 -30

2 . 4 - 3 3

2 .4 -33

2 .4 -35

2 . 4 - 3 5

2 . 4 - 3 5

2 . 5 - 1

2. 5-1

2. 5-1

2 . 5 - 4

2 .5 -7

2 . 5-8

2 .5 -9

2 .5 -13

2 .5 -15

2. 5-16

2 .5 -16

2. 5-18

2 .5 -18

2 .5 -19

2 .5 -19

2 .5 -19

2 .5 -23

2 . 5 - 2 4

2 . 5 - 2 7

2 . 5 -28

2 .5 -30

2 .5 -34

2.5-39

2 .5 -39

2 .5 -41

2 .5 -41

2 .5 -41

2 .5 -41

2 .5 -41

2.6- 1

2 .6 -1

2 .6-1

2 .6 -1

2 .6 -2

2 . 6-2

2 . 6 - 2

2 .6 -5

2 . 6 - 5

2 . 6 - 6

2 .6 -12

2 .6 -17

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-

0 3 - sc

0 1

2

APO LLO OPERA TIONS HANDBOOK

.

Section

-

T i 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 . 4

6 .4 . 1

6. 4. 1 . 1

6 .4 .

1.

2

6 . 4 .

1.

3

6 . 4 . 1 . 4

6 .4 . 1 .5

6 . 4 . 2

6 . 4 . 2 .

1

6 . 4 . 2 . 2

6 . 4 . 3

6 . 4 . 3 . 1

6 . 5

6 . 5 . 1

6 . 5 . 2

6. 6

6 . 6 .

1

6 .6 . 2

6 . 7

6 . 7 . 1

6. 7.

2

6 .7 .2 . 1

6 . 7 . 2 . 2

6 . 7 . 3

6.7.3. 1

6 . 7 . 3 . 2

6 . 7 . 3 . 3

6 . 7 . 3 . 4

6 . 7 . 3 . 5

6 . 7 . 4

6 .7 .4 . 1

6 . 7 . 4 . 2

6 .7 .4 . 3

6 .

7.4. 4

6 .7 .4 . 5

6 . 7 . 4 . 6

6 . 7.4. 7

6 . 8

6 . 8 . 1

6 .8 .

1.

1

6 . 8 . 1 . 2

6 . 8 . 1 . 3

6 . 8 . 1 . 4

6 .9

6 .9 . 1

6 .9 . 2

6 . 9 . 3

S p a c e Su it As s e mb l y (GF P ) .

S p a c e S ui t Off o r S h i r t s l e e v e E n v i ro n me n t

Co n s tan t We a r Ga rme n t .

F l ig h t Co v e ra l l s

Comm unica t ion s Soft Ha t

.

Co n s tan t We a r Ga r me n t E le c t r i c a l Ad a p ter

Elec t r ic a l Umbil ica l "S leep" A dapte r .

Space Suit On Envir onm ent

.

P GA Un p re s s u r i z e d o r Ve n ti l a te d .

P GA P r e s s u r i z e d

PGA Descr ip t ion

PGA Components

PGA Stowage

To rs o and Glove S towage .

Helm et S towage

.

PGA Connecting Equipment .

P r e s s u r e G a r m e n t A s s e m b l y ( P G A ) E l e c t r i c a l

A d a p t e r ( G F P )

.

Oxy ge n Ho s e (Umb i l i c a l ) (GF P )

.

C r e w C o u c he s .

C r e w C o u ch S t r u c t u r e

Cre w Co u ch P o s i t io n s

Occupied Pos i t ions

.

Unoccupied Po

sit

ons

Crew Couch Component Descr ip t ion .

H e a d r e s t .

B ack r e s t

A r m r e s t s .

S e a t P a n an d F o o t r e s t

C r e w C o uc h P a d s

Mechanica l Adjus tments .

He a d re s t Ad ju s tme n t s

A r m r e s t A d ju s tm e nt s

S e a t P a n Ad ju s tme n t D i re c t io n s

.

F o o t r e s t a n d F o o t s t r a p A d j u st m e n t s

.

D-Ring Handle Extension

Docking Pos i t ion A djus tment .

S h o u lde r S t ra p Ad ju s tme nt

.

C r e w m a n R e s t r a i n t s

High G-Lo a d Re s t r a in t s

.

C r e w m a n R e st r a in t H a r n e s s .

We ig h t l e s s Re s t ra in t

Guidance and Naviga t ion S tat ion Res t r a in t

Cre w ma n S le ep in g Re s t ra in t s

.

F l ig h t Data F i l e (GF P )

.

C o m m a n d e r ' s F l i g ht D a t a Fi le

S e n io r P i lo t ' s F l ig h t Da ta F i l e

P i lo t ' s F l ig h t Da ta

Fi le .

.

.

.

6-13

6-13

6 -1 3

6-14

6-15

6-15

6 -1 6

6 -1 7

6 - 1 7

6-18

6-18

6 -1 8

6-19

6 - 1 9

6-19

6-19

6-21

6-22

6-22

6-22

6 -2 3

6-23

6-23

6 -2 3

6 -2 4

6 - 2 5

6-26

6-27

6 -2 8

6-28

6-29

' l 2 1966 Change Date Pag e

X

M i s s on Bas i c Da te


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SM. -4 0

3

-

S C

0

2


S e c t io n T i t l e P a g e

6 . 1 5 . 4 Descr i p t ion and Use of Su rv iva l Ki t Components

.

6-47

6 . 15 .4 . 1 L i fe 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 . 1 5 .4 .

3

S u rv iv a l L ig h t s

( 2 ) .

6-48

6 . 1 5 . 4 . 4 S u rv iv a l G la 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 ts

( 2 )

P l u s T a b l e t s ( 1 6 ) . 6-49

6 . 1 5 . 4 . 8 E me rg e n c y Me d ic al S u rv iv a l K it

.

6-49

6 .

1 5 . 5 S e a W a t e r P u m p

( C F E )

. 6-49

6 . 1 6 Stowage 6-50

7 SYSTEM SCHEMATICS . 7 - 1

Miss ion Bas ic Da te 12 Nov 1966 Change Date Page xi i


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SMZA -03-SCO12


GENER AL INFORMATION

Q-BALL (NOSE CONE)

PITCH CONTROL MOTOR

JETTISON

MOTOR

LAUNCH ESCAPE

MOTOR

STRUCTURAL SKIRT

LA UNC H ESCAPE TOWER

TOWER ATTACHMENT (4)

C O W N O MODULE

C/M TO

S/M

FAIRING

SERVICE MODULE

EPS RADIATOR

ECS RADIATOR

SPACECRAFT LEM

ADAPTER (SLA)-

S f 5

ENGINE EXPANSION NOZZLE

S I A

PANEL JUNCTION

(BETWEEN FWD A N D A f l

PANELS)

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


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SM2A

-

0 3-SC 0 1 2

APO LLO OPERATIONS HANDBOOK

GENER AL INFORMATION

BREAKOUT PLUG

(FOR APEX COVER

r PILOT PARACHUTE)

LAUNCH ESCAPE TOWER

FORWARD HEAT SHIELD ATTACH MENT (TYPICAL)

(APW COVER)

NEGATIVE PITCH

OPTICAL S IGHTING ENGINES

PORTS

1

FWD VIEW1 N G

(RENDEZVOUS)

WINDOWS

CREW

POSITIVE PITCH

AFT HEAT SHIELD

\ I

\ I

^.. ..... .-^...

ID E W I N D O

(TYPICAL 2 PLACES)'

UMBI LI;AL'

u nATCnW""UW

ROLL ENGINES

(TYPICAL)

NOTE:

CENTER COU CH REMOVED FOR CLARITY.

Figure 1- 3.

S p a c e c ra f t

0

1 2 Command Module

SM-2A-642F

SPA CEC RA FT 012 CONFIGURATION

1-5

Miss io n Bas ic Da te

l 2

1966 Change Date Pa ge


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SMZA-03-SCO12

A P O L L O

OPERATIONS

HANDBOOK

GENERAL INFORMATION

1 .1 .2 . 1 F o rwa rd Co mp a r tme n t .

T he fo rwa rd c o mp a r tm e n t ( f ig u re 1 - 3 ) i s th e a r e a o u t s id e th e fo rwa rd

acc es s tunnel , fo r wa rd of the c r ew compa rtm ent fo rward bulkhead and i s

c o v e re d by t he f o rwa rd h e a t s h ie ld .

pe ri me te r of the tunnel contain the reco ver y equipment, two negative-pitch

re a c t io n c o n t ro l s y s te m e n g in e s , a n d th e fo rwa r d h e a t s h ie ld r e l e a s e

m e c h a n i s m .

of ea r t h landing ( reco ver y) sys tem components .

F o u r 9 0 - d e g re e s e g me n ts a ro u n d th e

Mos t of the equ ipment in the fo rwa rd com part men t cons is ts

T he fo rwa rd h e a t s h ie ld , o r a p e x c o v e r ,

i s ma d e

of

b r a z e d s t a i n l e s s -

s tee l honeycomb and covered wi th ab la tive ma te r ia l .

rec ess ed f i t t ings which perm it the launch escape tower to be a t tached to the

C / M i n n e r s t r u c t u r e .

C /M a f t e r e n t ry o r a f t e r th e l au n c h e s c a p e a s s e mb l y i s s e p a ra te d d u r in g

a n a b o r t .

s e c t io n 2.

)

It contains four

J e tt i s on th r u s t e r s s e p a ra te the a p e s c o v e r f ro m th e

(F o r a dd i t io n a l in fo rma t io n , r e fe r

to

the sequent ia l sys tem s in

1 . 1 . 2 . 2 C r e w C o m p a rt m e n t.

T h e c r e w c o m p a r t m e n t o r i n n e r s t r u c t u r e ( f i g u r e -1-3) i s a sea led

cab in wi th p res sur iza t io n main ta ined by the env ironmen ta l con tro l sys tem

(ECS) . The com part men t , p r o tec ted by a hea t shie ld , con ta ins con tro ls and

d i s p la y s fo r o p e ra t io n of th e s p a c e c ra f t a n d s p a c e c ra f t s y s t e ms ; c o nta ins

m e c h a ni c a l a d j u s t m e n t s f o r th e c r e w c o u c h e s, r e s t r a i n t h a r n e s s a s s e m -

bl ies , ha tch cove rs , window shade s , e tc .

;

and is p rov ided wi th c rew

equipment, food and wate r , was te management p rov is i ons , su rv iva l equ ip-

me n t , a nd s cie n ti f i c e x p e r ime n t s eq u ipme n t . Ac c e s s h a tc h e s , o b s e rv a t io n

windows , and equ ipment bays a r e at tached as pa r t of the comp artm ent s t ru c tur e .

T h e c re w c o mp a r tme n t h e a t s h ie ld , l i k e th e a p e x c o v e r , i s ma d e of

braz ed s ta in less - s tee l honeycomb and covered wi th ab la t ive ma te r ia l . Th is

hea t sh ie ld, o r ou te r s t ru c tu re , con ta ins the S /C umbil ica l connec tor ou t le t ,

ab la t ive p lugs , and a copper hea t s ink fo r the op t ic a l s ight ing por ts in the

lower equ ipment bay , two s ide observa t ion windows, two forw ard v iewing

windows,

and the ou te r

c o v e r fo r th e s id e a c c e s s h a tc h wh ich a l s o c o n ta ins

an observa t ion window.

1 . 1 . 2 . 3

S / C Co n t ro l s a n d D is pla y s.

In format ion re la t ing to con tro ls and d isp lays fo r opera t io n of the

s p a c e c r a f t an d i t s s y s t e m s i s provided in section 3 .

1 . 1 . 2 . 4

C / M M e c h a ni c a l C o n t r o ls .

Mechanica l con tro ls ( f ig u re 1 -4 ) a r e p ro vid ed in the c re w c o mp a r t -

ment fo r manu a l opera t ion of the c re w couch assem bly , s ide acc ess hatch

c o v e r s , fo rwa rd a c c e s s h a tch c o v e r , a nd ma n u a l o v e r r id e l e v e r s fo r th e

S P ACE CRAF T 012 CONFIGURATION

Mission Basi c Date

1 2

Nov 1966 Change Date P a g e 1 - 6


24/849


25/849


26/849

S M L A 0 3 - S C O

12


GENERAL

INFORMATION

FORWARD ACCESS HATCH COVER

EPS RECEPTACLE

(AFT SIDE

OF

M A I N

DISPLAY CONSOLE)

CONNECTOR

RACHET WRENCH

AIR OUTLET VALVE

(CLOSED POSITION)

CAUTION DECAL

LOCK PIN

OUTBOARD VIEW

0 OSTLANDING VENTILATION S Y S T E M (P L V )

@ FORWARD ACCESS HATCH

LOCK1 NC MECHAN I

SM

ACCESS HATCH FWD ACCESS

BREECH-LOCK HATCH COVER

IR I N L n

P O R T

CROSS-SECTION

VIEW

LANYARD (TO AFT i KAM

MTIEMIN ON LEFT

A ND CENTER COUCH)

SM-ZA-856A

F i g u r e 1-4.

C / M Me c h a n ic a l Co n t ro l s (S h e e t 3 of

3)

SPACECRAFT

12

CONFIGURATION

Miss ion Bas i c Da te l 2

1966

Change Date P a g e 1 - 9


27/849

SIM2 A - 0 3 - SC 0 1

2


G E NE RA L I N F

0

Rh4A T

ION

socke t a t one

end) is mounted on the cov er and wi ll bea r aga ins t

a

b ra c k e t

on

the tunnel wa l l . When tu rned by a handcrank or t o rque wrench wi th a

5 /32- i nch dr i ve . the jac ksc rew wil l in tend and a l low the cover to be ro ta ted

and removed . The cover i s ro ta ted by use of the ins ide handholds o r the

outs i de by an i te m of GSE and can only be re t ri eve d f ro m within the cre w

com par tm ent end of the tunnel.

1 . 1 . 2 . 4 . 5 Wind ows a n d S h a d e s .

FiL-e windows a r e p rov ided th rough the inner s t r uc t ur e and hea t sh ie ld

of the

C / M :

two forw ard viewing, two s ide observ a t ion , and the c r ew acc es s

ha tch windows. (See f igure 1 - 3 . ) During orb i t a l f l igh t , pho tographs of

ex te rna l o b jec ts wi l l be taken th roug h the v iewing and ob serva t i on windows .

T h e in n e r w in do ws ( in c lu d in g th e c i r c u la r in n e r h a tc h w in do w) a r e ma d e of

t e mp e r e d s i l i c a g la s s w ith 0. 25-inch- th ick double pan es , sepa ra t ed by 0 . 1

inch of sp ac e, and have

a

sof ten ing tempera ture po in t o f 2000F.

windows ( inc lud ing the sq uare o u te r ha tch window) a r e made of am orpho us

fused s il i con with a s ing le 0. 7-inch- th ick pane . Each pane con ta ins

a n

a n t i r e f l e c t in g c o at in g o n th e e x te rn a l s u r fa c e , a n d h a s b l u e - re d re f l e c t iv e

c o at ing o n the in n e r s u r fa c e fo r f i l t e r in g ou t mo s t in f ra re d a n d a l l u l t r a v io le t

ra ys , a sof ten ing tem per a tu re poin t of 2 8 0 0 " F ,

and a m el ti ng point of

31

1 0 F .

S h a d e s a r e p ro vid ed fo r c o n t ro l l in g e x te rn a l l igh t e n te r in g the C /M

T h e o u te r

th rough the t r iangula r fo r war d v iewing windows, the squ are s id e observ a t ion

windows, and the c i r cu l a r inner ha tch window. The se shades , ind iv idua l ly

d e s ig n ed fo r e a c h wind ow c o n f ig u ra t ion , a r e ma d e of m y l a r f i lm wh ic h h a s

b e e n h e a t - t r e a te d to ro l l up when no t he ld f la t . The shad es a r e opaque fo r

z e ro lig h t t r a n s mi t t a l , h a ve a n o n re f l ec t iv e in n e r a lu min iz e d s u r fa c e , two

s n a p fa s t e n e r s a n d fa b r i c h a n dle s fo r a t t a c h in g o r r e mo v in g f ro m a p a r t i c -

u la r window, and a 3 /4 - inch s t r i p of Ve lc ro hook m at e r ia l a round the ou te r

sur fa ce fo r ho lding the shade aga ins t the Ve lc ro p i le a round the pe r im ete r of

the window.

If d e s i r e d , a shade can be pee led back f r om the V elc ro p i le

m at er i a l and s towed in place on one s ide of he window.

1. 1.

2 . 4 . 6

C ab in P r e s s u r e C o n tr o l s.

T wo c o n t ro l l e v e r s fo r ma n u a l ly o p e ra t in g the E CS c a b in p re s s u re

re l ie f va lves a r e loca ted near the C/ M le ft couch and le f t s ide window.

f i g u r e 1 - 4 . )

ing and c los ing the redundant s ide s of the au tomat ic cab in p res su re regu l a to r .

(For a d di t io n al in fo rma t io n , r e fe r to th e e n v i ro n me n ta l c o n t ro l s y s te m in

sec t ion

2 . )

( S e e

T h e s e l e v e r s a r e p r ov i d ed a s a m e c h a n i ca l o v e r r i d e f o r o p en -

1 . 1 , 2 . 5

Cre w Equipment and Equipment Bays .

E a c h c r e w m e m b e r h a s p e r s o n a l a n d a c c e s s o r y e q u ip m e n t p r o vi d e d f o r

h i s u s e in th e c re w c o mp a r tme n t .

s i s t of a p r e s s u r e g a r m e n t a s s e m b l y ( P G A ) with a t tach ing hose and

u mb i l i c a l , a c o mmu n ic a t io n s a s s e m b ly ,

a

c o n s ta n t -we a r g a rme n t , b io -

me d ic a l s e n s o r s , a n d ra d ia t ion d o s i me t e r s . lMajor i t e m s of a c c e s s o r y

equipment sha red by the c re w cons is t o f an in -f l igh t tool se t and a med ica l

k i t . ( F o r a d e ta i l e d l i s t of c re w e q u ip me n t, r e fe r to s e c t io n 6 . ) (Spec if ic

i t e m s c o n ta ine d in th e

C / M

e q u ip me n t a n d s to ra g e b a y s a r e l i s t e d in f ig u re 1-6 .

)

Ma jo r i t e m s of p e r s o n a l e q u ip me n t co n -

SPACECRAFT 012 CONFIGURATION

Mis s io n Ba s ic Date l 2

1966

Change Date P a g e 1 -1 2


28/849


29/849

-

FORWARD REFERENCE

VIEW

LEFT-HAND FORWARD EQUIPMENT BAY (LHFE

-

1

2

3

4

5

6

7

B

9

IO1

12

13


30/849

+X

2

3

Ga

chronotopmph

4

Flight

qwlifisotim

t o p

n c o d r

5

Scientific q u i p m m p m n m t

A

6

Display/ot i i tde gyrrroccda-eter

(EU)

7

Food

itoras.

(5

containen)

8 A W t h g y r o ond ocalem-mter

9 b t . gym

IO

CWpl ing

ond

d i i p k y pnl

1I

I2

13 IMU

M t m l p w l

14

Liphting cont ml

15

16

17

Pallonding ECS

m a r m b l a

18

Fo-d OCC.L(

hatch

(nf)

19

Sox~ont

l a c o p

eyepieca s t o w

20 Sextont ond t e l a c o p

1

21

Computer display

and

control

p m l

22 G 6 N c on t ro l panal IMU

23

S u ni v ol p m r i i i o n

(nf)

24

25 P a r ono o l l m b l y ( P U )

?6 Doto s t o w q u i p e n t

s p c w i t

S~OWOQ*bop ond

sc ient i f ic .qu ipen(

i t o r q e (,,I

Sr pi lo t wi t mnnector p n c l o nd cl ec tr ic ol e ~ n ~ c t o rno

Cab in

air m c i r w l o t i m b n

( reo

F O I W O ~ c w

ha tch c wer

(nf)

Patloding ECS air outlet duct

Cl in ico l monitoring nst-mi wt comportment

27

Towel

s t o m g .

28 Sigml

mnd i twn ing .qu ipen t

29

VHF mr l t i p l ue r

30 Dot0

wi r i n g

31

P r d v l o t i m

OIOC-I

32

VHF ncore ty

&con

ond

VHF-AM tmrun i t t emc e i re r

33

Audio

ceniar

34 Centml timing

35

TV optics

rtom~e

re f )

36

h l u - c d e m o d u l o t i o n ( K M )

unit 2

t el anet r, q u i p e n t

37

38 h l w - c d a m d u l a t i c m

(PCM)

unit

I

l e l m e t y

q u i p . n t

39 Scientific q u i p e n t

ewoprrmont C

40

S - b o d

-.I onpl i f ier

41

C - b o n d t m n p a d . r

42

C@

ob.orb.r

mntoiwr (mf)

43

U

Digitol up-ho link

45

Unifid

$-bond e q u i m n t

46 Fecal

coni iter b i t i d )

47

Scientif ic quipnent mmporrmmt 8

48 &I1 c h o m l E D ,

49

Dolo

pcLog * conlo iner

lolm

m

wtbood

couch

ha )

50

G I N c a p u t e r

51 Pitch chonn.1 E D ,

52 A u x i l i o y

E D ,

VHF-FM

Imrunittar ond

HF tmrrrceivar

Food and

rort

table (in-flight tDol set)

Y a w channel E t *


31/849

41

C- bond t m npwd. r

42

CQ oborbr cm t o in r ( re f)

43

U

Dipitol up-doto

lint

45 Unified

S - b d

q u i p e n t

46 Fecal coni i ter

h i t i d )

47

4E bl l c h o m l t U

4 9

h t o pockog .

COnto in r (01.0

m w t k d

ouh

ha )

50 G h N c m p u t e r

51

Pitch

chonnel

E C *

52 A u r i l i o y E a

9 Yor3PmeI EU

F d

d o k

toble

(in-flight

tml

u t )

Scirntific e q u i m n t m m p O m m t B .

I

RIGHT-HAND FORWARD EQUIPMNT B A Y ( R HF E B) A N D R I G H

1

C@ obs0rb.r c o n b i w r

(n9

2

W a l e mampnnsnt

sn1.m


32/849

SMZA-03-SC012

POLLO OPERATIONS HANDBOOK

G E N E F AL

INFORMATION

,

\

'\\

(RHFEBI AND RIGHT-HANDEPIJIPMENT B AY (RHEB)

I 7

I 8

I9

20

ZI

21

21

24

25

26

Z?

29

n

F i g u r e 1-6.

C / M E q u i p m e nt and Stowage Bays

P A C E C R A F T 012 CONFIGURATION

p a g e 1 - 1 3 / 1 - 1 4

Miss on Basic Date

l 2

1 9 6 6 Change Date


33/849

SMZA -03-SCO 12

AP OL L O

OPERATIONS

HANDBOOK

GEN ERA L INFORMATION

1.1 .2 .6

1. 1.2.7

1 .1 .2 .8

1. 1 .2 .9

Food and Wate r .

Food and wate r p rov i s ions , including wa te r de l i ve ry and food pre par a -

t io n eq u ip me nt , a r e a v a il a b le in th e c re w c o mp a r t me n t L HE B a n d L E B

(f ig u re 1 -6 ) fo r the leng th of the miss ion .

by add ing wa te r to p las t ic bags con ta in ing the dehydra t ed food and knead ing

th e mix tu re .

a s t r o n a u t .

Hot o r c old wa te r

is

ava i lab le

at

the po tab le wa t e r supply pane l

fo r food recons t i tu t ion .

a

f l e x ible h o s e f r o m th e wa te r d e l iv e ry u ni t.

by-produc t o f the EPS fue l ce l ls .

F oo d ma y b e p re p a re d

Pr ep ar ed food can be squeezed d i rec t ly in to the mouth of a n

Chi l led d r ink ing wate r

i s

suppl ied to the c r ew th rough

The potab le wa te r

i s a

Waste Management.

Wa ste ma n a g e me n t p ro v i s io n s in th e c r e w c o m p a r tme n t R HF E B a nd

AESB (f igure 1 -6 ) cons i s t of equ ipment fo r co l lec t ing , s te r i l iz i ng , and

s to r in g h u ma n fe c a l ma t t e r a n d p e r s o n a l h yg ien e wa s te s ( s u c h a s u s e d

c leans ing pads , towel s , e tc . ). F e c a l m a t t e r a n d p e r s o n a l h yg ien e wa s te s

a r e co l lec ted in po lyethy lene bags , d is in fec ted , and s to red in a v e n te d a re a .

Ur in e i s e x p e l l e d o v e rb o a rd in to s p a c e .

Surviva1 Equipm ent.

T h e s u rv iv a l k i t s s towe d in th e c re w c o mp a r tme n t RHF E B (f ig u re 1 -6)

a r e ava i lab le fo r the pos t land ing phase of the mis s ion ( land or wa t e r) . The

ma jo r i te ms con ta ined in each k i t inc lude 6 pounds of w a t e r , a d e s a l t e r k i t ,

a

o n e -ma n l i f e r a f t , r a d io t r a n s c e iv e r , p o r t a b le l ig h t , s u n g l a s s e s , a n d a

m a c h e t e .

in th e space su i t s towage bag dur ing the o rb i t phase of the miss i on .

(See

f ig u re 1 -6 . )

Life ves t s worn by the c r ew dur ing l if t -o ff and en try a r e s towed

Aft Compartment .

T h e a f t c o mp a r tme n t ( f ig u re 1 -3 )

i s

t h e a r e a e n c o mp a s s e d by th e aft

T h is c o m p a r tme n t c o n ta in s 1 0 re a c t io n c o n t ro l

p o r t io n of th e c r e w c o m p a r tme n t h e a t s h ie ld ,

a f t hea t sh ie ld , and a f t por t ion

of the p r im a ry s t ru c tu re .

e n g in e s , a n imp a c t a t t e n ua t io n s t ru c tu re , in s t ru me n ta t io n , a nd s to ra g e t a n k s

f o r

wa te r , fu e l , o x id iz e r , a n d g a s e o u s h e l iu m. (F o u r c ru s h a b le r i b s , a lon g

t h e S / C +Z x i s , a r e provided as pa r t of the impac t a t tenua t ion s t r uc t ure to

abs orb energy dur ing a land imp ac t .

)

The a f t hea t sh ie l d , which enc loses the la rg e end of the C/M , i s a

s h a l low s p h e r i c a l ly c o n to ure d a s s e mb ly . It i s made of the s am e type of

m a t e r i a l s

a s

o th e r C / M h e a t s h ie ld s . Ho we v e r , th e a b la t iv e ma te r i a l o n

th i s h e a t s h ie ld h a s a g r e a t e r th i c k n e s s fo r th e d i s s ip a t io n of h e a t d u r in g

e n t r y .

C / M t o t he

S / M .

E x te rn a l p ro v i s io n s a r e ma d e o n th i s h e a t s h ie ld fo r c o nn e ct ing th e

~~

SPACECRAFT 01 2 CONFIGURATION

Mi s s io n Ba s ic Date l 2 1966 Change Date Pag e ' - I 5


34/849


35/849

SMZA

-03-SCO 12


--

GENERAL INFORMATION

I D I Z E R T A N K

ECS SPACE

ECS SPACE RADIATOR

EPS SPACE RADIATOR

SECTOR 4

( S K IN P A R T IA L L Y R E M O V E D

F O R

CLARITY)

C / M recton ( top v i e w )

SPS ENGINE /

E X P A N SI O N N O Z Z L E

1 and 4 are 50-degree s ec ton

2 and

5 ore

70dagree recton

3

and

6 am

&)-degree s ec ton

SERVICE MODULE ITEMS

S e c t o r 1

E l e c t r i c a l p o w er s y s t e m s p a c e r a d i a t o r

S u p e r - c r i t i c a l o x y ge n t a n k

(two)

S u p e r - c r i t i c a l h y d r o g e n t a nk (two)

S e c t o r 2

E n v i r o n m e n t al c o n t r o l s y s t e m s p a c e r a d i a t o r

S e r v i c e p r o p u l s i o n s y s t e m o x i d i z e r t a n k

R e a c t i on c o n t r o l s y s t e m p a c ka g e ( + Y - a x i s )

S p a c e r a d i a t o r i s o l a t i o n v a lv e (two)

S e c t o r 3

S e r v i c e p r o p ul s i o n s y s t e m f u e l ta n k

R e a c t io n c o n t r o l s y s t e m p a c k a g e ( t Z - a x i s )

S e r v i c e p r o p u l s i o n s y s t e m h e l i u m t a n k s ( two)

S e c t o r

4

E l e c t r i c a l p o w er s y s t e m s p a c e r a d i a t o r

F u e l c e l l p o w e r p la n t ( t h r e e )

H e l i u m s e r v i c i n g p a n e l

R e a c t i o n c o n t r o l s y s t e m c o n t r o l u n i t

E l e c t r i c a l p o w e r s y s t e m p o w e r c o n t r o l r e l a y b o x

S e r v i c e m o d u l e j e t t i s o n c o n t r o l b a t t e r y ( two)

S e r v i c e m o d u l e J e t t i s o n c o n t r o l l e r s e q u e n c e r ( t wo )

W a t e r s u p p l y t a n k ( t w o )

S e c t o r 5

E n v i r o n m e n ta l c o n t r o l s y s t e m s p a c e r a d i a t o r

S e r v i c e p r o p u l s i o n s y s t e m o x i d i z e r t a n k

R e a c t i on c o n t r o l s y s t e m p a c k a g e

( - Y

a x i s )

S e c t o r 6

S p a c e r a d i a t o r s e l e c t i o n v a l v e ,

(two)

G l y c o l s h u t o f f v a l v e s

(two)

R e a c t io n c o n t r o l s y s t e m p a c k a g e ( - Z a x i s )

S e r v i c e p r o p u l s i o n s y s t e m f u e l t a n k

C e n t e r s e c t i o n

S e r v i c e p r o pu l s i o n s y s t e m h e l i u m t a n k (two)

S e r v i c e p r o p u l s i o n s y s t e m e n g i n e

SM-2A-643 E

Figure

1 - 7 .

Spacecraft 012 Service

Module

S P A C E C R A F T

0

12 CONFIGURATION

Miss ion

Ba s ic Da te,1 2 1966 Change Date Pag e

' - I 7


36/849


37/849


38/849


39/849

SM2A -03-SCO 1 2

A P O L L O OPERATIONS HANDBOOK

v

SYSTEMS D.4T-4

SECTION

2

SUBSECTION 2.1

GUID.4NCE .4ND CONTROL

2 . 1 . 1

SYSTEMS INT ERFA CE. GUIDANCE -4ND CONTROL.

2 . 1 .7

Apollo CSM a tm osph er ic and space f l ight i s ach ieved by app l ica t ion of

contro l led t rans la t ion fo rces and ro ta t iona l fo r ce mom ents . Guidance and

c o n t ro l in i t i a t e s an d t e rmin a te s th e th ru s t a n d ro ta t ion a l fo rc e s a n d fo rc e

m o m e n ts a s

a

function of the mag nitude of the change r equ ired . Guidance

and con t ro l p rov ides the fo llowing bas ic func t ions:

Atti tude Control

Guidance

Navigation

Atti tude con tro l i s a funct ion assoc ia te d wi th s pace cra f t o r ien ta t ion

with r e s p e c t to a n in e r t i a l r e fe re n c e o r a kn own c o o rd in a te s y s te m .

Guidance is a funct ion r equ ir in g a combination of a tt i tud e cont rol with ra te

s tab i l iza t ion and s t ee r i ng command s fo r the purpose of modify ing space-

c ra f t t r a j e c to ry v ia ma j o r v e lo ci ty c h a ng e s .

space cra f t pos i tion and ve loc i ty , and pred ic ts fu tu re posi t ion .

Naviga t ion de te rmines

To accomplish miss ion r equ ire me nts , the gu idance and nav iga t ion ,

s t a b il i z a t io n an d c on t ro l , s e rv i c e pro p u l s io n , a nd re a c t io n c o n t ro l s y s te ms ,

p lu s the a s t ro n a u t s , a r e in te g ra te d in to a n a u to ma t ic /m a n u a l c lo s ed lo op

c o n t ro l s y s te m.

Guidance and con tro l ac t iv i ty is g rouped in to th r ee p r of i le s of f l igh t :

c o a s t in g , p o we re d , a nd a tmo s p h e r ic . T h e p r im a ry c o n t ro l lo o p s inv olve d

a r e i l l u s t ra t e d i n f ig u re s

2 .

1-1 th rough 2 . 1 - 4 .

abbrev ia ted in tegra t ion of a l l ma j o r e q u ip me n ts n e c e s s a ry to a c c o mp l i s h

the ac t iv i t ie s in a l l th ree f l igh t p rof i le s .

d iv ide the equ ipment in to the p roper pe rspec t ive fo r eac h prof i le .

F i g u r e 2. 1 -

1

i s a n

F i g u r e s2 . 1 - 2 th rough

2 . 1 - 4

I t mus t be noted tha t in f ig u re

2 .

1-1 ,

th e loo p s a r e c lo s e d th a t

F or powered f l igh t ( P F ) o r

epr ese n t coas t ing f l igh t ( CF ) funct ions .

a tmo s p h e r ic f l ig h t ( A F ) , open the coasting fl ight loops and close contacts

re p re s e n t in g th e d e s i re d lo o ps .

COASTING FLIGHT

The gu idance and con tro l ac t i v i t ie s invo lved in coas t ing f l igh t a r e

accomp lished th rough the bas ic funct ional loops shown in f igure

2 . 1 - 2 .

GUIDANCE -4ND CONTROL

Miss ion Bas ic Da te l 2 1 9 6 6 Change Date Page 2 * 1 - 1


40/849

SMZA - 0 3 - S C O

1 2


SYSTEMS DATA

The se loops p rov ide a t t i tude re fe renc e , a t t i tude con tro l , a t t i tu de ho ld , and

a u to ma t ic a nd ma n u a l ma n e u v e r c a p a b i l i t i e s n e c e s s a ry to a c c o mp l i s h the

s e v e r a l t a s k s inv olve d d u r in g c o a s t in g f lig h t.

r e fe re n c e a nd c o n t ro l lo o ps re q u i re d fo r a l l p h a s e s of flight.

T h ey a r e a l s o th e c e n t ra l

A r e fe re n c e a t t i tud e f r a m e i s e s t a b l i s h e d by th e G & N i n e r t i a l m e a s -

ur em en t uni t ( IMU), an d / or by the SCS body-mounted a t t i tude gyros

(BM AGs), and a t t i tude gyro coupl ing un it (AGCU). Ine r t ia l se ns or s sens e

S I C m o ti o n c o n t r a r y t o th e r e f e r e n c e f r a m e .

and ra tes a r e condi t ioned th rough se r vo e lec t ro n ics and logic to in i t ia te

counte r mot io ns v ia the reac t io n je t con tr o l (RCS) which nu l l i f ie s the o r ig ina l

motion. The 4 G C i n s e r t s a u to ma t ic c o n t ro l a n d ma n e u v e r c o mma n d s in to

the loop . The ro ta t ion , t r ans la t io n , and a t t i tude impul se con tro ls ins e r t

manua l com man ds in to the loop.

(F DAI) i s th e S / C a t t i tude v isua l d isp lay .

T h e s e n s e d a t ti t ud e e r r o r s

The f l igh t d i rec tor a t t i tude ind ica tor

2 . 1 . 3

2 . 1 . 4

POWERED FLIGHT.

P o we re d f ligh t i s c o n s id e re d th a t which w i l l u s e th e S /M s e rv ic e

propuls ion sys tem (SPS) eng ine to in i t ia te a m ajo r ve loc i ty change .

F i g u r e

2 .

1 - 3 i l l u s t r a t e s th o s e b a s ic loo p s n e c e s s a ry fo r th e t a s k s in v ol \ , ed .

-4s shown, the loops a r e an ex tens ion of those requ ire d fo r coas t ing f l ight .

Added,

a r e the (SP S) eng ine on-off th ru s t log ic and the SPS g imb a l c o n t ro l

loops . In coas t in g f l igh t , a l l a t t i tude con tro l is th rough the RCS. Powere d

f l igh t , by the SPS engine , req u ir es r o l l con t ro l th rough the RCS, and p i tch

and yaw contro l by g imbal ing the

SPS

engine nozzle .

thr usti ng i s by the -4GC.

cont ro ls c an be used ins tead of o r to backup au tomat ic func t ions .

-4

T

MOSP HE RI C

FLIGHT

P r im a r y c o n t rol of

However, f ig u re

2 .

1-3 show s how var ious manua l

Atm osph er ic f l igh t i s encou nte red dur ing the en tr y phase of the

mis s ion a t which t ime the S / C e x p e r ie n c e s a e ro d y n a mic fo rc e s .

F i g u r e

2 .

1-4 i l lu s t ra tes the bas ic loops requ ired fo r con tro l of the S /C

d u r in g th i s p h a s e . T h e c e n t ra l lo o p i s id e n t i c a l to tha t in f igure

2 .

1 - 2 .

T h e ma in d i f fe re n c e i s th a t s e r v ic e mo d u le /c o mm a n d mo d ule ( S / M - C / M )

s e p a ra t io n h a s t a k e n p la c e ,

and the command module RCS sys tem is

u s e d .

An o th e r d i f fe re n c e i s th a t th e a e ro d y n a mic fo rc e s w il l s t a b i l i z e th e C / M in

pitch and yaw,

and the en tr y g - leve l ( l i f t vecto:- con tro l ) wi ll i nc r eas e o r

d e c re a s e th ro u g h ro l l c o n t ro l . P r im a r y c o n t ro l i s au to ma t ic , w i th ma n u a l

ro ta t ion c o n t ro l a v a i l a b le , in exrent of au tom atic con tro l malfun ction s .

Fo r de ta i led oper a t ion of the sev era l loops invo lved in gu idance and

c o n t ro l ,

s u b s e c t io n

2 . 2 ,

and the stab i l iza t ion and con tro l sys tem , subsec t ion 2 . 3 .

re f e r to the desc r ip t i ons o f the gu idance and na\ . iga tion sy s te m,

GUIDANCE AND CONTROL

Mis s io n Ba s ic Date l 2 1966 Change Date Page 2 . 1 - 2


41/849


42/849


43/849

C O W N D S DIRECT DECOUPLING

(FCSM THRUST ON -O FF

SENSING) COMM ANDS ROLL ERRORS

N A V I G A T I O N

SIGHT I

NG

ANGLES ATTITUDE E R R O R S

PF

$

- I+ -+PTICAL

----

I ,

-

4

F - ~ _ E E R I ~ ~ E ~ R ~

2z CF I

7 -

T

I

I

I

I

I

I

I

M A N U A L

A V SETTINGS

?

TO

AG C THRUST ON- OFF

G U ID A N C E A N D

N A V I G A T I O N C O N T RO L A G C

LOO PS (CF, PF, AF)

MANUAL c

SPS

ENGINE

.

THRUST

ON

ON-OFF AND

C O W N D S VELOCITY

SENSING

- sRK

-

-+I-----+

LOOP

(wl

PF

C O M M A N D S (GbN)

FROM

- -

- - ---

ATTITUDE AND

.I

CDU

SERVO

STEERI NG

C O M M A N D S

Ln l T U D E

- - - - - _ _ _

PITCH AND

Y A W E R R O R S

ATTITLID

CHANGES

ATTITUDE

C O W N O S

ELECTRONICS - - k-4

ND CONTROL

ClRCUlTS

FROM

IMU -

ATTITUDE

I

10 IMU SENSORS

A l~m

51

as

.

PF

t

L l

M i


44/849

S M 2 A

-03-sc012

A P O L ~

PERAT IONS HANDBOOK

cFsc

r-

1

SYSTEMS DATA

I

-J

AERODYNAMIC

$

F

A N U A L

DIRECT cFzr

LJLLAGE

C O M M A N D

FORCES

7;- oToONTROL AND ( (

RCS ATTITUDE C r T L

~ ~ ~ l ~ a

E R R O R S pF

CF JET SELECTION L m P ( C F , PF, AF)

STEERING- - - - - - E R R O R S SUMMING

SUMMING

JET CONTROL

LO GI C CIRCUITS

CIRCUITS CIRCUITS

THRUST

I ACCELERATION

A N D

T AF DIRECTION

DYNAMICS

t

I

PITCH AND

GIMML

i t - - SERVO

PF

I

I

PF

t

I

FORCE

+

TO

M N C

ELECTRONICS

(SCS)

SPS ENGINE

GIMBAL

CONTROL LOOP (PF)

TO

MTVC

ELECTRONICS

4

I

I

1

OLL

T p J

w T ATE

I

-L

CF

I

I

PITCH,%-AW

I

RATES

I

I

BhUC

FROM FROM

1

T f f

1

OLL

CF

T p J

1, w T ATE

I

-L

I

I

T P i T i H ~ A W

I

RATES

I

I

BhUC

FROM FROM

.

BACK UP ATTITUDE RO LL

RATE (BMA GS) RATE

(SCS)

scs

GYRO

FROM

BM AG S ATTITUD E REFERENCE (ARS),

FRO M INERT IAL SENSOR, DISPLAY,

RATE A N D FEEDBACK

LOOPS

GYROS (CF, PF, AF)

FROM

A G C U

TORQUE

- - -

-I-f f

I

ATTITUDE

RATE

GYROS

ORBITAL RATE

LOCAL VERTICAL

~~

ATTITUM CHANGES

VELOCITY CHANGES

SM-2h-947

Figure2.

1 -

1 .

Integrated Flight Profile Functional Flow Diagram


Mission Basi c Date

l 2

N? 1966 Change Date I P a g e 2 . 1 - 3 1 2 . 1 - 4


45/849


46/849

-

ROTATION

COMMANDS

________*

PROFORTIONb

AllllUM I

PATES

TOTAL

A n l T U [ W

-

I ATTITUDE

1

*

A N D LIMITING 4

f ADBAND

TTITUDE COMMANDS

I

(SCS)

I )

.

ATTITUDE ERRORS

M A N U

TRANS

C O M M

M N U M

ROTATION

C O W N O S

I

ATTITUDE

IMWLSE

CONTROL

(GAM

I

P

M

-b

------

ATTI

DISP

f

AGCU ARS

AT^

SENSORS

4-

EULER 4

OR

L O

REF

A l l

A L I G N

COMPUTER

I . ..

I

M


47/849


48/849

1

I

N A V I G A T I O N C O NTRO L L O O P

FROM NAVIGATIONS

OR UPLINK (MSFN)

' A G C

N A V I G A T I O N

A N D

GUIDANCE

~ R O G M ~

(

I

TIME

-c

VELOCITY I

HANGES

ACCELEROMETER

sPS

MANUAL DIRECT

AND

THRUST ON-O FF

ENGINE

(SK)

+ CONTROL

THRUST ON-OFF

C U A M A N D S (G61.I)

i

I

I

STEERING

C O W N D S

I

I

I

I

I I

A N D C O N TR O L

I ( G h W

ATTITUDE

I

I

I

COMMANDS

T

I

I 4 1

VELOCITY

CHANGES

FDA1 (SCS)7

ATTITUDE

-


49/849

1

I

I

M A N U A l

ROTATION 4

C O M M A N D S

RATION

ACCELEROMETER

SENSOR

MANUAL DIRECT

AND THRUST ON-OFF

C O M M A N D S

ENGINE

CONTROL

ON

ROTATION

C O M R O S

(SCS)

I

2

PSEUDO RATE

MODULATORULSE

(SCS)

-

I

ATTITUDE

*

1 AND L IMIT ING

i

I

I

I

R O LL ERRORS I DEADMND

ATTITUDE

COMMANDS

FDA1 (SCS)

ATTITUDE 4

T

I

r----+-

-

ATTITUIX

RATES

TOTAL

ATTITUDE

I

I

~

- . -

-

4

*

\

-c

4

MANUAL

TRANSLATION

C O M M A N D S

PROPORTIONAL

GIMBAL

POSITION ELECTRONI

CONTROLS

A N U A l

LIM

ATTITUDE ERRORS

I

I

ATTITUMRS

S E N S O R S

*

EF

2zGN

(W AG S) SCS ATTITUDE CHAN GES

VELOCITY CHAN GES

F

Mission


50/849

SM2A

-

0

3

-

SCO

12


SYSTEMS DATA

RCS ATTITUDE

C O N T R O ~

I

I

I

I

I

1

L O O P

M A N U A L

DIRECT

C O M M A N D

DIRECT CONTROL

c

MANUAL TRANSLATION

TRANSLATION

CONTROL ULLAGE

COMMANDS (SCS)

c

T R E A C T I O N A N D 1

ORCE

JET

REACTION

CONTROL

JET SELECTION ~ (S/MRCS)

'

PSEUDO RATE

e

PULSE

(SC9

LOGIC (SCS)

ODULATOR -C

- 1

J -

GIMBAL

POSITION

SENSORS

*

66)

.

G I M B A L

POSIT ION

CONTROLS

ELE CTRON1

CS

1 I

SPS ENGINE GIMBAL

CONTROL LOOP

.

GIMBAL ENGINE

C O N T R O L G I M A L

ELECTRONICS CONTROL

G I M B A L -

SERVO

ELECTRONICS

-

(SCS)

(SCS) (SPS)

c

'

R A T E

GIM A L

SENSORS

( S P n

-

I

I

I

TORQUE

I

THRUST

ACCELERATION

A N D

THRUST

DIRECT

ION

OR

TORQUE

n

ATTITUDE REFERENCE, INE RTI AL SENSOR,

DISPLAY, AND FEEDBACK LOOPS


Basic

Date 12 Nov 1966 Change Date page

2.

1 - 7 / 2 . 1 - 8

Miss ion


51/849

I

I

I

I

I

I

I

I

I

I

I

I

I

I

VELOCITY I

CHANGES

I

-

I

I

I

I

I

I

I

I

I

I

I

I

I

VELOCITY

ATTITUDE

CHANGES CHANGES

I

AUTOMATIC GUIDANC E

AND I

N A V I G A T I O N C O NT RO L LOOP I

A G C

N A V I G A T I O N

A N D

GUIDANCE

PROGRAMS

( G W

N A V I G A T I O N

S IG H TIN G

ANGLES

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

ERROR

1

STEER

ATTITUDE

RATES

1

ATTITUDE

31

TTITUDE

L

I


52/849

3

M A N U A L R O T A T I O N

ROTATION CONTROLS .

COMMANDS (SCS)

TTITUDE

I

I

I

1

I

I

I

PITCH/YAW

E R R O R

D E C O U P t l N G

-

.

I

ATTITUDE

i *

+

- STEERING ERRORS 1 DEADBAND

A N D L I M I T I N G

-

(SCS)

I

-

h

ARS

ATTITUDE

REF

-

SENSORS

A G C U

EULER

COMPUTER

-

-

A T 1

ATTITUDE

RATES

(BMAGS) SCS,

ATTITUDE

I+

ROPORTIONAL

MANUAL

C O M M A

,

PSEUD

PULSE

MODU

.------------------

ATTITUDE REFERENCE, INERT

DISPLAY, AN D FEEDMCK LO

$MAG

1ACKUP

UTE

M i s s on


53/849

SMZA-03-SC012


SYSTEMS

D A T A

4

1

RCS A l l lTUDE CONTROL I

L O O P

I A E R O D Y N A M I C

IRECT CONTROL

. MAN UAL DISABLE

C O W N D S

-

f i

I FORCES

I

I

PSEUDO RATE REACTION

PULSE JET SEL ECT ION LL A R O T A T I O N

MODULATOR LO GIC (SCS)

(scn

JET CONTROL

14

- (C / M R C 9 I

-----C

SENSOR,

U Y , A N D R E D M C K LOOPS

SPACECRAFT

DYNAMJCS

A

O T A T I O N

ATTITUM CHANGES

VELOCITY CHANGES

SM-24-943

Figure 2. 1-4.

Atmospheric Flight Profile Functional

Flow

Diagram


Basic Date

l 2 Nov

1966 Change Date Pa ge 2 . 1

-9/2.1-10

Miss on

3


54/849

SMZA-03-SCO 1 2

APO LLO OPERATION S HANDBOOK

SYSTEMS DATA

SECTION

2

SUBSECTION

2 . 2

GUIDANCE AND NAVIGATION SYSTEM ( G & N )

2 .2 .1

2 . 2 . 2

INTRODUCTION.

The guidance and navigation (G&N)s y s t e m m e a s u r e s s p a c e c r a f t

a t ti tud e a n d v elo ci ty, d e te rmi n e s t r a j e c t o ry , c o n t ro l s s p a c e c ra f t a t t i tu d e ,

con tro ls the th r us t vec tor of the se r v ic e p ropuls ion eng ine , and prov ides

abor t in format ion and d isp lay da ta .

ve loc i ty and pos it ion , and computa t ion of the t ra j ec to ry p ar am et e r s i s

a c c o mp l i s h e d

by

the manned space f l igh t ne twork (M SFN).

P r im a r y d e te rmin a t io n of th e s p a c e c r a f t

T h e G & N s y s te m c o n s i s t s of th re e s u b s y s te m s a s fo l lo ws:

0 In e r t i a l s u b s y s te m (ISS)

0 Co mp u te r s u b s y s te m (CS S)

0 Op t ic s s u b s y s te m

(OSS)

T h e in e r t i a l s u b s y s te m is composed of an ine r t ia l mea sur em ent un i t

(IMU),

p a r t o f th e p owe r a n d s e rv o a s s e mb ly (P S A) , p a r t of th e c o n t ro l s a nd

disp lay s , and th re e ine r t ia l coupl ing d isp lay un i ts (CDUs) .

an ine r t ia l re fe r ence with a g imba led , t h r ee -degree -o f- f reedom, gyro

s tab i l ized s tab le p la t fo rm .

The IlMU provides

T h e c o m p u t e r s u b s y s t e m i s composed of an Apollo guidance com put er

(AGC), and two disp lay and keyboard pane ls (DSKYs ) , wh ic h a r e p a r t of th e

contro ls and d isp lay s . The AGC

i s

a d ig i ta l comp ute r which pr oc es se s and

c o n t ro l s in fo rma t ion to a n d f ro m th e IMU a n d o p ti c s , a n d s t o re s p ro g ra m s

a n d re fe re n c e d a ta .

T h e o p t ic s s u b s y s te m

i s

composed of a scanning te lesco pe ( SCT) , a

sex tan t (SXT), d r i ve mot or s fo r pos i t ion ing the SCT and SXT, p a r ts of the

PSA, p ar t of the con tro ls and d isp lays , and two opt ics CDUs. The SCT and

S XT a r e u s e d to d e te r min e th e s p a c e c ra f t po s i tio n a n d a t ti tu de w i th r e l a t io n

t o s t a r s a n d / o r l a n d m ar k s .

T h e th r e e G&N s u b s y s te ms a r e c o n f ig ure d s u c h th a t th e CSS a nd OSS

ma y be operated independently . Th is a llows continued use of the CSS an d/ or

OSS in the event of a malfunction in one of the se su bs ys te ms o r the ISS.

S y s te m p o we r re q u i re m e n t s a n d r e fe re n c e s ig n a l s a r e p ro v ide d b y th e po wer

a nd s e r v o a s s e m b l y

(PSA) .

the command module lower equi pment bay ( f ig u re 2 . 2-1) .

b r e a k e r s , caution and war nin g ind ica tor s , and one of the

D S K Y s

a r e lo ca ted

on the m ain d isp lay conso le .

FUNCTIONAL DESCRIPTION.

Major components of the sys tem a r e loca ted in

S y s t e m c i r c u i t

The gu idance and nav igat ion s ys t em prov id es capab i l i t ie s fo r the

f ol lowing:

0

0

Ine r t ia l ve loc i ty and pos i t ion (s t a te vec t or) computa t ion

Opt ical and ine r t i a l nav iga t ion meas ur em ent s

GUIDANCE AND NAVIGATION SYSTEM


55/849

G

D

-

4

N

N

G

O

S

Y

M

2

.

2

-

2

M

i

s

s

i

o

n

B

c

D

e

1

N

1

C

D

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P


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SYSTE-MS

D-4T.A

0 S p a c e c ra f t a t t itu d e me a s u r e me n t a n d c o n t ro l

Gen era tio n of guidance co mm an ds durin g CSXI-powered fl ight and

C / L I a tmo s p h e r ic e n t ry .

0

The G & K sy s t em is in i t ia l ly ac t iva ted and a ligned dur ing the p re launch

Du r in g th e a s c e n t p h a s e , th e s y s te m m e a s u r e s v e lo c ity a n d a t t i tu d e ,

hase .

c o mp u te s p os i t io n , c o m p a re s th e a c tu a l s p a c e c r a f t t r a j e c to ry wi th a p re

-

d e te rm in e d t r a j e c to ry , a n d d i s p la y s p e r t in en t d a ta . T h e f ligh t c re \v u s e s

the d isp layed in format ion a s a n a id fo r d e c i s io n to a b o r t o r c o n t in u e th e

mis s io n . Ho we v e r , s p a c e c ra f t c o n t ro l i s main taine d by the S-IVB guidance

u n t il CSM/S -IVB s e p a ra t i o n . Upon s e p a r a t io n , th e G&N s y s te m a s s u me s the

guidance and nav iga tion func t ions us ing the da ta acquir ed dur ing a scen t .

During per iods when onboard ve loc i tv and /o r a t t i tude change >ens ing

i s

n o t r e q u i re d , th e I l IU i s p la ce d in s t a n d b y o pe ra t io n to c o n s e rv e e l e c t r i c a l

p o we r .

a l s o be p la c e d in s t a n d b y o p e ra t io n to c o n s e rv e e l e c t r i c a l p o we r.

guidance a nd navigation function i s t o be re s t o re d , the

I l l U

and -AGC a r e

reac t iva ted , wi th the .AGC us ing the l a s t comp uted veloc i tv as the bas is fo r

fur the r veloc itL com puta t ions , New pos i t iona l da t a mus t be acquire d

i r o m

opt ica l s igh t ings

or

LISFN t h ro u g h t e l e me t r y o r v o ic e c o mmu n ic a tio n s .

The

-AGC

i s

u s e d m o r e e x ten sive lx . th a n th e IUU , h o we v e r ,

i t

will

I\

hen

t h e

In i t ia l pos i t ion and a t t i tude in format ion a s we l l a s pe r iod ic upda t ing o i

t h i s in fo rma t io n i s made th rough use of the op t ics .

by the nav iga 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 ig h t ing s a r e ma d e b y a cq u i r in g th e s t a r - l a n d ma rk w ith the S CT a n d l o r S XT .

When the v iewed ob jec t i s cen te r ed ,

a ma rk c o mma n d i s in i t ia t e d. T h e

-AGC

r e a d s th e o p t i c s a n g le s ,

11 , lU

a n g l e s ,

and t i me , in conjunc tion wi th in te rna l

p ro g ra m s , to d e te rmin e th e s p a c e c r a f t p o s it io n. T h i s p o s i t io n in forma t io n

a n d th e s p a c e c ra f t v e lo c ity a r e u s e d to c o mp u te a n e s t im a te d t r a j e c to ry .

The ac tu a l t ra jec tor : .

i s

c o mp a r e d w i th p re v io u s t r a j e c to r \ . d a ta to g e n e ra te

t he t r a j e ct o r y e r r o r ,

i f

a n y, f o r f u r t h e r r e f e r e n c e . O p t i ca l m e a s u r e m e n t s

a r e a l s o u s e d in a l ign in g th e I X I U t o a s p e c i f ic r e fe re n c e o r i e n ta t io n .

T h i s i s a c c o mp l i s h ed

The

T h e

IM U

( f ig u re 2 . 2 - 2 ) c o n ta ins th r e e i n e r t i a l r a t e in te g ra t in g g y ro s

( I RI Gs ) ,

t h r e e a n g ul a r d i f f er e nt i a ti n g a c c e l e r o m e t e r s ( -ADAS), and th re e

pulsed in tegra t ing pendulous acc e l e r om et e r s (PIP-As) . The IRIGs ,

PIP-As,

and one -ADA a r e mo u n ted o n th e s t a b le p la t fo rm wh ic h is gimbaled to p r o -

v ide th re e d e g re e s o f f r e e d o m.

the middle g imbal .

the I RI Gs and

- l D - A s

in con junc t ion wi th e lec t ron ic s tab i l iza t i on loops .

d isp lac ement of the p la t fo rm

is

sen sed by the IRIGs which produce output

s igna ls repre sen ta t i ve o f the magni tude and d i rec t i on of d i s p la c e me n t .

AD-As s e n s e th e d i s p la c e me n t r a t e a n d pro d u c e o u tp u t r a t e c o n t ro l s ig n a l s

to ma in ta in c o r re c t s t a b i l iz a t io n

loop

c o n t ro l r e s p o n s e .

s igna ls a r e a p p li e d to s e r v o a mp l i f i e r s , wh ich c o n di t io n the s ig n a l s to d r iv e

g imb a l to rq u e mo to rs .

p la t fo rm o r i e n ta t ion by driv in g the g im bals un t i l the l R I G s igna ls a r e nul led .

T h e two re ma in in g -AD.As a re mo u n ted o n

T h e s t a b l e p l a tf o r m i n e r t i a l r e f e r e n c e i s m a i nt a in e d 12)-

-An -

The

The IRIG and -4D.A

T h e g i m b a l to r q u e m o t o r s t he n r e s t o r e the in i t ia l

GUIDANCE AND N.4VIG-4TIOK SYSTEll

2 . 2 - 3

Mis s io n Ba s i c Da te

12

~ O V966 Change Date Pa ge


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A P O L L O

OPE RAT ION S HANDBOOK

SYSTEMS DATA

T h e P IP As a r e o r th o g o n al ly mo u nted a nd s e n s e c h a n g e s in s p a c e c ra f t

ve loc i ty .

a r e re prese n ta t ive of the magni tude and d i rec t ion of the ve loc ity change.

The ou tpu t s igna ls a re app lied to the ACC which uses the in format ion to

update spa cecra f t ve loc i ty da ta .

wi th respe c t to the in i t ia l space cra f t pos i t ion and t ra j ec tor y ,

enab les the

AGC to p rov ide cur ren t ve loc i ty , pos i t ion , and t ra jec to ry in format ion .

An acce le ra t i on or de ce le r a t io n res u l t s in ou tpu t s igna ls which

Continual updating of velocity in form ation,

The IMU a lso p r ov ides

a

s p a c e s t a b i l i z e d re fe re n c e fo r s p a c e c ra f t

a t t i tude sen s ing and con tro l .

mo n i to r in g th e s p a c e c ra f t a t ti tu de w i th r e fe re n c e to th e s t a b le p la t fo rm.

Re s o lv e r s a re mo u n te d

a t

the g imbal axes to p rovide s ign a ls represe n ta t ive

of the g imbal ang les . Ine r t ia l

CDUs

conta in res o lv ers which repea t the

p la t fo rm a t t i tude .

res o lv er ou tpu t s igna ls wi th the CDU res o lv er s igna l s . If the ang les d i f fe r ,

e r r o r s i gn a ls a r e + g e n e r a t edand applied to the s tabil i zation and control s y s -

t e m .

If

t h e a t ti tud e e r r o r i s l a rg e r th a n th e s e le c te d d ea d ba nd l imi t s , t he

SCS f i r e s th e a p p r o p r ia t e RCS en g in e s.

T h e s p a c e c ra f t is rota ted back to

th e in i t i al r e fe re n c e a t t i tud e an d th e e r r o r s ig n a l s a r e n u l le d (w i th in

deadband

l imi ts) .

Attitude change sensing i s accomp lished by

Atti tude monitoring is afforded by compar ing the

I X l U

The AGC prov ides au tomat ic execu t ion of comput e r p rog ram s , au to-

mat ic con tro l o f

ISS

and

OSS

mo des , and, in conjunction with the DSKYs,

man ual cont rol of ISS and O S S modes and compute r d isp lays .

con ta ins

a

two-pa r t m em or y which cons i s ts of a la rg e non-e rasab le sec t ion

and

a

s m a l l e r e r a s a b l e s e c ti o n .

a n d s y s te m p ro g ra ms a nd o th e r p re d e te rm in e d d a ta which a r e w i re d in

d u r in g a s s e mb ly .

Da ta r e a d o u t f ro m th i s s e c t io n

i s

non-des t ruc t ive and

cannot be changed during operatio n.

v id e s fo r d a ta s to ra g e , r e t r i e v a l , a nd o p e ra t io n s up on me a s u r e d d a ta a n d

te le m e te re d in fo rma t io n . Da ta r e a d o ut f ro m th i s s e c tio n i s d e s t ru c t iv e ,

p e rmi t t in g c h a n g e s in s to re d d a ta to be ma d e a s d e s i re d .

wi th in the m em or y m ay be ca l led up fo r d isp lay on the two DSKYs. T h e

DSKYs enab le the f l ight c re w to en t e r d a ta or ins t ruc t ions in to the AGC,

requ es t d isp lay of da ta f rom .4GC m em or y , and offe r an in te rru p t con tro l

of AGC operation.

v a r io u s f r e q u e n c ie s fo r in t e rn a l u s e a nd to o th e r o n b o a rd s y s t e ms wh ic h

r e q u i r e a c c u r a t e or synchron ized t iming . Da ta wi th in the AGC i s t ra ns -

mi t t e d to

,MSFN

th rough a "downl ink" te le metr y func t ion. Te le mete red

d a t a i s t r a n s m i t t e d a s

a

function of an AGC pr og ra m or

b y

r e q u e s t f r o m

LMSFN.

function controlled by M S F N . The XGC performs guidance functions b y

e x ec u ti n g in t e r n a l p r o g r a m s u s in g p r e d e t e r m i n e d t r a j e c to r y p a r a m e t e r s ,

a t t i tud e a n g les f ro m th e in e r t i a l CDUs , v e lo c ity c h a n g es f ro m th e

PIPAs,

a n d c o mma n d s f ro m the DSKYs (c re w ) to g e n e ra te c o n t ro l c o mma n d s .

T h e n a vig at ion fu n c t io n i s p e r fo rme d b y u s ing s t o re d s t a r - l a n d m a rk d a ta ,

op t ics ang les f r om the op t ics CDUs, and ve loc i ty changes f ro m the PIPAS

in the execu t ion of nav iga tion pr ogr am s .

The -4GC

No n -e ra s a b le m e mo r y c o n ta in s mis s io n

T h e e ra s a b le s e c t ion of me mo r y p ro -

Informat ion

The

AGC

t iming sec t ion prov ides t iming s igna ls of

Data within the ACC ma y be updated through a n "uplink" telemetr:;

GUIDANCE AND NAV IGATIaG. SYSTE M

..

2 .

2 - 4

' r . . .

. ..-

Miss ion Bas i c Da te l 2 1966 Change

DatB

'

'

P a g e

\


58/849

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

I

VISUAL

%E: 4 4 -

UNDMARKS

A N D H O R I ZON

I X U N N I O N

NOTES: I . AGC inpuh a d utpub

s h o r n

are

pment

at var iRn

t imes,

depcd i np

upan m o de

of opemtion, but

not

concurrently.

2. There capon enh a re

php ica l ly

mounted om

the

I M U

but

i l l v r t m t e d

a hown for

c l a r i t y .

MANUALiMODE S IGNAU

I

RUNNION

DRIVE

S C A N N I N G

TELESCOPE

AND SEXTANT

COUPLlNG

DISPUY

I

UNIT TRU NNIO N DRIVE SIGNALS

SHAFT

I

A

SHAFT CRIVE SIGNALC

I

OUPLING

SHAFT

DRIVE DlSPuy

SIGNAL UNlT

(*) AND

(-)

X

A V E L O C l l Y

1

DRNE I UPLINK DATA FROM MSFN

1 Y G T A L

- -

DRIVE SIGNAL

ATTITUDE

IMPULSE

CONTROL

THRUST C O W M S

TO REACTION

CONTROL SYSTEM

I

M O L L 0

GUIDANCE

COMPUTER

I

P

M

O

M

O

+


59/849

IMU INNER GIMBAL

c

ANALOG

CONVERTER

INNER GIMB4L

RESOLVER SIGNAL

I

GIMBAL INNER IMBAL DIFFERENCE

POSITION COUPLING SIGNAL

UNIT

'OMMANE

D I S P U Y

1

ANGLE SIGNALS

CRIVE SIGNAL"

FROM

MSFN

-

D l S P U Y A N D COMMANDS

EYBOARD

(2 LOCATIONS)

L * MO D E S I G N A U

-

ANGLE SIGNALS

I

DRIVE SIGNALS

($ A N D (-) Y

AVELOCITY

I

(*)

A N D (-)X

AVELOC ITY

I

M O L L 0

GUIDANCE

COMPUTER

' O S I T I O N C O M M A M S .

4

IMU/CDU

I I

1

1

TO NNER

SHAFT ANGLE

G I M M L

I J

C O A E E

ALIGN.

.

Y-IRI G TORQUE AM P

Y-IWG TORQUE

CALIBRATION GENERATOR

A U G N M OD E

-

N L Y )

M ID DL E G I W A L

RESOLVER SIGNAL

I

U/CD U

AU MIDDLE G IMBAL

' COMMANDS--

I I

i 1

I TO

MIDDLE

SHAFT

ANGLE

G l M M L C OA RS

Z-IRIG TORQUE

A L I G N N A P

Z-IRIG TORQUE

GENERATOR TO

OUTER

GIMBAL COARS

COMMANDS

(IS5 FINE

A L I G N M O DE

O N L Y )

-

MU OUTER GIMBAL

QSlTlON COMMANDS I

A U G N

AMP

OUTER G lM M L

RESOLVER SIGNAL

-I

Y A W ~ I T C H

RESOLVER

(GIMBAL

A X E S TO

N A V

BASE

A X E S )

3T FIXED

RESOLVER

( N A V

EASE AXES

TO S/C

AXES)

S/C BO

AN D O

ATTITUD

OFFSE

ATTITU

S/C

BO

ERROR

)

S/C W D

ATTITUD

(

M

DISPLAY SIGNAL

16X-OFFSET

ROLL ERROR S IG N

1 b SHAFT ANGLE J

D O W

N L IN K

TO

MSFN

+ ATA

TERNARY

SWITCH AN D X-IRIG TORQUE

X-IRIG

TORQUE

CALIBRATION GENERATOU

COMMANDS

(ISS FINE

A U G N M O D E O N L Y)

I

SPS E N G I N E ON/OFF COMMANDS

1


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PITCH A

M)DY PITCH ATTITUDE I , ORREC

ERROR

SIGNAL

I

I

I

1

1

I

I

FUNCTIONS

OF

INNER

AND MICDLE GlMeALS)

I

I

YAW I

I

I

i

E R R C X SIGNAL

E C A

I A

I I

BODY YAW ATTITWE

I

I

IGNU

(FUNCTIONS

OF INNER,

MIDDLE, AN D OUTER

GIMALS)

BE

4

SIGNALS

fAW ATTITUDE

CORRECTION

SIGNALS

REACTION

C O M R O L

SYSTEM

t

STABLE

MEMBER

I l h l h I C D

r,....,,

S

O

GI

GIMWL

RESOLVER

ANGLE SIGNAL TO

FLIGHT DIRECTOR

All ITUDE INDICATOR

MIDDLE

G I h U A L q

SIGNALS

TCH GIMBAL

O M M A N C S

1

YAW GIM BAL SERVICE

PROPULSION

SYSTEM

OMMANDS

THRUST ON/OFF

I

AUXILIARY

C 0 M M A N s

I

I

ECA

-I

(+) AND (-) 2

(+)

AND

(-1

X

(+) A N D (-) Y

VELOCITY CHAIGE SIGNALS

VELOCITY CHANGE SIGNALS

VELOCITY CHANGE SIGNALS

*


61/849

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AP OL L O OPERATIONS HANDBOOK

YSTEMS DATA

I

TORQUE MOTOR

DRIVE SIGNAL

I

Figure2.

2 - 2 .

G & N Sys tem Functional Block Diagram

GUIDANCE AND NAVIGATION

SYSTEM

Basic Date'

.

l 2 1966 Change Date

page2 . 2 - 5 1 2 . 2

M is s ion


62/849

S M

2 A -0 3

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SYS TEM S D.4T-4

T h e o p t ic s p rov ide a c c u ra te s t a r a n d l a n d ma rk a n g ula r me a s u re -

Sightings a r e acc ompli shed by the nav iga tor us ing the SXT ande n t s .

SCT.

h an d c o n t ro l l e r o r ma n u al ly u s in g a u n iv e r s a l to o l , a s d e s 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 60 -deg ree fie 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 u s e .

provi des 28-power mag nific ation with a

1.

8-d egr ee fie l d of view.

SXT has two lines of s ig ht, enabl ing i t to me as ur e the included angle

be tween two ob jec ts . Th is re qu ire s two l ines of s igh t which enab le the

two v iewe d o b je c t s to b e s u p e r imp o s e d . F o r a s t a r - l a n d m a r k s i gh t i ng ,

the landm ark l ine o f s ight i s c en te red a long the

SXT

s h a f t a x i s .

imag e is moved toward the lan dma rk by ro ta t ing the shaf t and t runnion

axes un t i l the two v iewed ob jec t s a re s uper im posed . The shaf t and

trunnion ang les a r e repea te d by the op t ic CDUs. When the nav iga tor i s

sa t i s f ie d wi th image pos i t ion s , he is su es a ma rk com mand to the -4GC.

The -4GC reads the optics C D U a n g le s , I M U CDU angles , and t im e , and

compu tes the pos i t ion of the spa cecra f t .

o n s to re d s t a r a n d l a n d ma rk d a ta which ma y a l s o b e u s e d by the .AGC to

re q u e s t s p e c i f i c s t a r s o r l a n d m a rk s fo r n av iga t io n al s ig h t in g s . T wo o r

m o r e s i gh t i ng s ,

o n t wo o r m o r e d i f f er e n t s t a r s , m u s t b e t a k en t o p e r f o r m

a comple te posi t ion de te rm ina t io n .

The op t ics a r e pos it ioned by dr ive mot ors comm anded by the op t ics

The shaft

T ru n n io n a x e s ma y b e o p e ra te d in p a ra l l e l o r o f f s e t ,

T h e S CT

is

a unity power ins t r ume nt prov iding an approx i-

I t i s u s e d to ma k e l a n d ma rk s ig h t ing s a nd

The SXT

The

T h e s t a r

The AGC bases the computation

2 . 2 . 2 . 1

Opera t iona l Modes .

T h e G&N s y s t e m i s o p e ra te d in s ix b a s ic o p e ra t io n a l mo d e s .

Selec tion of any one mode i s acco mp lish ed manual y

b y

the f light c re w or

au tomat ica l ly

by

the ACC.

T h e b a s ic mo d e s a r e a s fo llows:

0

0 Zer o encode

0

Co a rs e a l ig n

0 F in e a l ig n

0

Attitude control

0 E n t r y

The s ys t em conf igura t i on nec ess a r y to opera te in an)- of the modes i s

Xlonitor ( init i a ted by S C S mode se lec t ion)

es tab l i shed by re lay swi tch ing .

The moni to r mode i s used a t launch, a sce n t , and dur ing orb i t un ti l

CSM / S- I VB s e p a ra t io n , to p ro v id e f lig h t pa th d a ta fo r c re w d i s p la y s .

c o a r s e a l ig n , f in e a l ig n , a n d z e r o e nc o de mo d e s a r e u s e d to

a l ign the

I X l U

af te r s tandby per io ds o r to acquir e a new s tab le p la t fo rm

orien ta t ion . The a t t i tude con tro l mode prov i des fo r spacec ra f t a t t i tude

contr o l and nav iga t ion computa t ions to me asu re pos it ion and ve loc i ty .

e n t ry mo d e p ro v id e s c o n t r o l of th e s p a c e c ra f t l i f t v e c to r d u r in g e n t ry

p h a s e .

The

The

C U

I

D

A N

CE 4 N D N AV I

G

=Z TION S YS T E

11

Miss ion Bas ic Da te l 2 Nov l966 Change Date Pag e

2 . 2 - 7


63/849

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SYSTEMS DATA

The ISS and CSS wi l l be op e ra t ed i n on -s t andby cyc l e s t o conse rve

The OSS is sh ut off

e l e c t r i c a l p o w e r.

a tu r e , and t he CSS main ta ins AGC t iming func t ions .

when not in use .

subsys t ems , s t andby

i s

no t cons ide r ed a s ba s i c mode .

Dur ing s tandby opera t ion , the

ISS

main t a in s IMU t empe r

-

Since s t andby ope ra t i on t ime va r i e s f o r e a ch of t he

2 . 2 . 2 .

1. 1 Moni tor Mode ,

Dur ing p r e l aunch ope ra t i ons , t he

G & N

s y s t e m

i s

a l i gned t o t he de s i r e d

l aunch r e f e r en ce a t t i t ude and gy ro com pas se s t o m: in ta in th i s a t t i tude .

Approx ima te ly 3 m i n u t e s p r i o r t o l aunch , t he gy r o compass ing i s s t opped

a 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 igh t pa th angles by dr iv in g the Ine r t ia l Coupl ing Disp lay

Uni t s ( ICDUs) through p rog ra mm ed a t t i tude changes .

com pare d wi th t he

IMU

g imba l ang l e s t o p roduce f l ight pa th e r r o r s i gna l s

wh ich a r e d i sp l ayed by t he FDAI e r r o r need l e s .

w i th r e spe c t t o t he

IMU

or i en t a t i on , i s disp layed by the FDAI ba l l .

(P r e l au nch FDAI r ead ings

a r e

164. 76-degree ro l l , 58 .3 0-deg ree p i tch , and

9. 69-d egree yaw, wi th res pe c t to the navigat ion ax i 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,

a s sum ing a 180 -deg ree 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 i o r t o l aunch e scape t ower (L ET ) e t t i son , t he AGC d i sp lays

the fol lowing:

Upon lift-off the ACC beg ins

The ICDU angles a re

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 igh t pa th angle ; iner t ia l ve loc ity wi th re spe c t

t 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 ity 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 i gna 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 rad ius

in

NMs.

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

r ad iu s i n minu t e s and s econds .

This d i sp laye d da ta provid es the f l igh t c rew wi th suf f ic ien t in format ion to

make ab o r t o r con ti nue dec i s i ons ; howeve r ,

i f

t ime

i s

not c r i t i ca l , the

dec is ion

Documents

Ap Operations Handbook CSM SC 012 1966.pdf