apollo description manual for boilerplate 15

8/3/2019 Apollo Description Manual for Boilerplate 15

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57295 -64Accession No. --______

SM2A-07-BP15

C d at 3 year intervals; declassified afte r 12 years; DOD DI R 5200.10. .r .

PUBLISHED UNDER AUTHORITY OF THE N A T I ON A L A ER ON A U TI C S A N D SPA CE A D M I N I ST R A T I ON

SI D 6 3 . 1 4 4 2 6 APRIL 1964

NASASUPPORT MANUAL

APOLLODESCRIPTION MANUAL

FOR1 ' :BOILERPLATE 15 A ' d

C O N T R A C T N A S 9-150EXHIBIT I; P A R A G R A P H 10.3

4 -THIS MANUAL REPLACES SM2A-07-BP15 DATED 30 NOVEMBER 1963


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cSM2A-07 -BP1 5

NOTE: The port ion of the text affected by the changes is indicatedby a vertical line in the outer margins of the page.LIST OF EFFECTIVE PAGES-TO TAL NUMBER OF PAGES IN THIS PUBL ICATION IS 92,CONSISTING O F THE FOLLOWING:P a g e No.T it leAi t h r u i v1 - 1 t h r u 1 -42 - 1 t h r u 2 - 223 -1 t h r u 3-104 - 1 t h r u 4-245-1 th r u 5 -66-1 t h r u 6-27 - 1 t h r u 7 -68 - 1 t h r u 8 -1 2

*The asterisk indicates pages changed, added, or deleted by the current change.

Manuals wi l l be distributed OS directed by the NASA Apollo,Project Office. A l l requests formanuals should be directed t o the NASA Ap oll o Spacecraft Project O ff ic e at Houston, Texas.

A


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Sect ion

I

I1

111

TABLE O F CONTENTS

Ti t l e P a g eINTRODUCTION . . . ivMISSION AND OBJECTIVES . . 1-11-1 . Purpose . 1 -11-3. Boi l e rp l a t e 15 M iss ion . . 1 -11 -5 . F i r s t O r d e r T e s t O b je c ti v es . . 1 - 11-7. Second Ord er Te s t Object ives . . 1 -1PHYSICAL D ESCRIPTION . . 2 -12-1.2-3.2-5.2-7.2-9.2-11.2-13.2-15.2-17.2-19.2-21.2-23.2-25.2-32.2-36.2-40.2-46.2-50.2 -52.

2-27.

2-38.

2-48.

P u r p o s e . .L a u n c h E s c a p e A s s e m bl y .S t r u c t u r e .M otor sE lec t r i ca l and E lec t ron i c Component sSequencer s .Hot W i r e In i t i a to r s .Umbi l i ca l Connec tor s .Command M odule .S t r u c t u r e .F o r w a r d H e a t S h ie ld .Aft Heat Shield .I n t e r i o rServ i c e M odule, Inse r t , and Adapte rS t r u c t u r e .In t e r f ace Equipment .T e n s i o n T i e s . .Umbi l i ca l Connec tor s .Launch Vehicle .F ir s t S t ageBoos t e r Ins t rume nt Unit .econd S tage . .

2-12-12-22-82 -82-82-2 -2 -2 -2 -2-1

2-12-12-22-22-22-22 -22 -22 -22-2

LAUNCH ESCAPE SYSTEM . . 3-3-1.3-3.3-5.3-7.3-9.3-11.3-13.3-15.3-17.

P u r p o s eOpera t i ona l Desc r ip t ion .Motor Igni t ion .Tower Separa t i on .L a u n ch E s c a p e M o t o r .P i t c h Cont ro l M otor .L a u n c h E s c a p e T o w e r J e t t i s o nM iss ion Sequencer .Tower Sequencer s . M otor

. 3-. 3-. 3-. 3-. 3-. 3-. 3-. 3 -. 3-


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SM2A -07 -B P 15S e c t i o n

IVT i t l e P a g e

COMMUNICATIONS AND INSTRUMENTATION . . 4 - 1

v

VI

VI1

V I I I

4-1 . Purpose . 4 - 14-3 . Desc r ip t ion . . 4 -14-4 . Communica t ions Equ ipm ent . . 4 - 14-11. Ins t rum enta t ion Equ ipm ent . . 4 - 3EQUIPMENT COOLING SYSTEM . 5-15-1 . Purpose . 5-15-3 . Sys tem Des cr ip t ion . . 5-15-5 . P r inc ip les of Op e r a t i o n . . 5-1ELECTRICA L POWER SYSTEM . . 6-16-1 , Purpose . . 6-16 - 3 . Sys tem Equipment . . 6-16-5 . P r inc ip les of Op e r a t i o n . . 6 - 16-9. Pow er Consumption . . 6-1DOCUMENTATION AND SUPPORTING EQUIPMEN T . . 7 - 17-1 . Purpose . 7 - 17-3. Documentation . . 7 - 17-5. Support ing Equipment . . 7 - 3ELECTRICAL SCHEMATICS . 8-18-1 . Purpose . 8 - 18-3 . Schem at ic Diag ram s . . 8 - 1

LIST O F ILLUSTRATIONS

F i g u r e No. T i t l e P a g e1-1.1-2.2-1.2 -2 .2-3.2 -4.2-5.2 -6.2-7.2-8.2-9.2-10.2-11.

Boos te r Compat ib il i ty Space Veh icle .F l i g ht S e q u en c e a n d T r a j e c t o r y .L a u n c h E s c a p e As s e m b l yE s c a p e T o we r E x p l o s i v e B o l t .L a u n ch E s c a p e M o t o r a n d S t r u c t u r a l S k i r t A r e a . .L E S I n t e r s t a g e Ad a p t e r Ar e a C o mp o ne n tsNose Cone and P i t ch Cont ro l Motor Are aComm and ModuleC o mma n d Mo d ul e I n t e r i o r .Command Module Refe ren ce Axis .Dumm y Shock S t ru t an d GSE At tach F i t t ingServ ice Module Tens ion T ie .Serv ice Module and A dap te r .

..

.

1 - 21 - 32 -32 - 42-52-62 -7

2-102 - 1 12-162-182 - 1 92 -20


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Figure No. T i t l e Pag3-1.3 -2.3-3.4-1.4-2.4-3.4-4.5-1.5-2.5-3.6-1.8-1.

T a b l e No.2-1.2-2.2-3.3-1.3-2.3-3.4-1.6-1.7-1.7-2.

Launch Escape Sys t em Func t iona l B lock Diag ramM iss ion Sequen cer Schemat i c DiagramTower Sequ encer Schemati c Diagram .R&D Ins t rumenta t i on B lock Diagram .R&D Ins t rumenta t i on Loca tionsQ-Bal l .Q-Bal l B lock Diagram .Equipment Cool ing System. .Equipment Cool ing Sys t em Func t iona l D iag ramEquipment Cool ing Sys t em S impl i f i ed E lec t r i c a l Schemat i cE l e c t r i c a l P o w e r S y s t e m B l oc k D i a g r a m . . . .Boi l e rp l a t e 15 and GS E Hangar Checkout Equipment Combined

.

. .S y s t e m s S c h e m a t i c .

LIST OF TABLES

3-3 -73 -4-4 -

4-14 - 1

5-5 -5 -6-8 -

T i t l e P a gL a u n c h E s c a p e A s s e m b l y P h y s i c a l C h a r a c t e r i s t i c s . . 2 -Command M odule Phys i ca l Charac t e r i s t i c s . 2 -Command M odule Compar tmenta t ion . . 2 -T im e Hi s to ry o f Event s Leading to Tower Je t t i s on . . 3 -

Je t t i son M otor . . . . 3-M iss ion Sequencer Func t ions . 3-Apol lo CM/SM Measurement Lis t . , 4-1B a t t e r y P h y s i c a l C h a r a c t e r i s t i c s . . 6 -Boi l e rp l a t e 15 Supplementa ry Document s . . 7 -Ground Suppor t Equipment . . 7 -Opera t i ona l Char ac t e r i s t i c s o f Launch Escap e Towe r

i


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INTRODUCTION

Thi s manua l pe r t a ins t o t he mi ss io n , and prov ides phys i ca land opera t i ona l desc r ip t i ons of boi l e rp l a t e 15 , pa r t No . B14-000002-201, man ufactu red by Space and Inform at ion Sys tem sDivis ion of North Ame yican Aviat ion, Inc ., Downey, Cal i fo rnia .Suppor t ing do cumen tat ion and ground su ppo r t equipme nt i sd e s c r ib e d i n g e n e r a l t e r m s . F u n c ti o n al s c h e m a t i c s a n d b l oc kd i a g r a m s a r e a l s o i n c l ud e d i n t h i s m a n u a l.of th is manual i s l i s te d in the Index of Apol lo Suppo r t Manualsand P roce dures , SM lA-1 .

The appl icabi l i ty


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SECTION IMISSION AND OBJ EC TIV ES

1- 1. PURPOSE.1-2. Th i s sec t i on de sc r ib es t he mi s s ion and ob jec t i ves of bo i l e rp l a t e 15 ( f i gure 1 -1) . Am i s s i o n p r o fi l e i s shown in f i gure 1 -2 .1-3. BOI LER PLA TE 15 MISSION.1-4.qual i fy compat ibi l i ty of the Apol lo s pac ecr af t wi th the Satu rn I launch vehic lc and to dcf inet h e l a u n c h an d e x i t e n v ir o n m e n ta l p a r a m e t e r s .I boo s t e r f ro m the At l an t i c M iss i l e Range (AM R) a t a l aunch az imuth of 9 0 d e g r e e s f r o mt r u e n o r th .p r o g r a m e d r o l l m a n e u v er .

T h e m i s s i o n p r e s c r i b e d f o r b o i le r p l a te 1 5 i s t h e s e c o n d i n a s e r i e s t o deve lop andThe spa cec ra f t w i ll be l aunched by a S a t u r

A f light azim uth of 105 de gr ee s wi l l be obta ined soon a f t e r l aunch by a

1-5. FIRST ORDER TE ST OBJECTIVES.1-6.pref l ight and f l ight condi t ions .

F i r s t o rd e r t e s t Objec tives of t he bo i l e rp l a t e 15 f l igh t t e s t a r e a s fol lows:a .

b.c .

Dem ons t r a t e t he phys i ca l compat ib i l i t y of t hc l aunch vch ic l e and sp ace cra f t underD e t e r m i n e t h e l a u n ch a nd- e x i t e n v ir o n m e n ta l p a r a m e t e r s t o v e r if y d e s i g n c r i t e r i a .Dem ons t r a t e t he a l t e rna t e mode of l aunch esc ape t ower j e t t i son , us ing the l aunch

e s c a p c a n d p it ch c o n t r o l m o t o r s .1-7. SECOND ORDER TES T OBJECTIVES.1-8 . Second or dc r t c s t ob j ec t i vcs of t hc bo i l e rp l a t e 15 f li ght t e s t a r c a s fol lows:

a.

b.Dem ons t r a t e t hc s t ru c tu ra l i n t egr i ty o f t he l aunch csc; ipc sy s t e m under f l i gh t -l oad inDe mo nst ra te the Compat ibil i ty of the R&D communica t ions and ins t rumenta t i on

condi t ioi i ssy s t em s wi th t he l aunch veh ic l e sy s t em s .

1


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SM2A-07 - B P 1 5

L AU N C H ESC APE SYST EM

C O M M A N D M OD U LE

S-IV S E C O N D S T A G E

S-I/S-IV INTERSTAGE

\-1 FIRST STAGE

S T A T I O N 9 6 2. 30 4

SA

-

JRNL A U N C H V E H I C L E

Figure 1 - 1. Boos t e r Compat ib i l i t y Space V e h i c l eL S M - 2 A - 2 2 9 Dy 1 r S T A T I O N 1.0


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C5

00.

Ln-1

u) 0cv)

NI


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_.._SM2A -07 - B P I 5

SECTION I1PHYSICAL DESCRIPTION

2-1. PURPOSE.2-2. Th i s s e c t i on c on ta i n s a phys i c a l de s c r i p t i on of t he l a unc h e s c a p e s y s t e m , c omma ndmodu l e , s e r v i c e modu l e , i n s e r t , a nd a da p t e r . The bo i l e r p l a t e 15 s pa c e c r a f t , moun te d on aSaturn I l aunch vehic le , c o m p r i s e s t he c o m p l e t e t e s t v e h i c le . ( Se e f i gu r e 1 - 1 . )2 - 3 . LAUNCH ESCA PE ASSEMBLY.2-4.shown in f igure 2-1 .

S t r u c t u r a l r e l a t i ons h i p s a nd phys i c a l l oca t i on of t he c ompone n t s o f t he a s s e m bl y a r eP e r t i n e n t p h y s i ca l c h a r a c t e r i s t i c s a r e c o n ta i ne d i n t ab l e 2 -1 .

Table 2-1. L a un c h E s c a pe A s s e m b l y P h y s i c a l C h a r a c t e r i s t i c sO v e r a l l D i m e n s i o n s:

LengthWeight

T o w e r S t r u c t u r e :LengthWidth (top of t o w e r )Width (bottom of t o w e r )Weight

S t r u c t u r a l S k i r t :LengthD i a m e t e rWeight

La unch Es c a pe M ot o r :LengthD i a m e t e r a t n o z zl e e x i tD i a m e t e r o f m o t o r s t r u c t u r eWeight

T o w e r J e t t i s o n M o t o r :LengthD i a m e t e r a t n o z z l e e x i tD i a m e t e r o f m o t o r s t r u c t u r eWeight

33 feet6600 pounds

118 i nc he s36 inches

50. 6 i nches533 pounds

18.25 inches48 .8 i nc he s

227 pounds (appros )

185. 3 inches28 inches26 inches

4767 pounds (appros)

55 .6 i nc he s28 inches2 6 inche s

529 pounds a p p r o s )

? 2-1


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-SM2A- 07-BP15Table 2-1. Launch Escape Assemb ly Phys i ca l Charac t e r i s t i c s (Cont )P i t ch Co nt ro l M otor S t ruc ture :Length ( inc ludes ba l l a s t and motor s t ruc ture )Diamete rWeight

Pi tch Cont rol Motor :LengthDiameter of bodyDia me ter of f langeWeight

Ba l l as t :Diam eter of lead dis csThicknessWeight

Ba l l as t Enc losure :LengthD i a m e t e r ( f o r w ar d e n d )Diame te r ( a f t end)Weight

Nose Cone (Q-Ball) :LengthDiamete r ( fo rward end)Diame te r ( a f t end)Weight

18.62 inches26 inches

158 pounds (appro x)

22 inches8.79 inches

10.51 inches47 pounds (approx)

20.5 i nches1 .13 inches

189 pounds (ap prox)

29 inches13.1 inches

26 inches73 pounds (approx)

19.09 inches2 inches

13.03 inches35.1 pounds (appro x)2-5. STRUCTURE.2-6.an open f r a me of we lded t i t anium tub ing covered wi th s i l i ca - f i l l ed Buna-N rubber fo r i n su-lat ion.( f igure 2-2) .A s t ruc tura l sk i r t i s a t t ached be tween the t op of t he t ower s t ruc ture and the base o f t hel aunch esca pe motor .t he s t ruc tura l sk i r t and the i n t e r s t age s t ruc ture .we lded cy l indr i ca l s t ruc tu re which houses t he t ower j e t t i son motor exhaus t nozz l es andvar ious e l ec t r i ca l component s .component s .s t ruc ture be tween the i n t e r s t age s t ruc ture and the ba l l a s t hous ing .( f i gure 2-5) and the nose cone (M SFC-furn i shed Q-ba l l ) a r e of we lded Incone l shee t con s t ruc -t io n , a n d a r e b ol te d to g e t h e r t o f o r m a s ingl e con ica l s t ruc ture t o house t he shee t l eadba l l a s t , s e ns or s , and e l ec t ron i c modules i ns t a l led i n t he nose cone (Q-ba ll ) .

A t russ - type t ower s t ruc ture i s t he base of t he l aunch escape as sembly . The tower i sE a c h of the four l egs i s a t t ached to t he comman d module by a n exp los ive bo lt

At tachments a t the to p of eac h tower leg fac i l i ta te tower a l ignment ( f igure 2-3) .The housing of t he l aunch esca pe motor fo rm s a s t ru c tur e be tween

T h e in t e r s t a g e s t r u c t u r e ( f i g u r e 2 - 4 ) i s a

Two ac ce ss doo r s f ac i l i t a t e i ns t a l l a ti on and r emova l of t heThe housing of t he t ower j e t t i son moto r and the p i t ch con t ro l motor fo rm aThe bal las t housing

2 -2


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NOSEMLO N EPITCH CONTROLMOTOR N O Z Z L E 91-TOWER JETTISON

INTERSTAGE\DAPTER\AUN CH ESCAPE MOTOR

ESCAPE TOWER 1

C O MMAN D MO D U L EATTACH FITTINGSA ND SEPARATIONPYROTECHNICS7

MLLASTCOVER

PITCH CONTROLMOTOR

TOWER JETTISONMOTOR N O Z Z L E

REDUNDANTWIRING HARNESS

TOWERSEQUENCERS

STRUCTURAL SKIRT

LAUNCH ESCAPEMOTOR N O Z Z L E

POWER SYSTEMS A N DINSTRUMENTATIONCONNECTORS

Figure 2-1. Launch Esc ape A ssembly

SM- 1A-376A

2 - 3


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F i g u r e 2 - 2 . Es c a pe Towe r Exp l os i ve Bolt

2 -4


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LAUNCHESCAPE MOTOR

STRUCTURALSKIRT

ALIGNMEN T ADJUS

TOWER SEQUENCERS/T-

SM-2A-266A

F i g u r e 2 - 3 . Launch Escape M otor and S t ruc tura l Sk i r t Are a


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AccEsvOOR

\ JETTISON MOTOR

\ - -TERMINALBOARD

SM-4A-6OA

F i g u r e 2-4. LES I n t e r s t a g e A d a p t e r A r e a C o m p o n e n t s

2 -6


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NOSE CONE

QL ALL CONNECTOR

BALLAST HOUSING

SHEET LEAD BALLAST

PITCH CONTRO LMOTOR HOUSING

PITCH CONTROL MOTOR ACCESS DOOR

TERMINAL BOARDTERMINAL BOARD

SM-2A-377

Figure 2 - 5 . Nos e Cone a nd P i t c h Con t r o l M ot o r Ar e a2


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2-7. MOTORS.2-8.p i t ch c o n t r o l mo t o r i s loca ted jus t under the ba l l a s t wi th the m otor nozz le ex tend ing ou twardon a horiz ontal p lane through the pi tch cont rol mo tor housing.1 80 d e g r e e s a p a r t , p e r mi t a c c e s s t o t he h o t w i r e i n i t i a t o r s a nd a s s o c i a t e d wir i n g.j e t t i s o n mo t o r ( f i g u re 2 - 4) i s loca ted jus t be low the p i tch con t ro l motor .ex tend downward th rough the in te r s ta ge a r ea , can ted to ex i t th rough the s t ru c tu r e hous ingjus t above the l aunch escape mo tor fue l t ank . TWOd o o r s p e r mi t a c c e s s t o h o t w i r e i n i t i-a t o r s a nd a s s o c i a t e d wi ri n g in t he j e t t i s o n mo t o r a n d i n t e r s t a g e a d a p t e r a r e a s .e sca pe moto r hous ing ex tends f ro m the j e t t i son moto r nozz les to in te r fa ce wi th the s t r uc -tu r a l sk i r t . (See f igure 2 -3 . ) T h e f o u r l a un c h e s c a p e mo t o r n o z z l e s a r e c a n t e d to t h r u s ta wa y f r o m t h e c o mma n d mo d u le .

T h r e e l a u nc h e s c a p e a s s e m b l y mo t o r s a r e s t a c k e d a bo ve t h e t o we r s t r u c t u r e . T heTwo doo rs , approx imate ly

TheTwo f ixed nozz les

The launch

I g n i t e rs a r e l o c a t e d u n d e r t h e s t r u c t u r a l s k i r t .2 -9 . ELECTRICAL AND ELECTRONIC COMPONENTS.2-10.l a u nc h e s c a p e s e q u e n c e r s , h ot w i r e i n i t i a t o r s , a nd a s s o c i a t e d wi r i n g h a r n e s s e s a nd a t t a c h -me nts . Two logic and two pyro ba t te r ie s , located in the com man d module , supply power toope ra te the launch escape assemb ly .t h e l au nc h e s c a p e mo t o r , a n d a s s o c i a t e d r e d u nd a n t h a r n e s s e s a r e i n t e g r a l to t he t o we rs t r u c t u r e . E a c h t o w e r s t r u c t u r e h a r n e s s h a s a breakaway p lug tha t a llows the ha rn es s tode tach f rom the command module when the l aunch esca pe tower i s j e t t i soned . The wi r inghar nes ses p rov ide means fo r connect ing the rocke t motor and sep ara t ion c i rc u i t s wi th thesequence con t ro l l e r s , and the ins t rume nta t ion componen ts wi th the comm unica t ionse quipme nt.

T h e e l e c t r i c a l a n d e l e c t r o n i c c o mpo n en t s i n t h e l a u nc h e s c a p e a s s e mb l y c o n s i s t of

Redundan t wi r ing ha r ne sse s , bonded to the ex t e r i o r of

2-11. SEQUENCERS.2-12. Thre e sequen cers a r e prov ided to p rog ram the sequenc e of even t s du r ing the miss i on .T wo t o we r s e q u e n c e r s ( f i g u re 2 - 3 ) , l o c at e d on th e s t r u c t u r a l s k i r t , a r e i d e n t i c a l i n s i z e a n dshape . Each tower sequcnccr i s approx imate ly 2.5 inches in width, 8 .25 inches deep , and3 . 75 inches high. A mi s s i o n s e q u e n c e r i s in s ta l l ed in the com man d module and i s a s ing le -enc losed assem bly approx imate ly 15 inches wide , 8 .25 inches deep , and 7 inche s high.2-13 . HOT WIRE INITIATORS.2-14.plug devices .de tona te the motor ign i te r s .inch f rom the th readed end.the o the r end.pendent b ridg e w i r e c i r cui t s .

T he t wo ho t w i r e i n i t i a t o r s ( f i g u r e 2 - 4 ) f o r t h e t o we r j e t t i s o n mo t o r a r e t h r e a d e dBoth in i t i a to r s con tain the e lec t r i c a l c i rcu i t ry and exp los ives ne ces sa r y to

The in i t ia tor body is 1 inch long with a 0. 75-inch f lange, 0 .45T h r e a d s a r c l o c a t e d o n one e nd a n d a n e l e c t r i c a l c o n n e c t or a t

The e lec t r i ca l connec to r con ta ins four p ins to supp ly power to two inde-

2 - 15. UMB ILICAL CONNECTO RS.2-16.asse mb ly and the command module .separa t ion ad jacen t to the escape tower l eg we l l s of the fo rw ard hea t sh ie ld of the commandmodule . The recep tac le por t ion of the connector i s a t t a c h e d t o t h e c o mma n d mo d ul e s t r u c -t u r e . When the es cap e towersep ara tes f ro m the command module , the l anyard pu l l s the p lug f rom the recep tac le .p l ug s a r e p a r t of the l aunch esca pe tower w i r ing ins ta l l a t ion and separ a te wi th the tower .The recep ta c les a r e pa r t of the comm and module wi r ing ins ta l l a t ion and rem ai n wi th thecomm and module.

Two e lec t r i ca l umbi l i ca l connec to r s join the e le c t r i ca l sys te ms of the l aunch esca peT h e s e c o n n e c t o r s a r e loca ted on the p lane-o f -

The plug is a t t ached to the n ea r es t tower l eg by a l anyard .The

2-8


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2-17. COMMAND MODULE. (See f ig ure s 2-6 and 2-7. )2-18.e x t e r n a l s i z e a n d s h a pe .table 2-2.

The bo i l e rp l a t e comm and module s imula t e s the p roduc t ion co mma nd module i nP h y s i c a l c h a r a c t e r i s t i c s f o r th e c o m m a n d m o du l e a r e l i s t e d i n

T h e r e f e r e n c e a x e s a r e s ho wn i n f i g u r e 2 -8 .Table 2-2. C o m m a n d M o du le P h y s i c a l C h a r a c t e r i s t i c s

Shape Conica1Heigh t 134 inchesD i a m e t e r 154 i n c h e sWeight 9262 pounds

2-19. STRUCTURE.2-20.T h e s i d e s a r e s e m i m o n o c o q ue a l u m in u m s t r u c t u r e s a n d t e r m i n a t e i n t h e f o r w a r d a n d afth e a t s h i e l d s .s t r u c t u r e a g a i n s t a e r o d y n a m i c h ea t in g .p e r m i t s a c c e s s to t he i n t e r i o r.p rov i s ions f o r equ ipment.

The command module s t r uc t ure i s con ica l w i th a convex base and a rounded apex.The comm and module i s covered wi th a c o r k m a t e r i a l to p r o t e c t t he a l u m i n u m

A m a i n h a tc h i n th e s i d e of t h e p r i m a r y s t r u c t u r eShe lves and brack e t s a long the i nner w a l l a f fo rd mountingCompar tmenta t i on i s des c r ibe d in t ab l e 2 -3 .

Table 2-3. Comman d Module Com par tm enta t ion

C o m p a r t m e n tP r i m a r y s t r u c t u r e

F o r w a r d c o m p a r tm e n t

A f t c o m p a r t m e n t

I

Product ion Conf igurat ionFunct ion

C r e w c o m p a r t m e n t .

Houses pa rachute sys t emo f E L S, r e a c t io n t h r u s t e t s ,and as soc i a t ed equ ipment.Houses dummy shock s t ru t s ,e n v i r o n m e n t a l c o n t r o ls y s t e m s t o r a g e f a c i li t i e s,a n d C / M t o S / M u m b i l i c a l s .

Boi l e rp l a t e 15 ContentsL a u nc h e s c a p e t o w e r s e q u e n c e r , R & Dcommunica t ions and ins t rumenta t i on ,ba l l a s t t o s imula t e we igh t and cen t e rof gravity, e g r e s s t ub e t o s i m u l a t eproduc t ion t ube vo lume and ma in ha t chand R&D cool ing sys t em .R a d om e a n d t e l e m e t r y a n t e n n a ,

Aft hea t sh i e ld a t t achme nt f i t t i ngs ,GSE a t t ach f i tt i ngs , umbi l i ca l connec-t o r s , e q u i pm e n t a c c e s s d o o r s , s e r vi c emodule mat ing bea r ing pads , andtens ion t ies .

2-21. FORWARD HEAT SHIELD.2-22.s h e e t m e t a l c o v e r a n d a f i b e r g l a s s h o n ey c o m b r a d o m e a s s e m b l e d t o g e t h e r w it h th e a s s e m b l ybol t ed t o t he comm and module .sh i e ld , s i nce r ecov ery i s no t p l anned.

The fo rw ard hea t sh i e ld fo r m s the apex of t he com mand module.T h e r e a r e no p r o v i s i o n s f o r s e p a r a t i n g th e f o r w a r d h e a t

I t co nsi s t s of a

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W-24-235D

F i g u r e 2-6. Comm and Module

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F i g u r e 2 - 7 . Command Modu le In t e r io r (Shee t 1 of 5 )2-11


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CALORIMETER

CALORIMETER

HEAT EXCHANGER

-\--A-

TERMINAL BOARDTRANSDUCER

SM- 2A - 2050

Fi gu r e 2-7. Command Module In te r ior (Shee t 2 of 5)

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DC AMPLIFIER RACK

S IG N A L C O N D I T I O N I N G P K G

DC AMPLIFIER RACK

TERMINAL BOA

1090 TEMPERATURE SYSTEM BOXC O M M U T A T O R

TERMINAL BOARDT/M MULTIPLEXER

TRANSPONDERS

T/M MULTIPLEXER

TERMINAL BOARD

TERMINAL BOARDT/M M O D U L A T O RW I T H C O M M U T A T O R

PYRO BATTERY

TERMINAL BOARDL O G IC BAT T ERY

T E W I N A L B OA RD

L O G IC BAT T ERY

SM-2A-286D

Fig ure 2 -7 . Command Module In te r io r (Shee t 3 of 5)

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L

V I E W 0

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F i g u r e 2 - 7 . Command Module In te r io r (Shee t 4 of 5 )


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C/M TO

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-Y

+zI

I m I - Y

- 2V I E W ON X A X I S

- +x

. M A I NHATCH

+X

2-16

I-X

V IEW ON Z A X I S

I- X

V I E W ON Y A X I S

SM-2A - 2808

Figure 2-8. Command Module Ref e ren ce A x i s


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2-23. A FT HEAT SHIELD.2-24.of a luminum honeycomb bonded to the i nner and ou t e r sk ins of t he l a mina t ed f i be rg l a s s .T h r e e a d j u st a b le s t r u t s ( d u m m y s h oc k s t r u t s ) a n d o ne t e n s i o n ti e j o i n t he a f t h e a t s h i el d t ot he c o m m a n d m o d u le b a s i c s t r u c t u r e . (See f igure 2 - 9 . ) Two ho les a r e p rov ided in t hesh i e ld fo r i ns t a l la t i on o f t he umb i l i ca l e l e c t r i c a l connec tor s . N ine ho l es a r e p rov ided top e r m i t a t t a c h m e n t of t h e s e r v i c e m o du le t o t he c o m m a n d m o d u l e s t r u c t u r e .a r e f o r t he comman d module bea r ing po in ts ; the o th e r t h ree a r e fo r t he t ens ion- t i e bo l t s .(See f igure 2 -10 . )

The a f t h e a t s h i e ld f o r m s the convex ba se o f t he com mand module . It i s cons t ruc t ed

Six of the h ol es

2-25. INTERIOR.2 - 2 6 .bra cke t s fo r mounting the e l e c t r i ca l power, R&D ins t rum enta t i o n , and equ ipment cool ings y s t e m s . ( Se e f i g ur e 2 - 7 . )q u i lt e d f i b e r g l a s s m a t e r i a l .a tu re of no t g re a t e r t han 150 deg ree s Fah renh e i t and to r ed uce t he &ea t f low ins ide t hec o m p a r t m e n t .

T h e i n t e r i o r ( c r e w c o m p a r t m e n t ) a r e a of t h e c o m m a n d m o du l e c o n t a i n s s h e l v e s a n dT he i n t e r i o r a r e a i s i nsu l a t ed f ro m the s ide wa l l s w i th aThe insu l a ti on he lps t o p rov ide and main t a in a c ons t an t t em pe r

2-27. SERVICE MODULE, INSERT, AND ADAPTE R. (See f ig ur e 2-11. )2-28.p r i m a r i l y t o t r a n s m i t l o a d s f r o m t h e l a un c h v e h i cl e t o th e s p a c e c r a f t .m o d u l e s r e s t s o n t he s e r v i c e m o d u l e a t s i x c o m p r e s s i o n b e a r i n g p o in ts .bo l t s ho ld the comm and module mat ing bea r ing po in t s f i rm ly sea t ed .a r e ad jus t ed t o f ac il i t a te co mman d module - t o - se r v i ce module a l i gnmen t .s t i -uctural fa i r ing is l oca t ed be tween the comm and module and the se r v i c e module . Thefa i r i ng hous es a non-funct ion ing sepa ra t i on mec hani s m, a sup por t s t ru c tu re fo r d i s t r ibu t ingba s i c l o ads imposed by the com mand module to the se rv i ce module , and f ixed umbi l i ca lconnect ions between the two mod ules . The com man d module and ser vi ce module wi ll not bes e p a r a t e d d u r i n g t he m i s s i o n ; a n d , t h e r e f o r e , n o p y r o t e c h n i c s a r e i n s ta l le d . T h e s e r v i c em o d u l e - t o - i n s e r t a n d i n s e r t - t o - a d a p t e r i n t e r f a c e s a r e j oi n ed w i th 2 4 b o l ts e a ch .ada p te r i s bo lt ed t o t he i n s t ru me nt un i t us ing 32 bo lt s .cadm ium p la t ed t o p rov ide e l e c t r i c a l bonding .

The se rv i c e module i nc ludes t he i ns e r t and i s used i n the bo i l e rp l a t e 15 conf igura ti onThe command

Thre e t ens ion- t ieThe s i x bea r ing bo l t s

An ex t e r io r non-

Th eThe ho les fo r t hese 32 bo l t s a r e

2-29.l i s t e d a s fol lows:

A p a r t of t h e s p a c e c r a f t in s t r u m e n t a ti o n s y s t e m i s l o c a t e d i n th e s e r v i c e m o d u l e ,

Ser vic e module (between s ta t ions 1785.596 and 1661.596, f i g u r e 1-1)S ev en c a l o r i m e t e r sT wo s t r a i n g a g e sEleven f luctuat ing p r e s s ~ r e r a n s d u c e r sT h r e e v i b r a ti o n t r a n s d u c e r sTwo a c c e l e r o m e t e r sOne acous t i ca l - sens ing dev ice .

Adap ter (betwe en stat ion s 1609.596 and 1517. 596, f ig ure 1- 1 )F o u r s t r a i n g a g esO n e c a l o r i m e t e rT wo v i br a t io n t r a n s d u c e r sTwo f l u c t u a t i n g p r e s s u r e t r a n s d u c e r s .

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HEAT SHIELDMOUNTING STRUTS

YSE FITTINGSM- 2A- 10 2 A

Figure 2 -9 . Dummy Shock S t ru t and GSE Attach Fi t t ing


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S/M TENSION TI EATTACH FITTINGSM-2A-230

F i g u r e 2-10. Serv ice Module Ten s ion Tie

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LONGERONS/- (6 PLACES)

SERVICE

C-BANDAN T ENNA S(4 PLACES)

C

S/M TO I N S E R TCONNECTORS7LONGERONS(6 PLACES)

STRINGERS(28 PLACES)-INSERT1ADAPTER1

PRESSURE VENT HOLES(e PLACES)

b

< EACTION CONTROLMOTORS (4 PLACES)(SIMULATED)

- ONGERONS(6 PLACES)-STRINGERS(28 PLACES)-ADAPTER TO

BOOSTERINSTRUMENTUNIT CONNECTORS

-Y-zaZ y AIR CONDITIONINGBARRIERF i g u r e 2-11. Servi ce Module and Adap ter


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2-30.of gravi ty of the spa ce cr af t .p l ace on the s e rv i ce module t o s im ula t e ex t e rn a l conf igura t ion .

B a l l a s t i s i ns t a l l e d i n t he se rv i ce module and adap te r t o s imu la t e weight and cen t e rF i b e r g l a s s r e a c t i o n c o n t r o l s y s t e m n o z z l e s a r e m o u n te d i n

2-31.i n a d d i ti o n t o t he i n s t r u m e n t a t i o n ( p a r a g r a p h 2-29). T h e a i r - c o n d i ti o n i n g b a r r i e r c o n s i s t sof a double la ye r of nylon c loth impreg nate d on both s id es wi th a c h l o r o p r en e r u b b e r c o m -pound.

The adap te r c on ta ins Apol lo -Sa turn i n t e r f ace wi r ing and an ai r -condi ti on ing ba r r i e r

T he b a r r i e r f o r m s a b u lk h ea d a t the e x t r e m e aft end of the ada pte r .2-32. STRUCTURE.2-33 . The se rv i ce modu le , i ns e r t , and adap te r a r e cy l indr i ca l , of semimonocoque types t r u c t u r e , 1 5 4 i n c h e s i n d i a m e t e r , w it h a n a l u m i n u m o u t e r s k i n.i n s e r t ) i s 124 inch es i n l eng th .l o n g e r o n s .of a luminum.

T he s e r v i c e m o d ul e ( l e s sThe skin i s r i v e t e d t o a lu m i n u m r i n g f r a m e s a t t a c h e d t o s i x

The long eron s a re T - shaped , t he r im pa r t be ing f abr i ca t ed of s t e e l and the web

2-34.f r a m e s .l ower f r am e i s cons t ruc t e d of r ec t angula r a luminum tub ing .f r a m e s a r e r i v e te d t o s i x s t e e l an d a lu m in u m l o n g e r o n s an d 28 a l u m i nu m s t r i n g e r s .

T h e i n s e r t is 52 inc hes i n length. The sk in i s r i ve t e d t o upper and lower r i ngT h e u p p e r f r a m e i s composed of a luminu m angle s and webs r i ve t ed t og e the r ; t he

The upper and lowe r r i ng

2-35. The skin i s r i v e t e d to l o n g e r o n s a n d s t r i n g e r s .E igh t ho l e s i n t he a luminum sk in , even ly s pace d a round the aft end of the adap ter , providev e n ti n g f o r p r e s s u r e s w h i c h m a y b u il d up i n th e a d a p t e r .

T he a d a p t e r i s 92 inch es i n l ength .

2 -36. INTERF ACE EQUIPM ENT.2-37 . Boi l e rp l a t e 15 i n t e r f ac e equ ipment con s i s t s of bo l t s , t ens io n t i e s , and umbi l i ca lconne c o r s.2-38. TENSION TIES. (See f i gu re 2-10. )2 -39. COMMAND MODU LE-TO-SERV ICE MODULE TENSION-TIE BOLTS. The ten sio n-t i e bo l t s u t i li zed t o bo l t the comm and module t o the s e rv i ce module a r e s t ee l rod and tu r n-b u c k le a s s e m b l i e s .t he com mand module t o the s e rv i c e module comp res s io n bea r ing po int s .a r e a p p r o x i m a t e l y 42 i n c h e s l on g.28 .5 i nch es l ong.inc hes l ong on which hexagona l wrench f l a t s have bee n machined .a r e i n s t a l l e d o n b o i l e r p l a t e 15 configurat ion.u t i l iz e d a s a v e r t i c a l s t r u t t o h e l p ho ld t h e a f t h e a t s h i el d i n p l a ce .

T he a s s e m b l i e s a r e c a d m i u m p l at ed . The tu rnbuckle i s u s e d t o p r e l o aT h e a s s e m b l i e s

Two of t he as se mb l i e s us e 7 /8 - inc h hexagon s t ee l rod sNo pyro t echnic cha rge s

The th i rd tie a t l o n g e r o n No . 1 u s e s l - 1 / 4 - i n c h r ou n d s t e e l r o d 2 8.6The t ens ion tie a t l o n g e r o n No. 1 a l s o i s

2-40. UMBILICAL CONNECTORS.2-41.loca t ed i n t he p l an es -of - sepa ra t i on of the modules , a GSE umb i l i ca l connec tor fo r g roundsup por t equ ipment , and a coolant umbi l i ca l connec tor .sy s t em s of the modu les whil e t he modules a r e a t t ache d and prov ide a means of disconnect int h e e l e c t r i c a l s y s t e m s u p on m o d u le s e p a ra t io n . T h e r e i s n o r e q u i r e m e n t f o r m o d ul e s e p a -r a t i o n d u r i n g b o i l e r p la t e 1 5 m i s s i o n ; t h e r ef o r e , t he n e c e s s a r y h a r d w a r e f o r u m b i l i ca l d i s -c o n n e c t is omi t t ed ex cep t fo r GSE separa t i on .power whi le the boi l erp la te i s on the pad.f r o m G S E e q u i p m e n t o n the pad.

The umb i l i ca l con nec to r s on bo i l e rp l a te 15 con s i s t of e l ec t r i ca l connec tor s and p lugT h e s e c o n n e c t o r s j o i n th e e l e c t r i c a

The GSE umb i l i ca l suppl i es t he e l e c t r i ca lThe coolant umbi l ical suppl ies the f luid coolant

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SECTION 111LAUNCH E SCA PE SYSTEM

3-1. PURPOSE.3-2 . The bo i l e rp l a t e 15 l aunch escap e sys t em wi l l dem ons t r a t e t he s t r uc tu ra l adequacy ofthe des ign by the s ta t ic and dynamic loads imp osed whi le on the ground, and dur ing l i f t-of fa n d b o o s t p h a s e s .3-3. OPER ATION AL DESCRIPTION.3-4.j e t t i s o n ) i s a s fol lows:a r m e d p r i o r t o b o o s t e r i g n it io n by m a n u al c o m m a n d s.c u i t r y a r m s a n S - I/ S -I V s e p a r a ti o n r e l a y i n th e b o o s t e r i n s t r u m e n t u ni t.S - IV sep ara t i on , t he r e l ay c lose s and a 12- second t im er i n t he i ns t rum ent un it i s ac t iva t edAt t ime runout, t he separa t i on-p lus -12- /s scond s igna l opera t es t he r e l a y m ot or s i n t he t owes e n u e n c e r s , c los ing the mot or and se parat ion squib contacts , and thus supplying 28 vol t ss imul t aneous ly t o a l l j e t t i son motor and separa t i on squ ibs . F igur e 3 -1 i s a func tiona l b locdi ag ram showing sequenc e of events .t ower j e t t i son ,

The opera t i ona l desc r ip t i o n of t he l aunch escape sys t em ( f rom pre l aunch to t owerThe mi ss io n sequencer l og i c bus and tower seq uencer p yro bus a r e

T he m i s s i o n s e q u e n c e r l og i c c i r -At time of S-I/

Table 3-1 i s a t ime his to ry of the even ts leading to

Table 3-1. Time His tory of El rents Leading to Tower Je t t i son~

T i m e(Seconds

f r o mIgni t ion)

T - 3 .42T t OT + 69 .5T + 141.7T + 147.7T + 150.7T i- 61.7

~~

EventS-I igni t ionLift -offMax QS-I i nboardEng. cutoffS-I burnoutS-IV ig ni t ionEscape tower

J e1oc i y( F e e t /

Second)0

148182 121718. 3

;678. 41752. 5

Alti tude{ F e e t )

00

38 ,770198, 187219 ,886230 ,750265 ,581

DynamicP r e s s u r e( P o u n d s

Foot')00

72028. 311.0

7 .01 . 3

Fl ightP a t h

Angle(Deg)

9090

58. 725. 824. 824. 422. 8

0

505567

~~

MachNo.

00

1 . 57 .98. 99 .1

10.33-5. MOTOR IGNITION.3-6.pyro t echnic ca r t r i dg es which f i r e t he i gn it e r of t he motor .e m p l o y e d f o r i n c r e a s e d r e li a b il i ty .t he ca r t r i d ge , which ign i t e s t he rocke t moto r i gn i t e r .a 3/4- in ch f l ange , 0 . 45 i nch f rom the t h readed end.independent ho t w i re c i r cu i t s and four p ins .when one br idgewi re i s sub jec t ed t o a f i r i ng cur re n t of 3 .5 am pere s .t he exp los ive charge i s produced wi th in 12 mi l l i s econd s a f t e r app l i ca t ion of cur r en t .i gn i t e r fo r t he t ower j e t t i son moto r i s i ns t a l l ed i n the a f t dome of t he roc ke t motor .p r o p e l l a n t g r a i n i s an 8-point conf igurat ion of boron po tass iu m ni t r a te .

Each mot or i gn i t ion sys t em conta ins two e l ec t r i ca l hot w i re i n i t i a to r s t h readed in toRedundant i n i t i a to r s a r e

Cur re n t pas s ing t h rough low re s i s t a nce wi re s de tona t eThe ini t i ator body i s 1 inch long wit

The e l ec t r i ca l head er con ta ins twoThe ini t ia tor ign i tes wi thin 10 mi l l i s econ ds

T he p r e s s u r e l e v e l oThe

The

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3-7. TOWER SEPARATION.3-8.t he t ower t o t he comman d module.charg e and the shaped charge .t he bo l t and the shaped charg e i s j us t be low the bo l t head .taneously.explos ive bol t s .r ece ive d f rom the mi ss io n sequen cer t h rough the t ower sequencer s .detonate to f i re the explos ive bol t s wi thin 5 mi l l i seconds .m i ss io n sequencer s imul t aneous ly in i t i a te s de tona ting s igna l s t o the explos ive bo l t s and tothe t ower j e t t i son motor ho t w i re i n i t i a to r s .and pu ll ed c l ea r o f t he sp ace cra f t t r a j ec to ry .nec t ions a re d i sconnec t ed au tomati ca l l y when tower sep ara t es f r om the command module .

The tower se para t i o n sys t em co ns i s t s o f four exp los ive bo l t s ( f i gure 2 - 2 ) t h a t s e c u r eEach bo l t con ta ins two charge s , t he exp los ive bo l t

The explos ive bol t charge i s contained in t he cen t e r of theB o th c h a r g e s a r e f i r e d s i m u l -

Release of the tower i s accompl i shed by s imul t aneous de tona t ion of t he fourThe ho t w i re i n i t i a to r s fo r t he bo lt s a r e i gn it ed by 28-vo lt d -c s igna l sThe in i t i a to r s wi l l

To accompl i s h tower j e t t i son , t heT he e n t i r e l a u n ch e s c a p e a s s e m b l y i s r e l e a s e d

The tower t o command module umbi l i ca l con-

3-9. LAUNCH ESCA PE MOTOR.3-10.can t ed 35 degre es f ro m the me an moto r cen t e r l i ne . The r esu l t an t t h ru s t vec tor of 2. 3de gr ee s i s ob t ained by a d i f f e rence i n exhaust nozz l e t h roa t a r ea .i s appro xima tely 3000 pounds , giving the mo tor a g ro ss weights of app roxim ately 4800pounds.a t 7 0 d e g r e e s F a h r e n h e i t g r a i n t e m p e r a t u r e .wi th burnout a t 8 seconds .

The launch escape m otor i s a so l id -prope l l an t mo tor wi th four nozz l es nomina l lyThe prope l lan t cap ac i ty

Effect ive thrus t developed i s approximately 155, 000 pounds a t 36, 000 f ee t a l t i tude ,B u r n in g t i m e i s 3 s e c o n d s a t n o m i n a l t h r u s t

3 -1 1. PITCH CONTROL MOTOR.3-12.to 3400 pounds of thr us t for 0. 5 second in the min us Z- di rect ion, producing a pos i t ive pi tchra t e about t he Y-ax i s t o p rov ide d i sp l acement .

The p i tch con t ro l mo tor i s a so l id -prope l l an t r eac t i on moto r . The moto r p rov ides up

3-13. LAUNCH ESC APE TOWER JETTISO N MOTOR.3-14 . The tower j e t t i son moto r i s a so l id -prope l l an t moto r t ha t p rov ides t he t h ru s t fo rsep ara t i on of t he launch escap e t ower and r e l a t ed equ ipment f ro m the com mand module .The j e t t i son m otor i s mounted on top of t he i n e r t e s cap e motor .t r o l i n t he fo rm of o f f set exhaus t nozz l es p rov ides a t r a j e c t o r y t h a t a r c s s li g ht ly i n t h e p i tc hup d i r ec t i on .

P a s s i v e t h r u s t v e c t o r c o n -Fo r opera t i ona l chara c t e r i s t i c s of t he j e t t i son motor , r e f e r to t ab l e 3 -2 .

Table 3-2. Opera t i ona l Char ac t e r i s t i c s of Launch Escape Tow er Je t t i son M otorThr us t 33 ,000 poundsDurat ion 1 secondT i m e r e q u i r e d t o r e a c h 9 0 - p e r c e n t m a x i m u mthru s t 75 t o 125 mi l l i s econdsA n g l es b e t w ee n r e s u l t a n t t h r u s t a x i s a n d m o t o r :

P i tch planeYaw plane

2 d e g r e e s k30 minutes0 degre es *30 minu tes

3-3


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3-15. MISSION SEQUENCER. (See f ig ure 2-7 , s h e e t 5 , view E, and f i gure 3 -2 . )3-16.e v e n t s t h at a r e n e c e s s a r y t o e x e c ut e a s u c c e s s f u l l a u n c h e s c a p e t o w e r j e t t i s o n o p e r a t io n .The seque nce r con tains t he l og i c c i r cu i t s t o d i r ec t the t iming and or de r of t he e l ec t r i ca l l yini t ia ted s te ps of the miss ion.v ided fo r r e l i ab i li t y .o p e r a t e t h e m o t o r s w i tc h e s i n th e t o w e r s e q u e n c e r f o r f i r i n g t he e x p l o s iv e b o l t s q u i b s a n dign i ti ng t he t ower j e t t i son m otor .t he m i s s i o n s e q u e n c e r p r o v i d e s c o m p a t i b il i ty f o r m o n i t or i n g c r i t i c a l e v e n t s a s t hey occur ,t hus p rov id ing a n i npu t t o t he i ns t rumenta t i on sys t em.

The mi ss io n sequ encer l oca t ed i n t he comm and module con t ro l s t he sequence of

Comple t e r edundancy of t he en t i r e sequen t i a l ne twork i s p ro-T h e m i s s i o n s e q u e n c e r l o g i c c i r c u i t s s e n d e l e c t r i c a l s i g n a l s t o

Table 3 - 3 gives mi ss ion sequencer func t ions . In add i t i on ,

3-17. TOWER SEQUENCERS. (See f ig ure s 2 - 3 an d 3 - 3 . )3-18.s e q u e n c e r h a s o ne m o t o r - d r i v e n s w it c h.d r ive s e ach moto r -dr iv en swi t ch t o the ARM posi ti on .p o w er f r o m t h e p y r o b u s t o s i m u l t a n e o u s l y f i re t he t ower se para t i on exp los ive bo l t s , shapedc h a r g e s , a n d j e t t i s o n m o t o r i g n i t e r .func t iona l s t a tus of t he co n t ro l c i r c u i t s v i a GSE dur ing checkout opera t i ons .sequencer s p rov ides t o t a l r edundancy fo r r e l i ab i l i t y .

Two tower seq uenc er s a r e a t t ached to t he und er s ide of t he s t r uc tu ra l sk i r t . E a c hAn ou tpu t vo l t age f ro m the mi s s io n sequen cer

T h e s w i t c h e s t h e n a l l o w e l e c t r i c a lThe sequencer p rov ides c i r cu i t s fo r moni to r ing t he

Use of two

SignalLogic busA & B a r mz o m m a n d

Logic busA & B

P y r o b u sA & B a r mc o m m a n d

P y r o b u sA & B

Table 3-3 . M iss ion Sequencer Func t ions

Func t ionSuppl i es bas e vo l t age fo rt r a n s i s t o r i z e d s w it c hi n g n e t-wor k to energ i ze co i l s ofm o t o r - d r i v e n s w i t c h e s C 18K1an d C18K2.Suppl i es co l l ec to r vo l t age t ot r a n s i s t o r i z e d s w i tc h i n g n e t -wor k to energ i ze co i l s ofm o t o r - d r i v e n s w i t c h e s E 1 8K 1a n d E 18 K2 a n d t o a r m c o n -tac ts of S- I sep ara t io n s ignal .Suppl i es bas e vo l t age fo rt r ans i s to r i z ed swi t ch ing ne t -work to energ i ze co i l s ofm o t o r - d r i v e n s w i t c h e s C 18 K 3and C18K4.Suppl i es vo lt age t o f i r i ngco nta cts of E18K1 and E18K2.

T i m e' r e l aunch

' r e l aunch

' re launch

' re launch

Cont ro l l i ngComponent s

C18J4-b

C18K1 and C18K2,C18J2-XY and C18J2-YC18J4-X, C18J4-Y,

C18J4-V

C18K3 and C18K4,C 1 8 J 2 - T , a n d C l 8 J 2 - UC18J1-T , C18J1-U,

~

SignalS o u r c e

GSE

Logicb a t t e r i e sA and B

GSE

P y r ob a t t e r y A

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Launche s c a p et owe rje t t i son

SMLA -07-B i 5Table 3 - 3 . Miss ion Sequencer Func t ion s (Cont )

Funct ionSuppl ies bas e vol t age to t r an-s i s tor i zed swi tch ing ne tworkto energ iz e co i l s of moto r -dr iven swi tches E18K1 andE18K2.Suppl ies f i r ing vol t age tot owe r j e t t i s on mo t o r a ndl a unc h e s c a p e t owe r s e p a -r a t i on s qu i b i n i t i a t o rs .

~~

T i m eS-I s e p a -ra t ion p lus12 second s

S-I s e p a -ra t ion p lus12 seconds

Coc t r o l l ingCompone n t s

Iv p r o g r a m e r C 1 8 J l - J ,and C18J2-KC 1 8 J l - K , C 1 8 J 2 - J S

E18K1 and E18K2

Signa lSource

Logic busA and B

P y r o b u sA an d B

3 - 5 1 3 -


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SECTION IVCOMMUNICATIONS AND INSTRUMENTATION

4 - 1. PURPOSE.4-2.condi ti oning prese l ec t ed i n format ion and of t r ansm i t t i ng t h i s i n format ion to e a r th moni to r ingequipment .t rac kin g of the spac ecr af t dur ing the miss ion.equ ipment , t he i n format ion be ing used fo r boos t e r gu idance sys t em p er form ance eva lua t ion .The Q-ba l l sys t em i s not connected functionally with the Apol lo comm unicat ions and ins t ru -m e n t a t io n s y s t e m b u t is desc r ib ed in t h is sec t i on .

The communica t ions and ins t rumenta t i on sys t em pro v ides a me an s of acqu i r ing and( R e f e r t o ta b l e 4 - 1 f o r m e a s u r e m e n t l is t . ) T h e s y s t e m a l s o p r o v id e s f o r

The Q-ba l l con ta ins some ins t rumenta t i on

4-3. DESCRIPTION. (See f igu re 4-1 . )NOTE

Fclr de ta i l ed de sc r ip t i ve an d checkout i n for -mat ion fo r t he R&D e l ec t ron i c equ ipmentfur nis hed by NASA, re fe r to app licabl e NASAdocument .

4 4. COMMUNICATIONS EQU IPM EN T.4-5.t r a n s ponde r s .ommunica t ions R&D equipment cons i s t s of t he t e l em et ry sys t em and r a da r4-6. T he t e l e m e t r y s y s t e m c o n s i s t s of t h r e e F M / F M t e l e m e t r ysub sys t em s , one sys t em contain ing two PAM channe l s , t he t r a ns mi t t e r s of e a c h o p e r a t in gin to t he an t enna sys t em .c a r r i e r osc i l l a to r s and , i n add i ti on , subsys t em A conta ins a 9 0 x 10 an d a 90 x 1 - 1 / 4c o m m u t a t o r u s e d f o r t e m p e r a t u r e m e a s u r e m e n t s .

TELEMETRY SYSTEM.B e s i d e s th e t r a n s m i t t e r , e a c h t e l e m e t r y s u b s y s t e m i n c lu d e s s u b -

4-7 . T ransmi t t i ng f r equenc i es of t he t h ree sys t ems a r e a s fol lows:Te lem et ry sys t em A 237.8 m cT e l e m e t r y s y s t e m B 2 4 7 .3 m cT e l e m e t r y s y s t e m C 2 5 7 .3 m c .

4-8. The antenna sys tem con sis t s of a mul t ip l exer , a f i l ter , and a VHF omniantenna. Thean tenna i s located under a r a d o m e i n t he n o s e of t he com mand module .4 -9 .r ece iv ing a t 5690 mc and t r ansmi t t i ng a t 5765 mc .2-p ulse code spaced a t inte rva ls of 3 .5 micro sec ond s between leading edge s and fol lowed bya 2. 0-mic rosecond de l ay .r e q u i r e m e n t s .

RADAR TRANSPONDERS. The two r ad ar t r a nsp ond er s opera t e i n t he C-band ,T he t r a n s p o n d e r s a r e i n t e r r o g a t e d b y a

The r epe t it i on r a t e wi l l be cons i s t en t w ith r ange t r ack ing

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4-10.he l i c a l , f l u s h - moun t e d a n t e nna s.uppe r s e c t i on of t he s e r v i c e modu l e .

The r a da r t r a ns pond e r a n t e nna s y s t e m i nc l ude s t wo powe r d i v i de r s a nd f ou r c a v i t yThe a n t e nna s a r e moun t ed 9 0 d e g r e e s a p a r t a r ou n d th e

4-1 1. INSTRUMENTATION EQUIPMENT.

4 -1 2. I n s t ru m e n t a t i on e q u ip m e n t i n c lu d e s t h e n e c e s s a r y t r a n s d u c e r s , s e n s o r s , a n d o t h e rde v i c e s t o mon i t o r phys i c a l a nd t he r m a l e f f e c t s of f l igh t upon t he s pa c e c r a f t a nd t o c o nve r tt he m i n t o e l e c t r i c a l s i gna l s s u i t ab l e f o r t e l e m e t e r i ng . The de v i c e s a r e l oc a t e d i n a nd ont h e s p a c e c r a f t a s s ho w n in f i g u r e 4 -2 .m e a s u r e me n t de s c r i p t i on , c ha nne l , da t a r a nge , p r i o r i t y , r e s pons e , a nd de v i c e l oc at i on.Subheadings in the channe l co lumns ind ica te the fol lowing: LK ( l ink) des ig na tes the t e le -m e t r y ( r - f c a r r i e r ) p a ck a ge A, B , o r C ; S C No. ( s u b c a r r i e r n u m b e r ) d e si g n a t e s t e l e m e t r ychann el s 1 th rough 18 , a nd Com Seg ( c ommut a t o r s e gme n t ) de s i gna t e s t he t e l e me t r y c o m-m u t a t o r s e g m e n t a s s i g n e d t o t he m e a s u r e m e n t f o r t h a t v eh i c le .t e l e me t r y ) , wh i ch a ppe a r s i n t he c hannel LK and SC No. c o l umns , de s i gna t e s a me a s u r e -m e n t t o b e t e l e m e t e r e d b y l a u n c h ve h ic le t e l e m e t r y .m i n i m u m a n d m a x i m u m v a l u e s f o r a pa r a m e t e r i n e ng i ne e ri ng un i t s. The f o ll owing l e t t e r si n t he P R ( p r i o r i t y ) c o l umn ind i c at e how c r i t i c a l t he me a s u r e me n t s a r e :d e n o t e s m e a s u r e m e n t s t h a t m u s t b e a va il a b le a t l a unch f o r mi s s i o n s uc c e s s a nd t o me e t t hef l i gh t ob j e c t i ve s ; S ( s e c onda r y ) de no te s me a s u r e me n t s t ha t a r e h igh ly de s i r a b l e , bu t w il l noa b o r t o r d e l ay th e m i s s i o n if i nope r a ti ve , a nd M ( mu l t i p l e ) de s i gna t e s a g r ou p of m e a s u r e -me nts of which only a s pec i f i e d percentage m ay be inopera t ive .de no t e s t he r a t e a nd uni t r e qu i r e d t o p rov i de s a t i s f a c t o r y da t a r e s o l u t i on t o t i me o r wa ve -f o r m .c yc l e s pe r s e c ond ( c ps ) , a n d s a m p l e d - da t a m o n i t o ri n g ( P C M o r P A C E ) i s s pe c i f ie d i ns a m p l e s p e r s e co n d ( S / S ) .phys i c a l l oc a t i on wi t h i n t he s pa c e c r a f t whe r e me a s u r e m e n t i s t a ke n.

Ta b l e 4 - 1 pe r t a i n s t o i de n t i f ic a t i on numbe r ,

LV TM ( launch vehic leThe da ta range co lumns denote

P ( p r i m a r y )

The r e s pons e c o l umnRe s pons e f o r c on ti nuous da ta mon i t o ri ng ( t e l e me t r y o r r e c o r d e r ) i s s pe c i fi e d i n

The locat ion co lumn re fe r s to the coo rd ina t es which denote the

4 -1 3 .m e a s u r e m e n t s e n s o r s to t h e t e l e m e t r y s i g n a l in p ut r e q u i r e m e n t s a n d a l s o d i r e c t s t h e c o n -d i t i one d s i gna l t o the p r op e r t e l e me t r y s y s t e m.i s inc luded in the s igna l c ondi t ioner uni t.and R ( r a n g e ) i s equa l to 85 percen t of fu l l - sca l e s igna l .

SIGNAL CONDITIONER. The s i gna l c ond i t i one r a da p t s a l l s i gna l s r e c e i ve d f r o m t hAll R and Z c a l i b r a t i on c omma nd c i r c u i t r y

Z ( z e r o ) i s e q ua l t o 15 perc ent of fu l l - sca le s ign

4 - 14. Spa c e c r af t r a d i a l v i b r a t i ons a r e mon i t o r e d by s i x v i b r a t i ont r a ns du c e r s l oca t e d i n the c omma nd modul e ( I ) , s e r v i c e modu l e ( 3 ) , a nd a da p t e r ( 2 ) . Thes e ns o r c i r c u i t r y i nc l ude s a n a mp l i f i e r wh ic h r a i s e s t he s i gna l t o a l e ve l c ompa t i b l e wit h threq ui r ed s igna l input of the s igna l condi t ioner.d e v ic e ( m i c r o ph o n e ) a r e l o c a t ed o n th e s e r v i c e m o d u l e s u r f a c e t o d e t e r m i n e s t r u c t u r a lr e s po ns e a nd a e r odyna mi c a nd e ng i ne no i s e s du r i ng boos t a nd s t a g ing pha s e s .a r e r ou t e d t h r ough the boos t e r i n s t r um e n t un it .

VIBRATION SENSORS.

Two a ddi t i ona l s e n s o r s a nd a n a c ous t i c a lT h e s e s i g n a

4-15 .a nd t wo on t he s e r v i c e modu l e r i ng f r a me t o de t e r mi ne s pa c e c r a f t s t r uc t u r a l i n t e g r it y undedyna mi c l oa ds .pa t ib le wi th the r equ i red s igna l input of the s igna l condi t ioner .

STRAIN SENSORS. F o u r s t r a i n g ag e s a r e m o un t ed o n t he a d a p t e r s t r i n g e r f r a m e

The c i r c u i t r y i nc lude s a n a mp l i f i e r wh ic h r a i s e s t he s i gna l t o a l e ve l c om

4-16.s p a c e c r a f t a s f ol l ow s :modu l e .s e n s o r s a r e m o u n te d a b ou t th e c o m m a nd m o d ul e e x t e r i o r , t o d e t e r m i n e t h e a e r o d y n am i ce f f e c t s on t he s p a c e c r a f t t o ve r i fy s t a b i l it y a nd l oads .du c e r s a r e l oc a t e d on t he s pa c e c r a f t , t wo i n t he c omma nd modu le a nd e l e ve n i n t he s e r v i c e

PRESSURE TRANSDUCERS. T h e r e a r e 2 6 pr e s s u r e - s e ns i ng de v i c e s l oc a te d i n t heone t ran sdu cer in the com man d module and one in the s e rv i ceT he t r a n s d u c e r s m o n i t o r s t a t ic i n t e r n a l p r e s s u r e s . Nine con i c a l s u r f a c e p r e s s u

F i f t e en f lu c tu a ti n g p r e s s u r e t r a n s -

4 -


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4-4

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ii,

SA0087DINSIDE S/M

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SA0088DINSIDE S/M

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SM-a-369BV I B R A T I O N T R AN S D UC E R S (7 )

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SAOOO3ASA0004AINSIDE S/M

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F i g u r e 4-2. R & D Ins t rumenta t ion Locat ions (Sheet 2 of 6 )4-


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4-6

CA0580RCA0581RCA0583RCAO584RDIAMETRICALLYOPPOSITECA0587RCA0585RCA0586RDIAMETRICALLYOPPOSITESA0550R

SA0552RSA0598RSA0554RSA0555R

AA0594R

CALORIMETERS (20)

F i g u r e 4 - 2. R& D Ins t rumenta t ion Loca t ions (Sheet 3 of 6 )


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F i g u r e 4-2. R & D Ins t rumentat ion Locat ions (Sheet 6 of 6 )4-1


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I module . T h e s e me a s u r e m e n t s h e l p t o de f i n e b o u n d ar y l a y e r n o i s e , c o n f i r m e n v i r o n me n t a lp red ic t ions , and de te r min e son ic -induced v ib ra t ion respon se of the se rv i ce module pane l s .4 -1 7. AC C EL E R OME T ER S . S p a c e c r a f t a c c e l e r a t i o n me a s u r e me n t s i n a l l t h r e e p l a n e sa r e r e q u i r e d t o d e t e r mi n e fl ig h t p a r a m e t e r s a n d t o we r s t r u c t u r e f li gh t l o ad s .om et e r s a r e mounted in the nose cone of the launch escap e mot or . One i s a s s e m b l e d t ome a s u r e a c c e l e r a t i o n a lo n g th e Y-axis and the o the r i s a s s e m b l e d t o m e a s u r e a c c e l e r a t i o na long the Z-a x i s .a c c e l e r a t i o n i n a ll t h r e e a x e s a n d two a r e mo u n te d i n th e s e r v i c e mo d ul e t o me a s u r ea c c e l e r a t i o n s a l o n g th e Y - a n d Z - a x e s .

T wo a c c e l e r -

T h r e e a c c e l e r o m e t e r s a r e m o u nt ed i n t h e c o m m a n d m o du le t o m e a s u r e

4-18.to moni to r the ma in bus d - c vo l tage .can a l s o be moni to red by mean s of the vo l tage d iv ide r ne tw orks .s e q u e n c e i n f o r ma t i o n a s t o t h e t i me of a r m i n g t h e b u s e s .t h r o u g h r e l a y c l o s u r e , a r e je t t i s o n mo t o r i g n it io n c o mm a n d s an d r e s u l t a n t t o we r s e p a r a t i o n ,a n d t o we r - c o mma n d mo d ul e s e p a r a t i o n c o mma n d f r o m th e b o o s t e r g u i d an c e s y s t e m .purpose of moni to r ing the vo l tage l eve l s i s to de te rm ine the e lec t r i ca l capab i l i ty of thee le c t r i ca l power sys tem and the miss i on seque ncer dur ing f l igh t load ing cond it ions .purpo se of the even t s s igna l s i s to demon s t ra te tower j e t t i son sequenc ing .

VOLTAGE DIVIDER NETWORKS. Two vo ltage d iv ide r ne tworks p rov ide the m ean sThe vol tage le vel s of the two logic and two pyro bu se s

T h i s a l s o p r o v i d e s e v e n t sO t h e r e v en t s , w h i ch a r e s e n s e d

TheThe

4-19.t h e b o o s t e r i n s t r u m e n t un it a n d t o mo n i t o r t r a n s p o n d e r t r i g g e r s i g n a l s .

S e n s o r s a r e a l so p rov ided to moni to r the sequ encer con t ro l S-I l i ft -off s ign al f r om

4-20.t h e c o mm a n d mod u le a nd s e r v i c e mo d u l e to d e t e r mi n e i n t e r i o r t e m p e r a t u r e s d u r i n g f l i gh tloading conditions.s y s t e m t o w er s t r u c t u r e m e m b e r s t o d e t e r m i n e a e r o d y n a m i c h ea t i ng .mo u n te d o n e a c h c a l o r i m e t e r t o s e n s e c a l o r i m e t e r b o dy t e mp e r a t u r e f o r u s e i n c o mp u ti n ghea t f low f ro m the da ta p rov ided by the 20 c a l o r i m c t c r s .a mp l i f i r r c n v i ro n i n en t a l t e mp e r a t u r e s a r e n i on i l o re d f o r a b n o r ma l h e a t in g by s i x s e n s o r smounted in the t e lem et ry packages .

TEMPER ATUR E SENSORS. A t e m p e r a t u r e s e n s o r i s mo u n t e d i n t h e i n t e r i o r of b ot hE i gh t r e s i s t a n c e t h e r m o m e t e r s a r e mo u n te d o n t h e la u n c h e s c a p e

A the rmocoup le i sT e l e m e t r y t r a n s m i t t e r a n d r-f

4-21.hea t ing ra te s of va r ious a re as in o rd e r to adequa te ly def ine ae rod ynam ic hea t ing of thes p a c e c r a f t . Twelve a r e loca ted abou t the com mand module su r face ,mo d u l e s u r f a c e , a n d one o n t h e a d a p t e r s u r f a c e .

C AL ORI ME TE R S, T wen ty c a l o r i me t e r s a r e l o ca t e d i n t he s p a c e c r a f t t o me a s u r eI s e v e n o n t h e s e r v i c e

4-22 . CURRENT SENSOR. A cur r en t se nso r i s loca ted in the power con t ro l box . I t moni -t o r s t he t o t a l ma i n p o wer d i r e c t c u r r e n t f lo w d u r in g s y s t e m o p e r a t i o n t o a s s i s t i n d e t e r -min ing the e le c t r i ca l capab il i ty and opera t ion of the e lec t r i c a l power sys te m.4-23. Q-BALL. ( S e e f igure.s 4-3 and 4-1. ) T h r e e p r e s s u r e t r a n s d u c e r s w it h a s s o c i a te de l e c t r o n i c s a n d wi r i n g f o r m t h e MS F C - f u r n i s h e d Q- b a l l s y s t e m .Q-ba l l inc ludes ang le of at tac k, an gle of s idesl ip , and dynamic r am p r e s s u r e s .d u c e r s a r e l o c a t e d in the L E S n o s e c on e a nd s e n s e a i r f l o w d i r e c t i o n a n d p r e s s u r e t h r o u g hpor t s in the nose cone su r face .capac i tance -b a lanced with convers io n o f inpu t power to 8 k i locyc les.t r a n s d u c e r s is p r o p or t i on a l t o t he t h r e e d i f f e r e n t i a l p r e s s u r e s me a s u r e d . T h e t r a n s d u c e rou tpu t s a r e rou ted to the boos te r in s t rum enta t ion un it c on t ro l comput e r and cond i tioned fo rb o o s t e r t e l e m e t r y , b u t a r e n o t u s e d f un ct io n al ly .

Da ta acqu i re d by theI T h e t r a n s -

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SECTION VIELECTR ICAL POWER SYSTEM

6 - 1. PURPOSE.6 - 2 .and to a l l oper a t i ona l un i t s of t he communica t ions and ins t rume nta t i on sy s t e m for swit chingand d i s t r i bu t ion of even t s t ha t o ccur dur ing a m i s s i o n .a r r an ge me nt fo r even t d i s t r i bu t ion t o t he s igna l condi ti oning un i t and opera t i ng and moni -to r ing power fo r l aunch escap e sy s t em funct ions.

The e l ec t r i ca l power sys t em suppl ies the power t o t he env i ronm enta l con t ro l sys t emIt a l s o p rov ides t he swit ching

6-3. SYSTEM EQUIPMENT.6-4 . The e l e c t r i ca l power sys t em cons i s t s of s ix m u l t i - c e l l , z i n c - s i l v e r o x i de b a t t e r i e s ,p o w er c o n t r o l b o x, a ju n ct io n b o x, a nd a s s o c i a t e d w i r e h a r n e s s e s . T h e s e u n i ts a r e l o c a t e don the equ ipmen t r a ck s of t he com mand module .a r e l i s t e d i n t ab le 6-1.

P h y s i ca l c h a r a c t e r i s t i c s of t he ba t t e r i e s

6-5. PRINCIPLES O F OPERATION. (See f ig ure 6-1. )6-6.t h e i n s t r u m e n t a t i o n d e v i c e s s u c h a s s e n s o r s , a m p l i f i e r s , a n d t e l e m e t r y eq u ip m e nt . T hem a i n b a t t e r i e s s up p ly p o we r t o b u s e s A a n d B of the power co nt ro l box through nor ma l lyclo sed contacts of the inte rna l A and B power co n t ro l r e l ays .ene rg i z ed by GSE ac t ion.p l i ed by GSE to p re se r ve t he ba t t e ry power p r io r t o umbi l i ca l d i sconnec t.i s acco mpl i sh ed manua l ly .c l o s e a n d s y s t e m p o w e r is suppli ed by the on-board b a t t e r i e s .

The ma in ba t t e r i e s (NASA-furni shed) p rov ide t he e l ec t r i ca l power r eq u i r e d t o energ i

T h e s e r e l a y s c a n o nl y b eThe power con t ro l r e l ays r em ain open when power i s being sup-P o w e r t r a n s f e r

When power f r om GSE i s discont inued, the power cont rol re lay

6-7.s y s t e m c o m po n en t s.s u c c e s s f u l m i s s i on .

The pyro ba t t e r i e s p rov ide t he e l ec t r i ca l power to energ i ze t he t ower separa t i onRedundant c i r cu i t s p rov ide t he h igh r e l i ab i l i t y r equ i r ed t o as s ur e a

6-8.m i s s i o n an d t o w e r s e q u e n c e r s .a s s u r e a s u c c e s sf u l m i s s i on .

The log i c ba t t e r i e s p rov ide the e l ec t r i ca l power t o energ i z e con t ro l c i r cu i t ry of t heRedundant c i r c u i t s p rov ide t he h igh r e l i ab i l i t y r eq u i r e d t o

6-9. POW ER CONSUMPTION.6-10. O p t im u m p ow e r r e q u i r e m e n t s by s y s t e m a r e a s f ol lo w s:

Equipmen t coo ling sys t em 396 wat t s (mi s s ion)Communicat ions and ins t ru men tat ions y s t e m 9 24 w a t t s ( m i s s i o n )L a u nc h e s c a p e s y s t e m

Tower j e t t i son mo tor squ ibs 18 wat t s ( fo r 20 mi l l i s ec onds )Tower l eg sep ara t i on squ ibs 72 wat t s ( fo r 20 mi l l i s econds ) .

6


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SM2A-07-BP15

vINSTRUMENTATION

(SIGNAL CONDITIONER,SENSORS)COMMUTATORS,

BATTERY

0v v

ENVIRONMENTALCONTROLSYSTEM

C OM M U N I C A T I ON S( RF PACKAGE,TRANSPONDER)C-BAND

BATTERYIMISSION SEQUENCEROWER SEQUENCER TOWER SEQUENCER

PYROBATTERIES(2 )

SM-24-279A

LOGICBATTERIES(2)

Figure 6 -1 . E l e c t r i c a l P o w e r S y s t e m B l oc k D i a g r a m

Tab le 6 -1 . Ba t t e ry Phys i ca l Cha rac t e r i s t i c s

Main ba t t e r i e s ( i n s t rumen ta t ion )HeightWidthLengthWeightNominal vol tageCapaci tyE lec t ro ly t e

9.50 inches6 .36 inches9 .05 inches52 pounds28 vol t s120 - am pere hour sPo ta s s ium hydrox ide .

P y r o a n d l o g i c b a t t e r ie sHeight 3 . 52 inchesWidth 4. 69 i n c h e sLength 7 .00 inch esWeight 7.6 poundsNominal vol tage 28 vol t sCapaci ty 5 - a m p e r e h o u r sEle ct r olyte Po ta s s ium hydrox ide .

6 -2


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~~~

DocumentNo.

SM3A-2 08

SM3A-213

SM3A -2 2 1

SM 3A3-22 2

SM3A-226

SM3A -22 7

SM3A-228

SM3A-229

SM3A -2 35

SM3A-263

SM2A- 07 -B PI 5

Tab le 7 - 1 . Boi le rp la te 15 Supp lementa ry Docum ents (Con t )

T i t l eApollo Suppo rt Equipment , Mainte -nance Da ta Dis t r ibu t ion andRecording Console , M odel C14-420,P a r t N o. G16-850500-101Apollo Support Equipm ent , Mainte -nance Antenna Checkout Group,Mode l C14-032 , P a r t No.G16-850400-101Apollo Support Equipment , Mainte -nance Ground Cool ing Ca rt , ModelA14-011

Apollo Support Equipment , Mainte -nance Launch Esca pe Tower Subs t i -tute Unit, Model A14-001, Par t No.G16-820301-201Apollo Support Equipm ent , Mainte -nance Pyro techn ics BenchMain tenance Equ ipment , Mode lC14-051 , Pa r t No. G16-852700-101Apollo Support Equipment , Mainte -nance Launch Escape SequencerBench Main tenance Eq u ipment ,Mode l C14-029 , P a r t No.G16-853400-201Apollo Support Equipm ent , Mainte -nance Launch Vehicle Subst i tu teUnit , Model A14-021, P a r t No.G16-821300Apollo Support Equipm ent , Mainte -nance Optical Alignment Set , ModelA14-028, P a r t No. G17-824010Apollo Support Equipm ent , Mainte -nance Launch Cont ro l Group , Mode lC14-414 , Pa r t N o . G16-853950-101Apol lo Support Equ ipment , Main te -nance W ater-Glycol Cool ing Unit ,Model S14-052, Pa r t No.G16 -84802 0

Conten t sP h y s i c a l a n d f u n c t i o n a l d e s c r i p t i o n a n dmain tenance p rocedures cons i s t ing o ff u n c ti o n a l t e s t s a n d r e p a i r .

P h y s i c a l a n d f u n c t io n a l d e s c r i p t i o n a n dmain tenance p rocedures cons i s t ing o ff u n c ti o n a l t e s t s a n d r e p a i r .

Main tenance ins t r uc t io ns cove r inginspec t ion , c lean ing , lubr ica t ion ,t roub le ana lys i s , and main tenance ofequipm e nt .P h y s i c a l a n d f u n c ti o n a l d e s c r i p t i o n a n dmain tenance p rocedures cons i s t ing o ff u n c ti o n a l t e s t s a n d r e p a i r .

P h y s i c a l a n d f u n c t io n a l d e s c r i p t i o n a n dmain tenance p rocedures cons i s t ing o ffunct ional tes ts and r e p a i r .

P h y s i c a l a n d f u n c t io n a l d e s c r i p t i o n oft e s t , t r o u b l e a n a l y s i s , r e p a i r ,s e r v i c i n g , p a c ka g in g , a n d d i a g r a ms a sre la t ed to bo i le rp la te 15 conf igura t ion .

P h y s i c a l a n d f u n c t io n a l d e s c r i p t i o n a ndma i n t e n a n c e p r o c e d u r e s c o n s i st i n g off u n c ti o n a l t e s t s a n d r e p a i r .

Phys ica l and func t iona l desc r ip t ion andma i n t e n a n c e p r o c e d u r e s c o n s i s t i n g off u n c ti o n a l t e s t s a n d r e p a i r .Phy s ica l and func t iona l desc r ip t ion andma i n t e n a n c e p r o c e d u r e s c o n s i s t i n g off u n c ti o n a l t e s t s a n d r e p a i r .Ma i n t e na n c e i n s t r u c t i o n s c o v e r i n gins pe c t ion , c lean ing , lubr ica t ion ,t roub le ana lys i s , and main ten ance ofe qui pm ent.

7-2


70/119

DocumentNo.

SM3A-2 72

SM3A-2 73

SM4A -2 00-B P 1 5

SMZA-07-BP15

Table 7-1. Boi l e rp l a t e 15 Suppleme nta ry Documents (Cont )

T i t l e~

Apollo Suppor t Equipment, Mainte -nance MSFC Patch and LogicDistr ibuti on Sub Unit, ModelA14-075, Par t No. G16-853060Apollo Suppor t Equipm ent , Mainte -nance Umbi l i ca l Junc t ion Box,Model C14-192, P a r t No.G16-852850Apol lo S pac ecr af t MaintenanceB P 1 5

Conten t sPhys i ca l and func t iona l desc r ip t i on andm a i n t e n a n c e p r o c e d u r e s c o n s i s t in g offunc t iona l t e s t s and r ep a i r .

Phys i c a l and func t iona l desc r ip t i on andmain t enance pro cedu res c ons i s t i ng offunc t iona l t e s t s and r epa i r .

M ain t enance proce dure s c ons i s t i ng o ft e s t in g , t r o u b l e a n a l y s i s , r e p a i r ,r emova l and ins t a l l a t i on , and ca l i -b r a t i o n a n d a d j u s t m e n t a s r e l a t e d t oboi le rpla te 15 conf igurat ion.

7-5. SUPPORTING EQUIPMENT.7-6.table 7-2.

Suppor t i ng equ ipment fo r bo i l e rp l a t e 15 i s th e ground su ppor t equ ipment GSE l i s t ed i nAl l l i s t ed GSE has been shop - re l eas ed and a pproved by NASA.

Table 7-2. Ground Suppor t EquipmentModel No.414-001

A14-007

A1 4 - 009

A14-011

A14- 02 0

~

N o m e n c l a t u r eLaunch escap e t owersubs t i t u t e un it

LES op t i ca l a l i gnments e t

Space cra f t ada p te rc o v e r

Ground cool ing car t

S / M c o v e r

P a r t No.G16-820301-201

(315-824040

G18-828001

ME-362-0002-0001

G17-828003

De scr i pt io n3 r o v i d e s e l e c t r i c a l i n t e r f a c e n o r -n a l l y p r e s e n t e d by LES to the:ommand module .Zonsis t s of two pie ces ; a te lesco peidap te r and a t a rge t . The se t p ro-Iide s m ea ns of a l igning thr us tJec tor of LE motor i n r e l a t i on t o:ro ss CG of ab or t configurat ion.4 l ightweight, synth et ic , i inp reg -i a t e d , f a b r i c r a i n c o a t t o p ro t e c ti dap t e r f ro in sand , dus t , r a in , andsa l t sp ray .The ca r t wi l l f i l t e r , cool , dehu-: ii id ify, o r hea t ambien t a i r t o su i t -able l eve l fo r i n t roduc t ion i n tointe r io r of command modu le .A l ightweight, synth et ic , im pr eg -nated fabr ic f i t ted to conform toshape of S / M and used to p ro t ec tS / M f r o m s a n d , r a i n , a n d s a l t s p r a .dur ing handl ing, t r an s por ta i on ands t o r a g e .

7-3


71/119

vlodel No .i 1 4 - 0 2 1

914-024

414-026

A1 4- 02 7

A1 4- 076

c 1 1 - 1 1 2

C l 1 - 1 3 5

C14- 186

SM2A- 0 7-B P 1 5

Table 7-2. Ground Suppor t Equipm ent (Cont )~~ ~ ~~

Nomenc la tu reLaunch vehicle su bst i -tute unit C1

F l u i d a n d e l e c t r i c a lumbi l i ca l d i sconnec t se t

Ca p and plug s et

Ada pter cap and plugs e t

Spacecra f t GSEc r o sovc r di s t r ibutu rR a d a r t r a n s ponclc r andr e c o v e r y b e a c o nchccliout unit

Signal condit ionerc o n s o l e

E l e c t r i c a l c a b l e s e t

;16-82 1300

316-828010- 101

314-828012-301

318-828002

516-853056

516-852900