Vehicle Test Plan Apollo Mission A-004 Spacecraft 002

8/6/2019 Vehicle Test Plan Apollo Mission A-004 Spacecraft 002

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Copy No.47 SI D 64-2174VEHICLETESTPLAN

APOLLOM ISS ION A-004

(U)SPACECRAFT 002 I

NAS9-15029 January 1965

Exhibit I, Paragraph 3. 3

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This document contains i ing the national defense of theUnited States within the Espionage Laws. Tit le 18 U.S.C.Section 793 and 794. Its revelation of its contents in anymanner to an unauthorized pe d by law.

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N O R T H A M E R I C A N AV I A T IO N , I N C SPACE U rd INFORMATION SYSTEMS DIVISION

T I T L E O F D O C U M EN T L l B R A R Y U S E O N LY

Vehicle Te s t P la n

Apollo M ission A-004Spacecraf t 0 0 2

AUTHOR ( 5 )

CODE O R I G I N A T I N G A G E N C Y A N D O T H E R S O U R C E S D O C U M E N T N U M B E R

Development Analysis dept

29 January 1965 1 NAS9-150

t-

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Con t r ac tua l l y r equ i r e d veh ic l e t e s t p l an

This document def ines the engineer ing tes t r e q u i r e m e n t s a n d t z s t p l an sfor Apol lo Po wer -On Tumbling Bound ary Abort M ission A-004. It wil lbe the bas i c document for NASA prepa ra t i on of the mi ss io n d i r ec t i ve fort h i s t e s t .

F O R M 1 s t -V R E V 1 1 - 6 4P U B L I C AT I O N S U S E O N LY


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FOREWORD

Thi s docum en t de s c r i b e s t he r e qu i r em en t s andpla ns fo r the pre pa ra t io n and conduct ion of the Apollopower-on tumbl ing boundary p lanned abor t miss ionwi th Sp acec r a f t 002.per for me d a t the White Sands Mis s i l e Range a s thes ix th and f ina l t e s t in a s e r i e s of f l ight t e s t s of the

Apollo vehi cle lau nch e scape configurat ion.vehic le conf igura t ion a t l aunch wi l l cons i s t of aspacec r a f t l aunch e scap e su bsys t e m wi t h cana r dsand boos t p r o t ec t ive co ve r, spacec r a f t com m and andse r v i c e m odu l e s , a spec i a l adap t e r f o r s e r v i ce m odu let o boos t e r t r ans i t i on , and a Li t t le Joe I1 boost vehicle .

The miss ion is scheduled to be

The

Major cont r ibut ions to th i s document w er e furn i shedby Sys tem. Dynamics , Development Ana lys i s , S t r uc t ure sand M ate r ia l s Development Analys i s , Sys te ms In tegra-t ion, and Apollo Te st and Ope rat ion s.

Comm ent concerning th i s document should bedi rec t ed to the Tes t Req ui rem ents Sec t ion of Apol loDevelopment Analysis Engineering, N U , Downey ,exten s ion 3622 or 3623.

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CONTENTS

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INT RODUC TION .1. 1 P u r p o s e .1 . 2 P r e c e d e n c e of Documents .1. 3 Defin i t ions .

FLIGHT TEST OBJECTIVES .2. 1 M i s s i o n S u m m a r y .2. 2 Te s t O b j e c t iv e s

.TEST OBJECTIVE EVALUATION CRlTERIA3. 1 F i r s t - O r d e r Te s t O b je c ti ve C r i t e r i a3. 2 S eco n d -O rd er Tes t O b jec tiv e C r i t e r i a3. 3 T h i r d - O r d e r Te s t O b j ec t iv e C r i t e r i a

TEST VEHICLE CONFIGURATION .4. 1 Ve h ic le S u b s y s t em P r i o r i t i e s .4. 2 Veh ic le Descr ip t ion Sum ma ry .4. 3 M a s s P r o p e r t i e s D a ta .

FLIGHT CONSTRAINTS .MISSION RULES SUMMARY .SCHEDULE .VEHICLE CHECKOUT PLAN .

8. 1 Vehicle Pr ep ar at io n (%ID, Downey) .8 .2 Checkou t Oper at ion P la ns (Downey) .8. 3 Veh ic l e P rep a ra t io n (WS MR ) .8 . 4 F i e l d O p e r a t io n Plans (WSMR) .

FLIGHT TRAJECTORY REQUIREMENTS9.1 Tr a j e c t o r y D e si gn G r o u nd R u l e s9 .2 A b o r t E n v e lo p e .9. 3 Cont ingencies , .9 . 4 G ro u nd R ea l -T im e D isp lay .9 .5 R an g e C o v erag e P lo t s

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FLIGHT PLANS .10. 1 Mi ss i on Desc r i pt i on .10. 2 M i s s i o n Tr a j e c t o r i e s .10.3 Sequence of Even t s .10.4 Opera t iona l Tim e Lines .

POSTFLIGHT OPERATIONS .11.1 Reco ve r y Pe r sonne l and Equ ipm en t

11. 2 Exam ina t ion and Reco ve r y P r o ced ur e .equ i r em en t s .

APOL LO DATA REQUIREMENTS .12.1' Onboard Data

1 2 . 2 Ext e r na l Da ta12 . 3 Data Acq uisitio n . . I .

TEST REPOR TS .13.1 MSC Re po rt s13. 2 NAA-AT0 F i e l d Repor t s .13. 3 NAA Engineer ing Re por t s .

RANGE AND PAD SAFET Y14. 1 Range Safety .14.2 Pa d Safety

GROUND SUPPORT EQUIPMENT .15. 1 GSE Requi re men ts . . * .15.2 GSE Loca tions .15. 3 Fie ld Si te Suppor t Requ i reme nts .

GENERAL REQUIREMENTS .16. 1 S t r u c t u r a l D e si g n C r i t e r i a16. 2 Env i r onm en ta l Requ i r em en t s .16. 3 Handling and Transpor ta t ion Requi rem ents .16. 4 Elec t r oma gnet ic Compat ib i li ty

Requ i r em en t s

REFERENCES .APPENDIXESA. DEFINITIONSB. MISSION RULES .C. WSMR AP OL LO FLIG HT PROGRAM

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ILLUSTRATIONS

F i g u r e

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3-104 -14-24 - 34 -44-5

4 -64-74-87 -18-18 -28 -38 -48-58 - 69 -1

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C M In te rn a l Measu rem en t L o ca t io n s . .L au nch E sc ap e S u b sy s tem Mea su rem en t L o ca t io n sCM Outer Heat Sh ie ld S t ra in Gage Locat ionsCM In n er S t ru c tu re - F o rw ar d S idew all L o n g ero n 4

Str a in Gage Locat ions on Longerons 2 an d 8St ra in Gage Locations on Right -Hand Be am s of

SM A c c e l e r o m e t e r a n d F l uc tu a ti n g P r e s s u r e

SM Tem p er a tu r e an d S t ra in G age L o ca t io n sS id ew a ll a nd F o r w a r d H e a t S hi el d P r e s s u r e ,

A ft H e at S hi eld B a s e P r e s s u r e M e a s u r e L o c at io n s .S p acec ra f t 002 Stack Configuration ,Launch E sca pe Veh ic le Conf iguration .L au n ch E s cap e S u b sy s tem C o m p o nen tsTy p ica l T h ru s t -Tim e C u rv e of P i t ch C o n t ro l Motor .Ty p ica l T h ru s t -Tim e C u rv e of To w er Je t t iso n Mo to r

Ty p ica l T h ru s t -Tim e C u rv e of L au nch E sc ap e Mo to rMiss io n S eq u en cer S u b sy s temE l e c t r i c a l P o w e r D i s tr i b u ti o nActivity Schedule ,Downey Operations Schedule .Pr ela un ch Operat ional F low, Downey ,WSMR Operations Schedule .Pr ela un ch Ope rat ional F low, WSMR .Precoun tdown Task Sequence .Countdown Task Sequence .S a t u rn B o os t P r e l i m i n a r y Tr a j e c t o r y E n ve lo p e .P o w e r -ON Tu m b lin g B o u n d ary A b o r t P re l im in a r y

Ty p ic a l A lg ol T h r u s t Ve r s u s Ti m e ( P r e l i m i n a r y )Laun ch Comp lex 36, WSMR .Launch Site, WSMR .P r e l i m i n a r y M i s s io n P r o f i l e .L E V N o m in a l B oo st Tr a j e c t o r y P a r a m e t e r s

..

Stra in Gage Locat ions ..

Main Hatch .Measu rem en t L o ca t io n s . I .

.Te m p e r a t u r e , a n d H e a t F l u x M e a s u r e m e n t L o c at io n s .

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Envelope ..

( P r e l i m i n a r y ) .

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Fi gur e

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10-512-112 215-115-2c - 1

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Tab le

4 - 15 -18 -1

10-112-112-215-1B -1B -2B - 3c-1

L EV No m in al A b o rt Tr a j e c t o r y P a r a m e t e r s

L E V N o m in a l R e c o v e r y Tr a j e c t o r y P a r a m e t e r s

O p e r a t i o n a l P r e l i m i n a r y Ti m e L i n e s .O n b o ard In s t ru m en ta t io n N e tw o rk .O n b o ard C am era L o ca t io n .GSE R eq u i rem en t s a t DowneyG S E R eq u i rem en t s a t WSMR .WSMR Apol lo F l igh t P r o g r a m Vehicle Del ta

WSMR A p o llo F l ig h t P r o g ra m M iss io n A -0 0 4



Configurat ion .S u m m a r y .

TABLES

Weig ht , G rav i ty, an d In e r t i a S u m m a ry .F l ig h t C o n s t r a in t s .O p e ra ti o na l Te s t P r o c e d u r e s .N o m ina l S equ en ce of Miss io n E v ent s (P re l im in a ry )O n - B oa r d I n s tr u m e n t at i on S u m m a r y ( P r e l i m i n a r y )Sequen t ia l and Theodo l i te Track ing .Required GSE Uni ts .SC 002 and LJ I1 O p era t io n a l R ead in ess .O p era t io n a l R ead in ess of O n -B o ard In s t ru m en ta t io nO p era t io n a l R ead in ess of P h o to g rap h ic Track in g .WSMR Apollo F l igh t P ro g ra m Miss ion Object ives

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1 . 0 INTRODUCTION

1 . 1 PURPOSE

T h e " Veh ic l e T es t P lan , A po llo Miss io n A -00 4" p res en t s th e en g in ee r in gte s t r eq u i re m e n t s an d o b jec tiv es , t h e p l an s fo r v eh ic l e ch eck o u t p r io r t o th efl ight, t he t a s k s t o b e a c c om p l i s he d d u r i n g t he m i s s io n , a n d d a t a r e q u i r e m e n t san d r ep o r t in g p ro ce -d u res.th e mi ss i o n d i r e c t i v e .

T h i s in fo rm at io n w i l l b e u sed b y NASA t o p r e p a r e

1 . 2 PRECEDENCE O F DOCUMENTS

T h i s t e s t p la n t a k e s p r e c e d en c e o v e r a l l o t h e r c o n t r a c t o r r e p o r t s a ndd o cu m en t s co n ce rn ed w i th S p a cec ra f t 0 02 t e s t in g ; an d , i n tb rn , i t i s s u p e r -sed ed b y th e NASA P r o je c t A p o llo f li g h t m iss io n d i r ec t iv e fo r M iss io n A -00 4 .

1 . 3 DEFINITIONS

T e r m s u s e d i n t h i s d o c um e n t a r e d e fi n ed i n A p p en dix A.

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2.0 FLIGHT TEST OBJECTIVES

2. 1 MISSION SUMMARY

Apollo Mission A-004 wil l be a p l anned a bo r t m i s s i o n i n t he power- ontumbl ing boundary region .condi t ions in which the combined aerody nam ic and launch esc ape m otorexhaus t p r e s su r e s of t um bli ng abo r t i m posed on t he com m and m odu lesu r f ac e a ff ect a p r e s s u r e d i f f er e n t ia l a c r o s s t h e c o m m a n d m o du le o u t e rs t r u c t u r e ( o u t er s u r f a c e t o c a v it y b et we en i n n e r a n d o u t e r s t r u c t u r e s ) t h a tapp r oaches t he de s i gn l i m i t r ange of 9. 0 t o 11 . 1 p s i.a s s i gned f o r pe r f o r m an ce wi th Spacec r a f t 002 at WSMR; Spacecraft 010 isthe backup vehic le for the miss ion .launched by a Li t t l e Joe 11 boos t e r t o app r ox i m a t e l y 7 5 , 000 f ee t , at whichpoin t the a bo r t wi l l be in i t i a ted .j u s t be f o r e a bo r t i n i t i a ti on t o e nsu r e e scape veh i c l e t um bl i ng du r i ng t heabo r t . An apogee of appro xima te ly 120,000 fee t wi l l be reach ed.wil l cont inue up through the apo gee and down throu gh the uppe r regio n ofdescen t un t i l o r ien t a t i on and s t ab i l i z a t i on a r e accom pl i shed by t he c ana r d s .Dece lera t ion for vehic le touchdown and recov ery 42 m i le s f ro m the poin t ofl aunch wi l l be accompl i shed by the ea r t h l anding sub sys tem .

T h i s r e g i o n is def ined by ab or t in i t i a t ion

T h e m i s s i o n is

The launch esca pe vehic le wi l l be

A pi tch-up wi l l be per formed by the boos te r

Tumbling

2 . 2 TEST OBJECTIVES

The t e s t ob j ec ti ve s con ta i ned i n t h i s s ec t i on cons ti t u t e t he ach i evem en t sto be rea l i ze d through per for ma nce of Miss ion A-004. The te s t objec t ivesf o r a l l mi ss io ns of the Apol lo a bo r t f light pro gra m a t WSMR (ab or t thr oug hl au n ch e s c a p e s u b s y s te m p e r f o r m a n c e ) a r e p r e s e n t e d o n F i g u r e C - 1 ofAppendix C.

F i r s t - o r d e r t e s t o b je ct iv e s a r e a s follows:

1. Dem ons t r a t e s a t i s f ac t o r y l aunch e scape veh i c le ( LEV) pe r f o r m an cefo r an abo r t in the power-on tumbl ing boundary region

2. D e m o n s t r a te t h e s t r u c t u r a l i n t e g ri t y of t h e L E V a i r f r a m e s t r u c t u r ef o r a n a b o r t in the power-on tumbl ing boundary region

S e c o n d - o rd e r t e s t o b j ec t i v es a r e a s follows:

1. Dem on s t r a t e the capab i l i ty of t he cana r d subsys t em t o s a t i s f ac t o r i l yr eo r i en t and s t ab i l i z e t he L E V hea t sh i e l d f o r war d a f t e r a power-ont um bli ng abo r t

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2.

3 .

4.

5.

6 .

7.

Dem on s t r a t e the s t r u c t u r a l c apab i l i t y of t he p r oduc t i on boostp r o t ec t i ve cove r ( B P C ) t o withs tand the l aunch envi ronment

De t e r m i ne t he s t a t i c l oads on t he com m and m odu l e du r i ng t hel aunch and t he abo r t s equence

Dete rmine the dy namic loading of the comma nd module inne rs t r u c t u r e

De t e r m i ne t he dynam i c l oads and the s t r uc t u r a l r e s ponse of t heserv ice module dur ing l aunch

Dem ons t r a t e t he capab i li t y of t he com m and m odu le f o r war d hea ts h ie l d t h r u s t e r s t o s e p a r a t e t h e f o r w a r d h e a t s h ie l d s a t i s fa c t o ri l yaf te r the tower has been je t t i s oned by the tower j e t t i so n motor

D e t e r m i n e t h e s t a t i c p r e s s u r e s i m p o s e d o n t h e c o mm a nd m o d u leby f r e e - s t r ea m condi t ions and l aunch e scap e subs ys t em (LES)m ot or p l um es du r i ng a power-on tumbling abort

T h i r d - o r d e r t e s t o b j ec t iv e s a r e a s follows:

1 .

2 .

3 .

4.

5.

D e m o n s t r a te s a t i s f a c t o r y s e p a r a t i o n of t he l aunch e scape veh i c l ef r o m t he s e r v i c e m odu le

Dem ons t r a t e t he s a t i s f ac t o r y ope r a t i on and pe r f o r m anc e of t he

ea r t h l and i ng subsys t em (ELS) with a s p a c e c r a f t v e h i c le

Obtain da ta on the s t r uc tu ra l respo nse of the conimand moduledur i ng ea r t h l and i ng subs ys t em sequence

Obtain th erm al d a ta on the boos t pro tec t ive cover d ur ing a power-on tumbl ing abor t

Obtain acous t ica l noi se da ta ins ide the command module at a nas t r onau t s t a t i on

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3 .0 TEST OBJECTIVE EVALUATION CRITERIA

Thi s s ec t i on r e s t a t e s ve r ba t i m t he t e s t ob j ec t ive s of Sec ti on 2 . 0 ,des c r i b e s t he i s su es a s soc i a t e d wit h each ob j ec t ive , and spec i f i e s t he da t ap r ocu r em e n t i n s t r um en t a t i on and o the r docum en ta t ion m ed i a f o r r eco r d i ngthe accom plishm ent of object ive s.

Di ag r am s of t e s t veh i c l e i n s t r um en t a t i on po i nt s a r e i nc luded i n t h i ss ec t i on to a f f o r d g r ea t e r com pr ehens i on of i n s t r um en t a t i on l oca ti ons .d i ag r a m s , F i g u r e s 3 - 1 t h r ough 3 - 10 , a r e cop i e s of i l l u s t r a t i o ns i nSID 63-502, Apol lo Me asu rem ent Requ i reme nts , Spac ecraf t 002.

T h e s e

3. 1 FIRST-ORDER TEST OBJECTIVE CRITERIA

1. Objec t ive : Dem ons t ra te sa t i s fac tor y l aunch esc ape vehic le (LEV)p e r f o r m a n c e f o r a n a b o r t i n t h e p ow er -on tumbling boundaryregion .

Cr i t e r i a : Upon com m and t o abo r t , t he launch e scape subsys t em ( LES)wi l l be r e qu i r ed t o p r ope l t he space c r a f t con fi gur a ti on launch e s cape veh i cl eo n a n e s c a p e c o u r s e t o a saf e d i s tan ce beyond the s er v i ce module - Li t t l eJ o e I1 boos t e r s t a ck f o r de scen t and event ual r ecov e r y. S i nce L E V tumblingi s expec ted to commence at ab or t in i t ia t ion becau se of in s tabi l i ty c re a te d bya change in LEV angle-of -a t t ack (Li t t l e Jo e II pitchup), by a shi f t in thecen t e r of a e r odynam i c p r e s s u r e on t he LEV by e s cap e m o t o r exhaus t p l um eenvelopment, and by sho r t -d ura t ion th ru s t of the p i t ch cont ro l moto r, thee scap e m o t o r wi l l p r ope l the LEV f r om t he boos t e r i n a cu r v i ng t r a j ec t o r y.If the r a te of tumbling i s r a p i d o r i f motor combus t ion dura t ion i s appr ec i ab l e ,pa r t of esc ape mo tor t hr us t might be expended in dr iv ing the LEV backt owar d t he L i t t le Jo e I1 boos t e r. However, p r e l i m i na r y ana l y s i s i nd i ca t e stha t the maximu m tumbl ing ra te exp ec ted of the f i r s t tumble should be nog r e a t e r t ha n 90 d e g r e e s i n t h r e e s e c on d s .l aunch esca pe moto r wi l l be expended in l e s s than four seconds , a s indica tedo n F i g u r e 4-6 , it i s concluded th a t the L E V wil l be d r iven only on a c o u r s ed i ve rgent f r om t he boos t e r. The o r de r of d i s t ance between the LEV and theboos t e r r equ i r e d t o cons t it u t e s a t i s f a c t o r y abo r t pe r f o r m ance of t he LEVand t he o r d e r of t i m e du r a t i on r equ i r ed t o ach i eve t he nec es sa r y s ep a r a t i ona r e undef ined .

Since effective combustion of the

P r e l i m i n a r y a n a l y s i s a l s o i n d i ca t e s th a t t h e g r a v i t y f o r c e s i nd u ce ddur ing power -on tumbl ing should be wel l wi th in as t r ona ut l imi ta t ions .

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A t ti tu d e g y r o, r a t e g yr o , a c c e l e r o m e t e r , a nd e s c a p e m o t o r c h a m b e rp r e s s u r e i n s t r u m e n t a ti o n d a t a p l u s g r o un d s t a ti o ne d c i n e c a m e r a a n d c i n etheodol i t e recordings wi l l be obta ined to def ine the LEV t ra jec tory.supe r i m pos i t i on of t he LEV t r a j ec t o r y on t he Sa t u r n t r a j ec t o r y wi l l bea n a ly z e d f o r s u c c e s s f u l p e r f o r m a n c e a c c o m p l is h m e n t .pa r am e t e r s and cam er a and t heodo li te r eco r d i ngs m i nus t ha t of m o t o rc h a m b e r p r e s s u r e w i ll b e u s e d f o r a n a l y s i s of g r a v i t y f o r c e c h a r a c t e r i s t i c sand com p ar i son wit h a s t r onau t l i m i t a t i ons .s e n s o r s a r e i n di c at e d o n F i g u r e s 3 - 1 a n d 3 -2 .

The

Data of the same

Loca t i ons of LEV acce l e r om e t e r

2 . Objec t ive : Dem ons t ra te the s t ru c t ur a l in tegr i ty of the LEVa i r f r a m e s t r u c t u r e f o r a n a b o r t i n th e p o w er -o n t um b li n g bo u n da r yregion .

C r i t e r i a : The LEV i s expec t ed t o encoun te r s ev e r e ae r odynam i c ,

i ne r t i a l , and e scape m o t o r exhaus t b l a s t f o r c e s du r i ng power - on t um bli ng.T h e e x h au s t b l a s t f o r c e s on the conica l s ur fa ce of the co mmand module canbe e spec i a l l y g r ea t , s i nce t um bl i ng wi l l t end t o d r i ve one s i de of t he con i ca lsu r f ac e i nt o t he pl um e pa t t e r n i n a n o r m a l o r n e a r n o r m a l d i re c ti o n .exhaus t cone wi l l be augm en ted by f r e e s t r ea m p r e s su r e e x t e r na l of t he coneagain s t the d i rec t ion of tumble . The abi l i ty of t he veh i c l e s t r u c t u r e t ore m ai n in tac t in the tumbl ing envi ronment wi l l be ana lyzed f ro m photographicrec ord ing s of the on-board ca m er a shown in Figu re 12-2 and of grounds t a t i oned cam e r a s .

T h e

3.2 SECOND-ORDER TEST OBJECTIVE CRITERIA

1. Object ive : Dem ons t ra te the capabi l i ty of the can ard sub sys tem tosa t i s f ac t o r i l y r eo r i en t and s t ab i l i z e t he LEV hed t sh i e l d f o r wa r da f t e r a power-on tumbl ing abor t .

C r i t e r i a : The ca na r ds wi l l be dep l oyed 11 s econds a f t e r abo r tin i t i a t ion fo llowing esc ape motor burnout . However, end-over -end LEVtumbl ing i s expec ted to cont inue dur ing coas tup through the apogee and ondown i n t he de s cen t un t i l t he can a r d s becom e su f fi c ien tl y ae r odynam i ca l l ye f f ec ti ve t o a r r e s t t um bl ing and o r i e n t t he LEV wit h t he aft heat sh ie ldt o w a r d e a r t h . T h i s i s expec t ed t o occu r i n t he a l t i tude r ang e f r om 90, 000

t o 75 , 000 fee t . The LEV wi l l t hen p r obab l y osc i l l a t e about i t s t r i m a n g le -of - a t t a ck i n ne a r 180 - deg r ee sweeps and d i m i n i sh g r adua l l y wi th de c r ea s i n ga l t i t ude un t il s a t i s f ac t o r y s t ab i l i z a t i on i s ach i eved f r o m 50, 000 to 25 , 000f ee t a l t i t ude.p r o pe r dep loym en t of t he ea r t h l andi ng subsys t em ( ELS) pa r ach u t e s .

S t ab i li z at i on a n d p r o p e r o r i e n ta t i o n a r e n e c e s s a r y t o e n a bl e

T h e c a n a r d s a r e m e c h a n i z ed f o r d e pl oy m e nt a t 11 s econds a f t e rin i t i a t io n of any type of ab or t in which the LES i s employed.s e l e c t e d to a c c o m m o d a t e t h e t i m e - c r i t i c a l p ad a b o r t s e q ue n c e.

Th i s va l ue was

3 -2SID 64-2174


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-i/

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Y

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3 - 3

SID64-2174


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N O R T H A M E R I C A N AV IA T IO N , IN C . S PA C E an d INFORMATION SYSTEMS DIVISION

i ~ ~ - -

-ZY

TYPICAL FOR LA0215S, LA0216S, LA0217S,andLA0218S USIN G TWO GAGESPE R TOWER LEG

LEGEND0 Q BALL(3)@ TOWER ACCELEROMETER (2)@) PCM CHAMBER PRESSURE(1)@ LES MTR CHAMBER PRESSURE (1)@ TOWER STRAIN (4)@ CANARD DISPLACEMENT@ CANARD LINK STRAINS (2)@ FORWARD HS VIEW CAMERA

NOTE:LA LD ----AND LK----REFER TO MEASUREMENTSIN THE REQUIREMENT LIST.

NUMBERS

XL 352.04I

LA0201S &LAO202S I

cI\

LK0023HLK0024HLKOO25P

LAO01 AMOO 12A

\ D0012P

\ D0013PI

F i g u r e 3 -i2 . L a u n c h E s c a p e S uib sy ste m M e a s u r e m e n t L o c a t i o n s3 - 4

SID 64-2174


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Cana r d pe r f o r m an ce wil l be ana lyzed f r om a t t it ude gy r o , r a t e gy r o ,and acc e l e r om e t e r i n s t r um en t a t i on da t a pl us g r ound s t a t i oned cam er ar eco r d i ngs .

2. Objec t ive : Dem ons t ra te the s t r uc tu ra l capabi l i ty of the product ionboos t p r o t ec t i ve cove r ( BPC) t o withs tand the l aunch envi ronment .

Cr i t e r i a : The de s i gn pu r pose of t he BPC i s t o sh i e l d t he com m andm odu l e co n i ca l su r f ace f r o m ae r odynam i c hea t i ng du r i ng t he l aunch phase .Although the launch of thi s m iss io n wil l con st i tute only p ar t of the no rm alm i s s i on l aunch phase , t h i s wi ll be t he f i r s t t i m e t ha t a spacecraf t conf ig-ura t io n BPC wi l l be exposed to ac tua l l aunch envi ronment .nec es s a r y t o dem o ns t r a t e t ha t th r oughout th i s l aunch t he spacec r a f tcon f i gu ra t i on BPC r em a i ned i n t ac t wit h no pe ne t r a t i ons and r em a i ned i npos i t ion on the co mmand m odule .f r o m onboa r d t ower - i n s ta l l ed and g r ound- s t at i oned ca m e r a r eco r d i ngs .

3 . Objec t ive : Deter mine the s ta t i c loads on the comman d module

It wil l be

P e r f o r m a n c e of the BPC wil l be analyzed

I

dur ing the l aunch and the ab or t sequence .

Cr i t e r i a : S t at i c l oads a r e s t r uc t u r a l - t ype l oads of ve r y low f r equencyvar ia t ion .dynam i c , i ne r t i a l , and e scape m o t o r exhaus t b l a s t f o r ce s du r i ng power- ontumbl ing resul t ing in h igh s ta t i c loading of comma nd module s t ru c t ur a lm e m b e r s .module to be launched in f l ight, the load info rmati on obtained wil l be a b a s i s

of subs equen t comm and module design.du r i ng l aunch and abo r t wi l l be de t e r m i ned f r om s t r a i n i n s t r um en t a t i on da t a.The s t r a i n i n s t r um en t a t i on loca t i ons a r e i nd i cat ed on F i gu r e s 3 - 3 t h r ough

The command module i s e x p ec t ed to e n c ou n t er s e v e r e a e r o -

Since th i s wi l l be the f i r s t sp acecra f t conf igura t ion comman d

Command module s ta t i c loads

3 -6.

4. Objec t ive : Dete rmin e the dynamic loading of t he com m andm odu l e i nne r s t r uc t u r e .

C r i t e r i a : The command module wi l l be subjec ted to aero dyna micno i se , a cous t i c no is e , and m echan i ca l l y t r ansm i t t ed v i b r a t i on t h roughou tth e f l ight , each cont r ibut ing to the ov era l l dynamic load on the s t ru c tu re .

Aerodynamic noi se i s expec ted to be of gr ea te s t in tens i ty through thetransonic region of the launch phase.h i ghes t du r i ng LE S moto r burning . Dynamic loading and resp ons e cha rac -t e r i s t i c s of t he space c r a f t con f i gu r a ti on com m and m odul e s t r uc t u r e wi l l bed e t e rm i n e d f o r t he f i r s t t i m e f r o m v ib r a ti o n , a c c e l e r o m e t e r , a n d s t r a i ni n s t ru m e n t a t io n o n i n n e r s t r u c t u r a l m e m b e r s . S o m e of t h e i n s t r u m e n t e dpoin t s a r e indica ted on Fi gu res 3-1 and 3-4 through 3-6.

Acous t ic noi se probably wi l l be

3 -5

SI D 64-2174


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18/160


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N O R T H A M E R I C A N AV I A T I O N , I N C . S PA C E and I N F O RM AT I O N S Y S T E M S D I V I SI O N

CA1514S1

xc 80.75--

Xc 113.6-

I \ /

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NOTES:1. CA----S NUMBERS REFERTO

MEASUREMENTSIN THE REQUIREMENTLIST.

2. STRAIN GAGE CA0413SIS MO U NTED O NWEB OF LONGERON. ALL OTHERS AREMOUNTED O N OUTER ORINNER FACES.

F i g u r e 3 -4. C M I n n e r S t r u c t u r e - F o r w a r d S id e wa llL o n g e r o n 4 S t r a i n G a ge L o c a t i o n s

3 - 9

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F i g u r e 3-5. S t r a i n G a g e L o c a t i o n s o n L o n g e r o n s 2 a n d 8

3 - 1 0

SID 64-2174


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X, 61.7, CA0511SSECTIONA-A

F i g u r e 3 - 6 . S t r a i n G a g e L o c a t i o n s on R i g h t - H a n d B e a m of M a i n H a t c h

3 - 1 1

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5. Obj ec t ive : De t e r m i ne t he dynam i c l oads and t he s t r u c t u r a lresp ons e of the se rv ic e module dur ing l aunch.

C r i t e r i a : Ae r odynam i c no i s e and m echan i ca l v i b r a t i on wi l l beencoun t e r ed by t he s e r v i c e m odu l e du r i ng l aunch .ae r od ynam i c no i s e wi l l p r obab l y be encoun t e r ed t h r ough t he t r anson i cregion .l ike ly induce concen t ra t ion s of aerod ynam ic noi se and v ibra t ion on loca l iz edsu r f ac e a r e a s of t he s e r v i ce m odu l e wh ich wi l l a ff ec t the ove r a l l dynam i cl oad . Dynam ic l oadi ng and r e spo nse cha r a c t e r i s t i c s of the spacec r a f tcon f i gu ra t i on s e r v i ce m odu l e s t r u c t u r e wi l l be de t e r m i ned fo r t he f i r s t t i m ef r o m v i b r a ti o n a c c e l e r o m e t e r a n d s t r a i n i n s t r u m e n t a t i o n o n t h e s e r v i c e

The h ighe s t l eve l s of

The RCS engine quads , by the i r pro tub erant ins ta l l a t ions , wi l l

module .and 3 - 8 .

6.

Som e of t he i n s t r um en t a t i on poi n ts a r e i nd i ca t ed on F i g u r e s 3 - 7

Object ive:f o r w a r d h e a t s h i e l d t h r u s t e r s t o s e p a r a t e t he f o r w a r d h e a t s h ie ldsa t i s f ac t o r i l y a f t e r t he t ower ha s been je t t i soned by t he t owerj e t t i son m ot o r.

Dem ons t ra te the capabi l i ty of the comman d module

C r i t e r i a :t he t h r us t e r f i r i ng s i gna l 0 .4 s econds a f t e r t r ans m i s s i o n of t he LES j e t t i sonm ot o r f i r i ng s i gna l . Th i s de l ay of f o r w ar d com par t m en t exposu r e i s in t endedt o p r o t ec t t he ea r t h l andi ng equ i pm en t f r om t he boost p r o t ec t i ve co ve r a s itsweeps and b r ushes by t he f o r w ar d com par t m en t upon ex t r ac t i on by t he t owerdur ing LES je t t i son .i m m ed i a t e l y a f t e r LES j e t t i son i n o r d e r t o a l l ow am pl e t i m e f o r com m andm odu le dece l e r a t i on by pa r achu t e s e r i e s depl oym ent .sa t i s fa c to ry hea t sh ie ld e jec t io n wi l l be documented by ground photographicc o v e r age.

T h e m i s s i o n s e q u e n c e r s u b s y s te m i s m e c h a n i z ed t o t r a n s m i t

F o r w a r d h e a t s h i e ld e j e c t io n b y th e t h r u s t e r s i s r e q u i r e d

Demon st ra t ion of

7. Obj ec t ive : De t e r m i ne t he s t a t i c p r e s su r e s i m posed on t hecom m and m odu l e by f r e e - s t r ea m condi t ions and LES m ot o rp l um es du r i ng a power-on tumbl ing abor t .

Cr i t e r i a : Power- on t um bl i ng i n t he t um bl ing bounda r y r eg i on wi l ldr iv e one s ide of the com mand module conic a l sur fac e in to the l aunch

esc ape m o t o r exhaus t b l a s t i n a n o r m a l o r n e a r n o r m a l i m p in g e m en t ,r e su l t i ng i n hi gh p r e s s u r e i m pac t on t he su r f ace f ac i ng t he d i r ec t i on oftumble .t o c r e a t e a pr e s su r e d i f f e r en t ia l be t ween t h i s su r f ac e and t he sp ace cav i t yb e tw e en i n n e r s t r u c t u r e a nd o u t e r s h e l l ( v e n te d t o f r e e s t r e a m p r e s s u r e )t ha t app r oach es t he de s i gn l i m i t r ange of app r ox i m a t e l y 9 to 11 psi .

Ana l ys i s i nd i ca t e s t ha t t he se su r f ace p r e s su r e s m i gh t be su f f i c i en t

3-12

SID 64-2174


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Pr es su r e va l ue s on the com m and m odu l e ou t e r su r f ac e wil l be ob t a i nedf r om p r e s su r e i n s t r um en t a t i on po in t s i nd ica t ed on F i g u r e s 3 - 9 and 3 -10.P r e s su r e i n t he spac e cav it y be t ween i nne r and ou t e r s t r u c t u r e s wi l l bed e r i v ed f r o m r e f e r e n c e s t a t i c p r e s s u r e i n s t ru m e n t a t io n .

3. 3 THIRD-ORDER TEST OBJECTIVE CRITERIA

1. Objec t ive : Dem ons t ra te sa t i s fa c tory sep ara t ion of the l aunchescap e veh ic l e f r om t he s e r v i c e m odu l e .

C r i t e r i a :equi pped wi th t he com m and and s e r v i ce m odu le e l ec t r i c a l um bi l i c a l andplumbing hard l ines .u m b i l i ca l an d h a r d l i n e s m u s t b e p r o p e r l y c u t i n o r d e r t o a c h ie v e s a t i s -f ac t o r y com m and m odu le s epa r a t i on f r om t he s e r v i ce m odu le . Dem on-

s t ra t ion of th i s event wi l l be documented f o r analys i s by ground-s ta t ionedc a m e r a s . f

Spa cec raf t 002 wi l l be the f i r s t Apol lo f l ight vehic le to be

The ref ore , th i s wi l l be the f i r s t f l ight on which the

2. Obj ect i ve : Dem on s t r a t e t he s a t i s f ac t o r y ope r a t i on andpe r f o r m an ce of t he e a r t h land ing sub sys t em ( ELS) wi th aspacec r a f t veh i c l e .

C r i t e r i a : The s pac ecr af t 002 comma nd module wi l l be the f i r s t n e a r -con t r o l- we i gh t com m and m odul e t o be d ece l e r a t ed and r e t u r ne d t o ea r t hf ro m a c tua l f l ight by the ELS. The m ax im um descen t de s i gn r a t e ve l oc i t yof 33 fee t p e r s eco nd a t 5000-foot ele vat ion (4200-foot WSMR elev atio n) i s

req ui r ed to be achiev ed by two main pa rac hut es func tioning proper ly . Thedescen t r a t e i s expec t ed t o be app r ox i m a t e l y 26 f ee t pe r s econd wit h t h r eem a i n pa r achu t e s i n p r ope r f unc t ion ,cont ro l -weight comm and module wi l l be ana lyzed f ro m a t t i tude gyro , ra teg y r o, a n d a c c e l e r o m e t e r d a ta p lu s g r o u n d - s ta t i o n e d c a m e r a r e c o r d in g s .

ELS pe r f o r m an ce wi th the ne a r -

3. Objec t ive : Obta in da ta on the s t ru c tu ra l resp ons e of the commandm odu le du r i ng e a r t h l and ing subsys t em sequence .

C r i t e r i a : Pa r ach u t e dep loym en t shock suspens i on l oads a r e expec t edt o be loca l ized a round the forwa rd ha tch a r e a of the comm and module inner

s t ru c tu re . S ide loads a l so might be induced if pa r achu t e i n i t i a l l i ne s t r e t chocc u r s wh i le t he com m and m odu le i s i n a n osc il l a ti ng swing angl e f r om t hed i r ec t i on of de scen t . S t r uc t u r a l r e spo nse da t a on a spacec r a f t com m andmodule in ac tua l f l ight wi l l be obtained for the f i r s t t im e f ro m vibra t ion ,a c c e l e r o m e te r , and s t r a i n i n s t r um en ta t ion .

4. Objec t ive : Obtain th er ma l da ta on the boos t pro te c t ive cov erdur ing a power-on tumbl ing abor t .

3-15

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N O R T H A M E R I C A N AV I AT I O N , I N C . SPACE nd INFORMATION SYSTEMS DIVISION

N O T E

1e

CA---P NUMBERS REFER T OMEASUREMENTSIN THEREQUIREMENT LIST.

2. VIEW IS LO OK ING FORWARD.

F i g u r e 3 - 10 . A f t H ea t a i e l d B a s e P r e s s u r e M e a s u re m e n t L o c at io ns

3-19SID 64-2174


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N O R T H A M E R I C A N AV I AT I O N , I N C . S PAC E an d I N F O R MAT I O N S Y S T E M S D I V I S I ON

Cr i t e r i a : Th i s wi l l be t he f i r s t spacec r a f t con f i gur a t i on boost p r o t ec t i vecover to be ins ta l l ed on the command module for ac tua l f l ight .of the cove r wil l be ana lyz ed for e ffe ct iv ene ss of heat shield ing qual i t ies .Thes e da ta w i l l be ob t a ined f r o m t em p er a t u r e and hea t f l ux i n s t r um en t a t i onins ta l l e d on the c onica l sur fac e of the comman d module .i n s t r u m e n t e d p oi nt s a r e i n d i c a te d o n F i g u r e 3-9.

T h e r m a l d a ta

Loc atio ns of the

5. Object ive : Obta in acou s t ica l noi se da ta ins ide the commandm odu le a t a n a s t r onau t s t at i on .

Cr i t e r i a : Sound a t t enuat i on p r op e r t i e s a c r o s s t he spacec r a f tconf igura t ion comm and module s t r uc tu re i n f light wi l l be inves t ig a ted wi thda t a ob ta i ned f r o m acous t i c a l i n s t r um en t a t i on i n s i de t he command moduleon the center couch p la t form. The command module dec ib e l a l lowance int he speec h i n t e r f e r ence l eve l (300 to 4800 cycles per second) wi th a l l

equ ipm en t ope r a t ing i n no r m a l f l i ght i s 55 dec ibe l s .I

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4. 0 TES T VEHIC LE CONFIGURATION

4 .1 VEHICLE SUBSYSTEM PRIORITIES

Te s t Ve hi c le S u b s y s t e m s

L au n ch escap e su b sy s t em

Q -ba l lP i t c h c o n t r o l m o t o rL E S j e t t i so n m o to rL a un c h e s c a p e m o t o rC a n a r dTo w e rB o o s t p r o t e c t i v e c o v er

E a r t h l a n di n g s u b s y s t e m

D ro g u e p a rach u tesP i lo t p a rach u te sMain p a rach u tes

P r i m a r y s t r uc t u re s

C o m m an d m o d u leS erv ice m o d u leAdap ter

R e ten tio n an d sep a r a t io ns u b s y s t e m

C M-S M sep ara t io nC M-to w er sep a ra t io nC M- f o r w a r d h e a t s h i e l d

s e p a r a t i o n

S eq u en cer su b sy s e m

M i s s i o n s e q u e n c erTo w e r s e q u e n c e rELS s e q u e n c e r

Conf igurat ion

CompleteCompleteCompleteCompleteC o m p le eCompleteComplete

C o m p e t eCompleteCo mp l e t e

Go mp le eCompleteS imulated

CompleteC o m p 1 t eComplete

In te r imIn te r imComplete

P r - J r i t y

P r i m a r yP r i m a r yP r i m a r yP r i m a r yP r i m a r y

' P r i m a r yP r i m a r y

P r i m a r yP r i m a r yP r i m a r y




4 -1SID 64- 21 74


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Te s t Ve h i cl e S u b s y s t e m s

E l e c t r i c a l p ow e r s u b s y s t e m

Configurat ion

Ba t t e r i e s and power d i s t r i bu t i on

Comm unica t ion andi ns t r um en t a t i on subsys t em

Te l e m e t r y a n d a nt e nn aO n bo a rd r e c o r d e rEnd i n s t r um en t a t i on and s i gna l

C- band t r a nspo nde r and an t ennaC a m e r a

cond i t i one r s

Launch veh i c l e subsys t em s

Pr opu l s i onStabi l i za t ion and cont r olAbor t t i m e r

I n t e r i mI

I n t e r i mI n t e r i mI n t e r i m

I n t e r i mI n t e r i m

I n t e r i mI n t e r i m

P r i o r i t y

P r i m a r y

P r i m a r yP r i m a r yP r i m a r y a nd

s ec onda r yP r i m a r yP r i m a r y


See Appendix A for def in i t ions of te rmi nol ogy .

4 .2 VEHICLE DESCRIPTION SUMMARY

Det a i led i n f o r m a t i on on t he Spa cec r a f t 0 0 2 conf igura t ion i s defined indraw ings and pr oc es s spec i f i ca t ion s of the "Spacecraf t 0 02 Cont r ac t ua l End-I t em Specif icat ion" (SID 63-699) . Fi gu re 4-1 i s a d i a g r a m 6 f Spacec r a f t 002in the s tack conf igura t ion .

The p r i m ar y s t r uc t u r e s of Spacec r a f t 002 wil l be the l aunch esca pesubsys t em , t he sp acec r a f t con f i gu r a t ion com m and m odu le , and t he spacec r a f tcon f i gur a t i on s e r v i ce m odu l e . Equ i pm en t f o r veh i c l e e scape f rom the boos te rand f o r e s cap e sub sys t em j e t t i son f r o m t he com m and m odu le w i l l be containedi n t he l aunch e scape subsys t em .sequence r subsy s t em , r e t en t i on and s epa r a t ion subsy s t em , ea r t h l and ing

s u b s y s t e m , e l e c t r i c a l p ow e r s u b s y s t e m , a n d co m m u n ic a ti o n a n d i n s t r u -m en t a t i on subsys t em .r eac t i on con t r o l subsy s t em quads , a blas t sh ie ld , a n d a n a d a p t e r m a t in gr ing fac i l i t a t ing serv ice module ins ta l l a t ion wi th the Li t t l e Joe 11 boos t e r.

The command module wi l l house the

The s er v ic e module wi l l be equipped wi th s imul a ted

The f ol lowing a r e t he m ode l and gen e r a l a s s em b l y d r awi ngs app l i cab let o t he Spacec r a f t 002 vehic le .

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10:

PITCH CONTROLMOTOR

TOWER JETTISONMOTOR

LAUNCH ESCAPE MOTOR

LAU NCH ESCAPESYSTEM TOWER

COMMANDMODULE

AN D EXTENSION SIMULATED RCS

PACKAGE

BOOSTER A NDINSTRUMENT

FINS SHOWN ROTATED45 DEGREES FROM t-w*om fN'piTRUE CONFIGURATION TO CLARIFY STACK

F i g u r e 4 - 1. Spa cec raf t 002 S tack Conf igurat ion

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End I temG e n e r a l A s s e m b l y

Drawing No.Mode l Se r i a l No. ISpacecraf t s t ack

Launch e scape subsys t em

Command module

Se r v i ce m odu le

V14-3- 002

V15-3-9

V16-3-2

V 1 7 - 3 - 11

V 14-000002- 121

V 15- 000002- 121

Vlh-000002-121

V17-000002-701

Ear t h landi ng subsy s t em I V16-3-2 I V16-5760034 . 2 . 1 Launch Esca pe Subsys t em

The l aunch e scape subsys t em f o r Spacec r a f t 0 02 w i l l be a s t r u c t u r a ltowe r se cu re d onto and ov er the apex of the com mand module and sypp ort inga tub ular cas ing enc los ing the fo l lowing components :

Q -ba l l i n s r ume ntat ion packageP i t ch con t r o l m o t o rJe t t i son m ot o rE s c a p e m o t o rC a n a r d a i r f o i l sBa l l a s t

Th i s con f i gu ra t i on i s shown on F i gu r e 4 - 2. The boost p r o t ec t i ve cove r f o rthe command module i s a l s o cons i dered a par t of the l aunch esc ape sub-sys tem . Al l components l i s t ed , inc luding the tower, have ,been des ig na tedp r i m ar y un i t s of t he subsys t e m .subsy s t em o r i en t a t ion wi th t he r e f e r ence ax i s subsy s t em i s pr e sen t ed onF i gu r e 4 - 3 .

A di ag ra m of LES compo nents and

4.2 . 1 . 1 Q-bal l Assembly

The Q- ba l l a s s em bl y cons t i t u t e s t he ou t e r m os t t i p of t he l aunch e s capesubsy s t em whi ch i s m os t r e m o t e f r om t he com m and m odu le .t r ansduce r s and a s soc i a t ed a t t a chm en t s and wi r i ng t o s ense a i r p r e s s u r eand a i r f l ow d i r ec t i o n th r ough po r t s i n t he Q- ba l l su r f ace .ang l e of s i de s li p , and dynam i c p r e s su r e wi l l be de r i ved f r o m t hem e a s u r e m e n t s ,

I t co nsi s ts of

Angle of a t tack ,

4 . 2 . 1 . 2 P i t ch Con t r o l Mot o r

Si tua ted below the Q-ba l l i s t he so l i d - p r ope l l an t p i tch con t r o l m o t o rt o f u r n i sh a m om ent a r y t h r us t no r m a l to t he l ong i tud i na l ax i s of the l aunchesc ape subs ys t em t o fac i l i t a t e down-r ange e scap e du r i ng abo r t . However,

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. -

i t s t h r us t h a s i nconsequen t i a l e f f ec t i n a power -on tumbling bounda ry ab ort .The p i t ch con t r o l m o t o r i s igni ted with igni t ion of the laun ch es ca pe mo to ra t abor t i ni t ia t ion . The p i tch m o t o r de s i gn t h r u s t - t i m e cu r ve i s con t ai nedon F i gu r e 4 - 4 .

4 . 2. 1 . 3 J e t t i son Mot o r

The tower j e t t i son so l i d - p r ope l l an t m o t o r p r ope l s t he en t i r e l aunchescap e sub sys t em p l us t he boost p r o t ec t i ve cove r away f r om t he com m andm odu le p r ep a r a t o r y t o pa r achu t e dep l oym en t f o r r ecove r y.two canted exhaus t nozz l es powers the l aunch escape subsy s tem on a curvingt r a j ec t o r y. The m ot o r de s i gn t h r us t - t i m e cu r ve i s con t ai ned on F i gu r e 4 - 5 .

Thr u s t t h r ough

4 . 2 . 1 . 4 Esca pe Mot or

The launch e scap e so l i d - p r ope l l an t m o t o r g ene r a t e s t h r us t t h r oughfour canted exhaus t nozz les to prop e l the l aunch escap e vehicde on an escap ecour s e away f r om t he boos t e r.conta ined on Figur e 4-6 .

The m ot o r de s i gn t h r us t - t i m e cu r ve i s

4 . 2 . 1 . 5 C a n a r d s

The cana r ds cons t i t u t e a pa r t of t he l aunch e scape subsys t em andcon sist of two deployable su rfa ce s and an actuat ing and locking me cha nis mloca ted in the LES ju s t below the Q-ba l l .pos i t ion fo rm a por t io n of the LES upper cy l indr ic a l cas ing . They ac t a s

a i r f o i l s upon deployment a t 11 seconds a f t e r abo r t in i t ia t ion to subsequent lyor ient and s tab i l i ze the l aunch escape vehic le aft hea t sh i e l d t owar d ea r t hf o r r e c o v e r y.

The cana r d s u r f ace s i n t he s t owed

4 . 2 . 1 . 6 E s c a p e To w er

The l aunch e sc ape t ower i s an open f r am e s t ru c tu re of welded t it an iumIt i s t h e i n t e r m e d i a t eub i ng i n t he f o r m of a t r unca t ed r ec t angu l a r py r am i d .

s t r u c t u r e be t ween t he com m and m odul e and t he e scape subsy s t em r ocke tm o t o r s .m i n i m i ze ae r odynam i c hea t i ng du r i ng boost and to m i n i m i ze r ocke t exhaus thea t ing dur ing abor t .a t t a chm en t t o the uppe r ba s e of t he t ower. The a t t a chm en t s a r e ad j us t ab l ef o r t h r us t a l i gnm en t .four poin t s by quick re lease dua l -mode exploding bol t mechanisms .

An ab l a t i ve The r m ol ag m a t e r i a l i s appl ied onto the tower to

A s t r uc t u r a l sk i r t f a c i l i t a t e s l aunch e scape m o t o r

The tower base i s secured to the command module a t

4 . 2 . 1 7 Boos t P r o t ec t i ve Cove r

The boost p r o t ec t i ve co ve r e nc l ose s the en t i r e con i ca l su r f ace of t hecom m and m odu l e t o p r o t ec t it f r o m ae r odynam i c hea t i ng du r i ng h i gh / Mach

4-7

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3000

2500

2000

h

m-1

v

15005PI:

I-I

1000

500

0

PROPELLANT GRAIN TEMPERATURE 70 F

0.3 0.6 0.9 1.2 1.5

TIME (SEC)

F i g u r e 4 - 4 . Ty p i c a l T h r u s t - Ti m e C u r v e of P i t ch C o n t ro l Mo to r

4 - 8SID 64-2174

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N O R T H A M E R I C A N AV I ATI O N , I N C . SPACE and 1NM)RMATION S Y S TEM S DIVISION

U

8

(e1 0001) S r l l H l

4 - 9

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0


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200

180

160

140

120

h

m-1

00 too0

!z2

Y

II-

80

60

40

20

0

PROPELLANT GRAIN TEMPERATURE 70FAND VACUUM CONDITIONS

- \

-

I I0 1 2 3 4 5 6 7 8 9 10

TIME (SEC)

Figure 4-6 . Typica l Thr us t - Ti m e Cur ve of Launch Escape Motor

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N O R T H A M E R I C A N AV I A T IO N , I N C . S PA C E an d INFORMATION SYSTEhlS DIVISION

num ber - h i gh dynam i c p r e s su r e l aunch .f ab r i ca t ed i n s even s ec t i ons .honeycomb f ib erg lass wi th an outer ab la to r whi le the a f t por t ion i s ofTef lon- impregnated sof t f ib erg lass c lo th wi th a n abla t iv e sur fac e of co rk .

The cov er wil l be pul led off the comman d module by the tower dur ing launchescap e sub sys t em j e tt i son .

The soft por t ion of the c ove r i sThe f o r war d pa r t of t he co ve r i s of ha r d

4 .2 .2 Ea r th Landing Subsys tem

The ea r t h l and ing subsys t e m com pr i s e s the d r ogue pa r achu t e sub -sys t em , t he pi l ot pa r achu t e sub sys t em , and t he m a i n pa r achu t e su bsys t e m ,

4 . 2 . 2 . 1 Drogue Pa r ach u t e Subsys t em

Two 13. 7-foot d i a m e t e r f i s t r ibbo n nylon par ac hu te s and two deployment

m o r t a r s cons t i tu t e m a j o r pa r t s of t h i s subsys t em . Mo r t a r f ir i ng dep loym entof both drogue chutes occu rs two secon ds a f te r LES je t t i son;wi l l be in the 40-p ercen t reefed conf igura t ion t o mini mize opening shock unti ld i s r ee f i ng occu r s e i ght s econds a f t e r l i ne s t r e t ch .r e l ea se d f r om t he com m and m odu le a s t he veh i c l e de scends th r ough 11 , 000feet at t i tude.

Both chutes

Both d rogue s wi l l be

4 . 2 . 2 . 2 P i l o t Pa r ach u t e Subsys t em

T h r e e 7 . 2 - foo t d i am e t e r r i ng s l o t pa r ach u t e s and t h r e e dep loym en tm or t a r s cons t i t u te t he m a j o r pa r t s of t h i s subsys t em .deploymen t of a l l th re e p i lo t c hutes oc cur s wi th the 11 , 000- foot a l t i tudepa r a l l e l s i gna l t ha t r e l ea se s t he two d r ogue chu t e s.one main para chute bag o ver boa rd to fu l l ex tens ion , of the m ain chute r i s e r sbefor e m ain chute deployment.m a i n c h u te s .

M o r t a r f i r in g

Each p i lo t chute pul l s

The p i lo t chu t e s r em a i n a t t a ched t o t he

4 . 2 . 2 . 3 M a in P a r a c h u t e S u b sy s te m

T h r e e 83 . 5 - foot d i am e t e r open - r i ng r i ng sa i l pa r achu t e s cons t it u t eEach m a i n chu t e i s deployed in the n ine percent reefedh i s s u b s y s te m .

conf igura t ion to m inim ize opening shock.a f t e r l i ne s t r e t ch .

Dis reef ing occ urs e ight seconds

4 . 2 . 3 P r i m a r y S t r u c tu r e s

The com m and m odu le , t he s e r v i ce m odu l e , and t he s e r v i c e m odu leL i t t le Jo e I1 adap t e r f o r i n t e r f ace wi th t he L i t t le Jo e 11 b o o s t e r c o m p r i s et he p r i m ar y s t r uc t u r e of Spacec r a f t 002.

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4 . 2 . 3 . 1 Com m and Modu le S t r uc t u r e

The command module i s cons t ruc ted of a cons tant -depth , bra zed -honeycomb, s te e l out er sh e l l and a bonded-aluminum honeycomb inners t r u c t u r e ,com par t m en t t h e r m a l p r ot ect i on .m a t e r i a l .com par t m en t hea t sh i e l d, t he c r e w com par t m en t hea t sh i e l d , and t he a ftcom par tm ent hea t sh ie ld . The for war d hea t sh ie ld i s a comple te conica lun i t s ec u r ed t o t he i nne r s t r uc t u r e a t f ou r po in ts . T he c r e w c o m p a r t m e n thea t sh ie ld conta ins numerou s cutouts fo r ac ce ss pane l s , windows, and thecr ew ha tch . The aft heat sh ie ld i s a continuous unit s e c u r e d t o th e i n n e rs t r uc t u r e by t ens i on bo l ts .t h r ough t h i s hea t sh i e l d t o t he i nne r. s t r uc t u r e .

The ou t e r she l l con t a in s a l ayer of cork coa t ing for c rewThe co r k s i m u l a t e s t he spacec r a f t ab l a t i ve

The outer she l l i s d iv ided i n t o t h r ee m a j o r s ec t i ons : t he f o r wa r d

T he b o o s t er t h r u s t i s t r a n s m i t t e d d i r e c t l y

T h e in n e r s t r u c t u r e i s the load-bea r ing a r t i c le of the command module ;i t conta ins a forward bulkhead, f o r war d and a ft s i dewa l l s , and a f t bulkhead.Four cont inuous longerons suppor t the l aunch escape subsys tem a t theforwa rd end, and the se p lus addi t iona l longerons in the aft s i de wa l ld i s t r i b u t e t he l aunch boos t e r t h r us t l oad,t he f o r war d bu lkhead d i s t r i bu t e the i n t e r na l p r e s s u r e , f o r war d hea t sh i e l de jec t io n load , drogue and p i lo t chute m o r t a r loa ds , and main parachutea t t a chm en t l oads . The num er ous cu tou t s co r r e s pond t o t hose i n t he ou t e rshe l l .

F o u r s t r u c t u r a l b e a m s a t t ac h e d t o

B oth t h e o u t e r s h e l l an d t h e i n n e r s t r u c t u r e a r e s y m m e t r i c a l a bo ut a

com m on cen t e r l i ne .

4 . 2 . 3 . 2 Se r v i ce Modu le S t r uc t u r e

The Spacecraf t 002 serv ice module wi l l be a spacecraf t conf igura t ions e r v i c e m o d ul e s t r u c t u r a l s h e l l o nly.s epa r a t i on appa r a t us , s i gna l d i s t r i bu t i on un i t s , t ape m odu la ti on packages ,t ra ns du ce rs , and am pl i f i e r s wi l l be the only equipment conta ined wi thin these r v i ce m odul e. The she l l i s cons t ruc ted of one - inch a luminum honeycombi n s i x s e g m e n t s . I t s d i a m e t e r i s 154 inche s , an d it i s 155 inche s long.Nonf i r ing s im ula ted re ac t ion c ont ro l subs ys tem (RCS) engine quads wi l l be

i ns t a l l ed on t he ex t e r i o r s u r f a ce of t he s e r v i ce m odu le .

Com m and and s e r v i ce m odu le

4 . 2 . 3 . 3 Se r v i c e Modu le - Li t t l e Joe I1 Adap t e r

A 15- i nch l engt h ex t ens ion adap t e r she l l i n t e r f ace s wit h t he s e r v i cemodule at one end and wi th the Li t t l e Joe I1 boos t e r at t he o t he r i n o r d e r t oach i eve t he neces sa r y d i m ens i ona l t r ans i t i on . A p r e s s u r e b a r r i e r m o un te d

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ac r o s s the adap t e r i n s i de d i am e t e r sh i e l d s the com m and m odu le f r omLi t t l e Joe I1 des t r u c t b l a s t p r e s su r e , shou ld de s t r uc t i on becom e neces sa r y .

4.2.4 Retent ion and Separa t io n Subs ys tem

Spacec r a f t 002 wil l conta in the capabi l i ty for re te nt ion and sepa ra t i onof (1) he command module and the serv ice module , (2) he l aunch e scapesubsy s t em and t he com m and m odu le , and ( 3 ) t he f o r war d hea t sh i e l d and t hecommand module .

4.2.4. 1 CM-SM Retent ion and Sepa ra t ion

Thr ee t ens i on t i e r ods , e ach connec t ed t o a mounting plate and si tuatedappr ox i m a t e l y 120 deg r ee s ap a r t a r ound t he pe r i phe r y of t he com m andm odul e ba se, s ec u r e t he com m and m odu l e t o t he s e r v i ce m odul e s t r uc t u r e .

Each t i e rod co nta ins two shaped explos ive c har ges tha t de tona te toge th erto f r ac tu re the rod (de tonat ion of a s i ng l e cha rg e i s su ff i ci en t t o f r a c t u r ethe rod) and toge th er wi th sev era nce of the e lec t r i ca l umb i l i ca l and p lumbingha rd l ines be tween the command module and ser v ic e module by cut te r s , thecommand module i s com pl e t e ly d i sj o i ned f r o m t he s e r v i c e m odu le and f r eet o be s epa r a t ed by l aunch e scap e m o t o r t h r us t .

4.2.4.2 LES-CM Retent ion and Sepa ra t ion

T h e la u nc h e s c a p e s u b y s t e m i s s e c u r e d t o the command module throught he e scape t ower a t i t s f ou r ex t r em i t i e s by dua l- m ode bo l t s .

by s e l f - con t a i ned r edundan t exp l os i ve cha rg es i s a ccom pl i shed t o f r ee t heen t i r e l aunch e scape sub sys t em and t he boost p r o t ec t i ve cove r f o r s epa r a t i onby the j e t t i son m ot o r.

Bo l t f r ac t u r e

4.2.4.3 Fo rw ar d Heat Shield-Command Module Retent ion and Sepa ra t ion

Four t ens i on t i e r ods , e ach connec t ed t o a t h r u s t e r - e j e c t o r a s se m bl y ,The f ou r t h r us t e r -ec ur e the for wa rd hea t sh ie ld to the command module .

e j ec t o r s a r e s i t ua t ed a r ound the ex t e r i o r of t he f o r war d eg r e s s t unne l atappr ox i m a t e l y 90 d e g r e e s a p a r t .e ach gene r a t o r ope r a t i ng two t h r u s t e r s 180 deg r e e s apa r t .o c c u r s 0.4 seconds a f te r j e t t i son motor igni tion , f rac tur ing the t ens io n t i er ods and e jec t i ng the hea t sh i e l d f r o m t he com m and m odu l e.

Tw o g a s g e n e r a t o r s o p e r a te t h e t h r u s t e r s ,T h r u s t e r f i r i n g

4.2. 5 Sequencer Subsys tem

Ev ent s of power-on tumbling boundary abo r t mis s io n A - 0 0 4 will be

A bl ock d i ag r am of t he s equence r subsy s t em i s p r e sen t ed onschedu led by t he m i s s i on s equence r, the EL S sequ encer, and the towers e q u e n c e r.F i g u r e 4-7.

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r---

LJ - lI

1 r--------_ . - - - - - A

IIIIIIII

IIL

I IPITCH-UP I I

II

IIGNALI

- - - - - - - -

ABORTTIMER

BACKUP ABORTLIFT-oFF IMER BOX

. RANGE SAFETY' RADIO COMMANDL ABORT SIGNAL

(IF REQUIRED)

SIGNALSFROM BLOCKHOUSE1 . ACTIVATE GSE ABORT LOCKOUT RELAY

ARM L O GI C AN D PYRO BUSES2. LAUNCH COMMANDTO LJ II3. LIFT-OFF, T - 0 GSE ABORT LOCKOUT DEENERGIZE)

11-SECTIME DELAY

ll-SECTIME DELAY

I UMBlLICAL I

I CHARGE) I

IIRE CM-SM

SEPARATION SYS

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(C ON M CTOR)

FIRE PITCHCONTROLMOTOR

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tI


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BAROMETRIC SWITC H BAROMETRIC SWITCH

I

TOWERILTS


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11,000-FTYITCH BAROMETRIC SWITCH

B

2-SECTIME DELAY

.au

2-SECTIME DELAY

1 1

1-1 I

1I

- I& I

I1P

I I

I

I

"DROGUESDEPLOYED

REEFED

TIME DELAY TIME DELAY

DISREEFDROGUES

8-SECTIME DELAY

F i g u r e


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8!


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4 . 2 . 5 . 1 Mi s s i on Sequence r

T h e m i s s i o n s e q u e n c e r f u r n i s h e s t h e s i g n a ls f o r c o m m a nd m o d ul esepa r a t i on f r o m t he s e r v i c e m odu l e, c ana r d depl oym en t , f o r wa r d hea t

sh i e l d t h r us t e r f i r i ng , and s a f i ng and a r m i n g of t he t ower and ELSs e q u e n c e r s .s equence r, bu t it wil l be shunted nonfunct ional fo r M issi on A-004.t i m er w i l l be of the sa me conf igura t ion a s tha t on Boi le rp la te 22 .

An a b o r t b ac ku p t i m e r c o n s t it u t e s a pa r t of t he m i s s i onThe

4.2.5.2 Tower Sequ encer

The t ower s equence r i s s i tua ted in the comm and module on Spacecraf t002. It cons i s t s of r e l ay s wh ich r ece i v e s i gna l s f r o m t he m i s s i on s equence rand , upon c l o su r e , a l l ows e l e c t r i c a l power f r om pyro t echn ic ba t t e r i e s t oene rg i ze squ ibs and i gn i t e r s fo r f i r i ng t he launch e scape , p i t ch con t r o l , and

je t t i son mot or s , and for de tona t ing the four dua l -mode explos ive bolt s tha ts e c u r e t h e L ES s t r u c t u r e t o th e c o m m a nd m od ul e. 1

4 . 2 . 5 . 3 E L S S e q ue n c er

Th is component con sis ts of two redundant package s located in th ecomm and module r igh t -hand equipment co mpa r tmen t .two ba r oswi t ches , one f o r c i r cu i t com ple t ion t o t he d r ogue chut e m o r t a r sand t he o t he r f o r c i r cu i t com pl e t ion t o t he p il o t chut e m o r t a r s p lu s d r oguechu te d i s connec t m echa n i sm .

Each package conta ins

4 . 2 . 6 E l e c t r i c a l P o w e r S u b sy s te m

S i x E a g l e - P i c h e r s i l v e r o x i d e- z in c s t o r a g e b a t t e r i e s c o m p r i s e th eonboa r d e l ec t r i c a l power sou r ce f o r Spacec r a f t 002.MAP 4095) wi l l power the ins t rum enta t io n through the NASA-supplied powercont ro l box a s shown on F i g u r e 4 - 8 . As i nd i ca ted on t h i s F i gu r e , ano t he rtwo ba t te r ie s ( type MAR 4090) wi l l furn i sh power to the seque ncer subsys temlogic c i rc ui t , and the th i rd pa i r of ba t t e r ies ( type ME 461-0007) wi l l se rv ea s the pyrotechnic power source .

Two ba t t e r i e s ( t ype

4.2. 7 Com m uni ca t i on and I ns t r um en t a t i on Subsys t em

4 . 2 . 7 . 1 Te l em e t e r and An tenna

Two t e l e m e t e r t r a n s m i t t e r s w i l l t r a n s m i t f li gh t d a t a t hr ou g h amul t ip lexer and one VHF antenna .antennas .

This an tenna i s one of two scimitarThe other wil l be nonfunct ional on this vehicle .

4-17SI D 64-2 174


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INSTR BATTERY 28 VD C0INSTR BATTERY 28 VDC

IOWER CONTROL

BO X

(NASA SUPPLIED)

INSTR LOADS(28 VDC)

28 VDC

I]OGIC 140 WATT-HR

o$. ,ATTERY A

TELEMETRYMAGNETIC TAPE RECORDERSRATE GYRO PACKAGESIGNAL CONDlTlON ERATTITUDE GYRO PACKAGEMODULATION PACKAGERF POWERQ-BALL

' PYROTECHNIC

LAUNCH ESCAPEMOTOR-- PITCH CONTROLMOTORTOWER JETTISONMOTORCANARD ACTUATIONSERVICE MODULE SEPARATIONTOWER SEPARATIONHEAT SHIELD THRUSTERSDROGUE MORTARSDROGUE RELEASEPILOT CHUTE MORTARS8 VDCLOGIC 140 WATT-HR

BATTERY B

F i g u r e 4-8. E l e c t r i c a l P o w e r D i s t r ib u t i o n

4 -1 8

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4.2.9 Configurat ion Differ ences

Conf igurat ion d i ffe rence s of Spac ecraf t 002 in re la t ion to the a bor tMis s ion A-003 vehic le (Boi le rp la te 2 2 ) a r e a s follows:

Ar t i c l e

Command moduleSe r v i c e m odu leBoos t p r o t ec t i ve cove r

CM-SM separa t ion

Bo i l e r p l a t e 22

Bo i l e r p l a t eBo i l e r p l a t eEight -sec t i on

(boi le rp la te )C o m p r e s s i o n p a d s a n d

r a d i a l b e a m s

Spac ec ra f t 0 02

Spacec r a f tSpacec r a f tSeven -s ec t i on ( spacec r a f t )

Com pr es s i on pads and r ad i a lbeam s p l us e l ec t r i c a lum bi l i c a l and p l um b ha r dl i n e s

Conf igurat ion d i ffe re nces be tween Apollo vehic le s of succe s s i ve l aunchescap e subsys t em ab or t m i s s i o ns i n t he WSMR Apo ll o fl i gh t p r og r am a r esu mm ar ize d on Figur e C-2 of Appendix C.

4 . 3 MASS PROP ERTIES DATA

T he p r e l i m i n a r y m a s s p r o p e r t i e s d a t a c u r r e n t l y a v ai l ab l e o n Spacec r a f t

More comple te0 0 2 a r e p r e sen t ed on Tab l e 4 -1 .for the vehic le in the f l ight rea din ess s ta t e on the l aunch pad .m as s p r op e r t i e s da t a wi l l be ava i l ab l e a t a l a t e r da te .

T he v a l u e s a r e t h o s e c u r r e n t l y p r o p os e d

Table 4- 1. Weight , Grav i ty, and Ine r t i a Summary

4- 20

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N

I

5 -2

SID 6 4 - 2 1 7 4


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6 . 0 MISSION RULES SUMMARY

The mi ss i on ru l es conta in informat ion both on the l aunch l imi ta t ionsthat gov ern cont inuat ion or suspe nsion of lau nch countdown and on the d esignte st point condi t ions of the launch es ca pe vehicle .and d i rec t ions , v i s ib il i ty, and launch angle a r e the e lem ent s inc luded unde rl aunch l i m i ta t i ons . Mach num ber, dynam i c p r e s s u r e , f l igh t pa t h ang l e ,angle of a t t ack , and p i t ch ra te s co ns t i tu te the esc ape vehic le t es t pointcondi t ions a t s t a r t of abor t . Launch l imi ta t ions mu s t not be exceededto a l low the l aunch vehic le the g rea te s t probabi l i ty of a t t a in ing the de s ignpoint condit ion$ wi th in the a l lowable d i s per s io ns .

Launch s i t e wind ve loc i t i es

The l im i ta t ions and tes t poin t condi t ions a r e def ined in Appendix B ofth i s document . I

6- 1

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7 . 0 SCHEDULE

The var iou s pha se s of S pacec raf t 002 ac t iv i ty wi l l be accom pl i she d inTh i s i n f o r m a t i on i scco r d ance wi t h t he s chedu l e p r e sen t ed on F i gu r e 7 - 1 .

based on Mas ter Development Schedule (MDS) 8 , Revis ion 2 , dated22 January 1965.

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8 . 0 VEHICLE CHECKOUT PLAN

8 . 1 VEHICLE PREPARATION (S&ID DOWNEY)

Upon com plet io n of s ys te m s instal la t ion by Manu factur ing, theSpac ecraf t 002 vehic le wi l l be d e l ivere d to NAA Apol lo Te s t and Opera t i onsfo r t es t pre par a t io n a t Downey pr i or to sh ipm ent to WSMR.wil l cons is t of f ive pha ses .of tests t o be pe r f o r m e d on Spacec r a f t 002 f r om t he com pl e ti on of sys t em sinstal lat ion unt i l shipment to WSMR.t r ac es the proposed f low movement of the m aj or components of the vehic le

throu gh the Downey complex. Upon com plet io n of s ys tem instal lat ion , thefol lowing wil l be accomplished in Bui lding 290:weight and balan ce, config urat io n ver i f ic at ion, and open work' i tem s. Thepower-on test ing sequence wil l be conducted in Bui lding 001 and in the high-bay a s se m b l y tower.

P r e p a r a t i o nFig ure 8-1 def ines each phase and the seq uence

The b lock d iagram in Figu re 8-2

m echan i ca l f i t checks ,

8 . 1 . 1 F i r s t P h a s e

In Building 290, a com ple te examinat ion of the vehic le s ys te ms andsubsy s t em s wi l l be pe r f o r m ed t o ve r i f y con f o r m ance wi t h the l a t e s t con fi g -ur a t i on , spec i fi c a t ions , and eng i nee ri ng o r de r s t o ensu r e the r ead i nes s oft he ha r dwar e f o r checkout ope r a t i ons . P a r t s sho r t a ges wi l l be r em ed i ed ,and R & D equ ipm en t t hat was no t ava i lab l e i n the sys t em s i n s t a l l a ti on a r e awi l l be ins ta l l ed . Dur ing th i s per iod , the ess ent ia l f l ight har dw are i t e mswi l l be ins ta l l e d in the command module and ser v ic e module , and the pr e -l im ina ry weight and ba lance wi l l be accompl i shed . These uni t s wi l l then bemated on the s tacking f ix ture , H14-9030, and a l ignm ents wi l l be comple ted .The boos t pro tec t ive cover wi l l be f i t checked on the command module withthe l aunch esc ape tower ins ta l led . While these uni t s a r e s tacke d, a conf ig-ura t io n ver i f i ca t ion and an inspe c t ion shakedown wi l l be per for me d. Thevehic le wi l l be dem ated , and open work i t e ms wi l l be comple ted . The vehic lewi l l be pre pa re d for movem ent to Building 001.

8 . 1 . 2 S ec on d P h a s e

The comman d module , wi th the apex cov er remov ed, wi l l be mated tothe se rv ic e module H14-9030 com binat ion in Bui lding 450 (Navajo tow er) .The launch esc ape tower wi l l be mated to the com mand module , and thecana r d and the Q- ba l l w i l l be e l e c t r i c a l l y connec ted t o t he l aunch e s cape t owers k i r t .c r a f t spec i a l t e s t equ ipm en t ( STE) p r i nc i pa l l y m e t e r r oom equ i pm en t , andan i n t eg r a t ed GSE sys t em s t e s t wi l l be pe r f o r m ed .

Dur ing th i s pe r iod , the GSE wi l l be as se mb le d and mate d wi th spa ce-

The STE wi ll p r e se n t

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SERVICEMODULE

CO MMA N DMODULE

LAUNCHESCAPESYSTEM

GROUNDSUPPORT

EQUIPMENT

SYSTEMINSTL

I

I


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BUlLDlNG 290

PHASE I

H14-9030

~

-t.TACK

-tTACK

STACK VEICM-LESA LIG N

BOOSTCOVER

FIT CHECKWITHLET

INSPECTIO NSHAKEDOWN

DEMATE

COMPLETE

ITEMSBLDG 1

DEMATE

COMPLETE

ITEMS

DEMATE

COMPLETE

ITEMS

~ - ,LDG 1

MOVETO

BLDG 1

@ E


63/160

PHASE I I

] ~ D

STACKSMTO

9030

C MT OSM

LETT OC MIN

BLDG 1TOWER

-D

GSE.

CABLINGV E H I ~ L E

BATTERYINSTL

T

IIIII

III1I1IIIIII

I ,IN

SYSTE


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N O R T H A M E R I C A N AV IA T IO N , I N C .

BUILDING1 TOWER

PHASE IV

-I--PHASE Ill

I

E - I - --INTEG

SYSTEMTEST

DRYRUN

I1IIII ,I

INTEGSYSTEM

TESTSELL-OFF

C O N F I GVERIFA N DDATAEVAL

F i g u r e 8 - 2 . Prelauncl-

8


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S PA C E an d INFORMATION SY STE MS DIVISION

L O p e r a t i o n a l F l o w, D o w n e y

-5,8-6

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inputs to the GSE and ver i fy outputs to the s erv ice module umbi l i ca l i n or de rto es tabl i sh in te r face compat ib i l i ty.the l aunch escap e tower ; however, the vehic le ' s e l e c t r i c a l i n t e r f a c e s w i l lbe provided to the canard and Q-ba l l subsys tems .ins t rum enta t io n wi l l be ins ta l l ed on a hold ing f ix ture loca ted near the sp ace -craf t s t ack in the tower. Upon comple t ion of the GSE in tegra ted sy s te mste s t , the GSE-vehic le cabl ing hookup and ba t te ry ins ta l l a t ion wi l l pr ep ar ethe vehic le for sys tem checkout .

The i ne r t m o t o r s wi l l not be m a t ed t o

These uni t s and the i r

8 . 1 . 3 T hi rd P h a s e

The t h i r d phase of t e s t p r epa r a t i o n wi ll cons i s t of space c r a f t sy s t em sAn e l e c t r i c a l s y s t e m t e s t w i lle s t s t o ve r i f y i nd iv idual sys t em r ead i n es s .

ver i fy the opera t ion of the e l ec t r i ca l power subsy s tem f r om ground powera nd f r o m i n t e r n a l b a t t e r y p o w e r.

subsy s t em s wi l l a l so be ve r i f i ed .l anding sequences wi l l be 'conducted to ver i fy the prop er occ ur r enc e of a l lof the abo r t s equences , i nc lud ing s epa r a t i on r ocke t - m o t o r s t a r t s , f o r w ar dcom par tm ent cover j e t t i son , and parachute deployment. Al l t es t ing wi l l beaccom plishe d with WSMR-type cabl ing and J-bo x equipment .s i m u l a t o r s wi l l be u sed t o p r ov i de c i r cu i t l oadi ng and t o g ive p r ope r r e spo nsesfor l aunch escap e sub sys tem and explos ive devices t es t ing . Both the pro perphasing and t iming of functions and redundant funct ions wil l be tested . Wherei n t e r lock i ng c i r cu i t s a r e pr ov ided t o p r even t a func t ion f rom occur r ing outof sequence , the inter lo cking funct ions wil l be tes ted . During this test ing,the explos ive devices c i rcu i t s wi l l be moni tored to de te r mine w hether o r not

i n t e r ac t i on ex i s t s t ha t m i gh t c ause p r em a t u r e ope ra t ion .GSE wil l r ec or d the number of actuat ions of the f i r ing uni ts .

Pow er switching and act ivat ion of veh icle

E l ec t r i c a l t e s t s of t he abo r t and ea r t h

Pyr o t echn i c

Coun t e r s on t he

Ins t rumenta t ion t e s t s wi l l inc lude checkout and opera t ion of the t e le m-e t r y su bsys t e m s and checkout and oper a t i on of t he onboa r d t ape r ec o r de r s .The vehic le an tenna su bsy s tem s wi l l be t es ted for pro per output.t ion of a l l end ins t rum ent s wi l l be accompl i shed .wi l l be func tional ly t e s ted on bench maintenance equipment (BME) .wi l l then be ins ta l l ed in the vehic le and checked a s a veh i c l e subsys t em .

A c a l i b r a -The C-band t ransponders

They

8 . 1 .4 F o u r t h P h a s e

The f ou r t h phase of t e s t p r epa r a t i on wi l l be t he i n t eg r a t ed sy s t em scompat ibi l i ty t e s t .J -box es and wi l l inc lude se quent ia l opera t ion of a ll veh i c le subsys t em s t over i fy sub sys em compat ib i l i ty.

The t e s t s wi ll be conducted with WSMR-type cab les and

8-7

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8 . 1 . 5 F i n al P h a s e

The f ina l phase wi l l inc lude prepa ra t i on of the vehic le for sh ipment .The veh i c l e wi l l be dem a t ed and t hose sys t em s s chedu led f o r s ep a r a t eshipment to WSMR wil l be rem ove d and packaged. In ge ne ra l , the vehic lewi l l be sh ipped wi th su bsy s te ms ins ta l l ed .documents and NAA drawing numb ers wi l l be found in the "P rep ara t ion forDel ivery and Transpor ta t ion of Apollo Spacecraf t , " MAD116-001 and

A complete l i s t of appl icable

MAD 1 16 -0 12.

A ll a i r b o r n e i t e m s , i . e . , l aunch e scap e subsys t em , com m and m odu le ,s e r v i ce m odu l e , and se rv ic e module extens ion , wi l l be sh ipped by a i r c r a f tf r om Long Beach a i r po r t t o Ho ll om an Ai r F o r ce Base . Tr anspor t a t i on f r omS&ID, Downey, to Long Beach and fr om Holloman Air F or c e Bas e to the te sts i t e (WSMR) wil l be by t ruc k. The spa ce cr af t GSE wil l be shipped overl and

by t r uc k to WSMR. Shipment pla ns and meth ods a r e subject to change; how-ev er , the mos t expedi t ious sh ipping p lan compat ib le wi th the t es t sc li edulewi l l be implemented . Day 1 of the f ield sched ule ind icat es the ar r iv a l of thecommand module i n the vehic le a sse mb ly bui ld ing a t WSMR.components and GSE wil l be received at WSMR before Day 1.

Other vehic le

8 . 2 CHECKOUT OPERATION PLANS (DOWNEY)

The opera t iona l t e s t proce dur es l i s t e d on Table 8- 1 wi l l be employedto es tabl i sh the f l ight readiness of Spacecraf t 002 .denoted by the let ter P in the Loca t ion column wi l l be appl icable for checkout

a t Downey.

Only those procedures

8 . 3 VEHICLE PREPARATION (WSMR)

Pr e pa r a t i o n of Spacec r a f t 002 a t WSMR wil l co ns is t of two phase s;

The t e s t sequ ence, f r om r ece ipt of the vehic le at WSMR tospa cec raf t ass em bly building and spa cec raf t checkout and countdown a t thelaunch s i t e .launch countdown, i s shown i n F i gu r e s 8 - 3 and 8 - 4 .

8 . 3 . 1 Vehic le Assembly Bui ld ing Prepara t ion

Upon a r r i va l a t WSMR, the command module and GSE wi l l be de l iveredto the vehic le assem bly bui ld ing (VAB) for rece iv ing inspec t ion . The mo to rsand ordnance wi l l be de l ivere d to the VAB f ro m the ordnance s tora ge a r e a .Assembly of the launch escape subsystem, including the instal lat ion of a l li n s t r um en t a t i on and i n s t a l l a t i on of pa r ach u t e s and o r dnance i n the com m andmodule , wi l l be per fo rme d in the VAB.

F i na l we igh t and ce n t e r -of -gravi ty d e te rm ina t io n wi l l be accompl i shedin the VAB. Weight and balance te st s of the s er vi ce module wil l not be

8 -8

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Table 8-1. O p era t io n a l Tes t P ro ced u res

Location

P & AAAA

APP & AP & AP & AP & AP & A

AA

PA

P & AA

PP & AP & AP & AP & AP & A

AA

P & AA

P & AAA

P & AP & A

AP & AP & AP

P & APP & A

Opera t iona l

Checkout rlr1P r o c e d u r e No.

*

P DowneyA F i e l d

have not been a ss igne d , This in forma t ion wi l l be suppl ied when i t b e c o m e s a v a i la b l e .

Tit le

I n t e g ra t e d Sy s t em T e s t sCountdown Spacecraft 00 2 a n d L i t t l e J o e IISimulated Countdown, Sp ace craf t 002 and Li t t le Joe I1Py ro Rece iv ing Inspec t ion , S torage & Pre ins ta l la t ion

Elec t r ica l Sys tem CheckoutElec t r ica l Ver i f ica t ion & Func t iona l Power ChecksLE S & ELS Sequence r Ver i f ica t ion ChecksBME Checks ELS Seque ncer and Baroswitc hBonding Verif ica tion of Spa cec raf t and GSEBat