Apollo Familiarazation Manual Boilerplate and Flight Assignments

8/4/2019 Apollo Familiarazation Manual Boilerplate and Flight Assignments

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NASASUPPORT MANUAL .

r - L L -

PUBLISHED UNDER AUTHORlTY O F THE NA TIO NA L AERONAUTlCS AND SPACE AD Ml NlSTRATlON


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F i g u r e 7-2. Block I Boilerp la te Vehic le Sys tem s Configura t ion forSpacecraf t Development


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F i g u r e 7-3. Block I S pace cra f t Veh ic l e S ys t ems Conf igura t ion fo rS pac ec ra f t Deve lopment


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SYSTEMS CONFIGURATIONLEGEND

kJOR GROUND TEST VfHlCLlS

COVERY TESTI t

STATIC IESTS

A N N O MI U M U I H r nR I G HT S (

Figure 7-4. Block 11 Spacecraft Vehicle Sys tem s Configuration forSpacecraft Development


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NOTEBlock I1 information is based on preliminary dataonly.

7 - 11. Block I encom passes the en t i re boi lerplate progra m, and spacecraf t 001, 00 1A,002, 002A, 004, 004A, 006, 007, 008, 009, 010, 011, 012, 014, 017, a nd 020.7-12. The boil erp late portion of Block I provides:

a . Ear l y su pport of sys tem s development for land impact, water im pact , and para -chute recovery prequal i f ica t ion tests

b. System s qual i fica tion to support spacecraf t p rog ram s inc luding pad abort , h igh-alt i tu de abor t , and hous e spa cecr aft No. 1 (boilerpla te 14) which contains al l syste ms

c . Ma rsha l l Space Fl ight C enter support inc luding Saturn I development and mic ro-meteoroid detec t ion

d. Space-fl ight capa bil i t ies development and coordination of manufacturing, test ingop era tio ns , engine ering, and NASA functions.7- 3 . The s pac ecr aft port ion of Block I provides:

a. Command module and s erv ice module development for manned ear th orbi ta lm i s s i o n s

b. Dem onstrat io n of op erational capabil i t ies of sys tem s including al l types of ab or tland recov ery, water re covery, Saturn IB and V operatior. (and compatibil i ty), andopera t ion dur ing ear th orbi ts (unmanned)

C. Qualified team s developm ent for checkout, launch, manned spa ce flight network,reco very , and f light analysis .

NOTES /C 001 wi l l be refurbish ed and designated 2s-1Afo r Block I1 propulsion tests.

7-14. Block I1 enc om pas ses s pa cec raf t 2H-1, 2s-1 , 2 s- lA , 2s -2, 2TV-1, 101, 102, 103,105, 106, 107 , 108, 109, 110, 111, and 112, and provid es:

a . Incorp oration of lunar e xcu rsio n module provis ionsb. Reduction of weight in command modulec . Impro vemen t of c ente r-of - gravity in command moduled. Evaluat ion and incorpora t ion of sys tem changes wi th resp ect to lunar m issio n an

re l i ab i li t y impac te. Cost reduction.

7 - 15 . BOI LER PLA TE MISSIONS.7 - 16. The boi lerpla te mis sion s ar e pr imari ly res ear ch and development tests to evaluthe s t r uc tur a l in tegr i ty of the spa cecraf t and confi rm basic engineer ing concepts re la t ivto sy stem per forman ce and compat ibi l ity . A number of mi ss ion s wil l be conducted durthis phase of the test pro gram . The miss ions a r e scheduled to follow a patte rn of deveme nt s ta r t ing with bas ic s t ruc ture evaluat ion, fol lowed by s yste ms perfo rmanc e andcompatibil i ty confirmation.7- 17. Eac h missi on i s dependent upon the previous m issi on in developing the sy ste msopera t io ns r equisi te f or lunar explora tion. Pr io r to the s ta r t of any missio n, the boi l epla te to be tested i s thoroughly checked a t the manufacture r tes t prepara t ion ar ea undethe directio n of NASA inspec tors . Aft er sys tem and str uc tur al checkout has been approthe boi lerpla te i s shipped to the te st s i te for fu r ther checkout and mating. A launch codown is started only after the second checkout and mating have been approved. Figure dep ic t s a wa te r impac t t e s t.


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A PENDULUM FOR APOLLO-An impact test faci lity, from which NASA's unmannedApoll o test command modules are swung and dropped on land w water, is seen i n operationat Downey, Calif . The Apo llo command module s suspended below the steel platform andthe huge "arm" swings the capsule, releas ing i t at controlled angles and speeds to simu-late impact which later manned Apollo spacecraft will undergo upon return to earth.

Figure 7- 5. Struc tural Reliabil i ty Te s t7- 18 . BLOCK I BOILE RPLA TE TEST PROGRAM. The following i s a lis t of each bo iler -plate and relat ive mission data. Boilerplates and their mis sio ns a r e par t of the Block Iportion of the Apollo program. The l i s t i s i nt ended a s a c ross - re fe re nce fo r bo i l e rp la t eobjectives. Chronological or de r of miss ions and test grouping i s not intended or r efle ctedin the arra ngem ent of the l i s t .

I Ioiler -plateNo.

B P I

Same as BPI .

Te st Site

BP2 None

.. cont inued

Downey,Calif.

Purpose

Downey,Calif.

Develop ment and evaluation of cr ewshock absorption s yst em ; evaluationof C/ M on land and water, du ringandaf ter impact .S a n e a s B P I .

Miss ionLaunchVehicle

Drop tests ut i l izingDowney, California,d rop t e s t t owers .

None


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White SandsMiss i l eRange(WSlMR),NewMexico

Block I Boi le rp la t e Tes t P rog ram (Cont )

To determine aerodynamic stabi l i ty,tower vibrat ion, and spa cec raftdynam ics during a pad abo rt ; tode mo nst rat e capability of LES top rope l C / M to a safe distancefro m launch ar ea dur ing a pad abort .BP6 refurb ished for parachute

Calif. r ecovery sys t em t e s t in the a i r ,

Pu rposeTo evaluate parachute recoverysyst em in the a i r (des t royed)

Boi ler -plateNo.

C

B P 3

Mar sha l lSpaceFlightCen te r(MSFC),Alabama

Tes t S i teEl Cen t ro ,Calif.

Dynamic test to be determ ined byNational Aeronautics and SpaceAdministrat ion.

WSMR,NewMexico

BP9A CapeKennedy,F lo r ida

BP12A

To be determine aerodynamicstabi l i ty cha rac ter ist ics of Apolloescape configurat ion during tran-sonic abor t f rom Li t tle Jo e 11. Todem onst rate capabil i ty of LES opropel C /M to safe d is tance f romlaunch vehicle dur ing an abor t a th igh-dynamic pres sure . Todemon st rate s t ruc tural in tegr i ty oflaunch escape tower and operat ionalcha ract er i s t ics dur ing a t ransonicabo r t , and demonst rate spacecraf t -L i t t l e Joe I1 compatibility.

To be utilized for launch vehiclequalif icat ion and micrometeoridexper iment .

Downey,Calif.

B P I 3

BP12 refurbished to evaluate C / Mdur ing hard ro l lover water landingcondition.

CapeKennedy,F lo r ida

To qualify Saturn I launch vehicle,demonstrate physical compatibi l i tyof launch vehicle and spacecraftunder preflight and flight conditions,and determ ine launch and exi t envi-ronmental parame ters to veri fydes ign c r i t e r i a .

LaunchMission Vehicle

via ai r drop. (drop)Pa d abor t miss ion Launchsuccessfu l ly comple- escape( ted 7 November ]system

via a i r drop.1 ; IDeterm ination ofdynamic s t ructuralcomp atibility of te stS / C with Saturn I.

None

Micrometeoroidexperiment usingNASA -ins tal ledexperiment .

Saturn

Transonic abor tmiss ion successfu l lycomp leted 13 May

Lit t leJ o e I1

Launch environmentmiss ion successfu l lycompleted 28 May1964 to 31 May 1964.

Saturn


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SM2A-02

Block I B o i l e rp l a t e T e s t P r o g r a m ( C on t)

. ontinued7 - 9

LaunchVehic leNone

Sa t u r n I

A i r c r a f t(d rop)

Li t t leJ o e I1

Li t t l eJ o e I1

Launche s c a p es y s t e mm o t o r .

Mi s s i o nResea rch and deve l -opmenta l tool forsys t ems eva lua t ion(s t a t i c veh ic l e ) .Launch exi t environ-ment (o rb i t a l f li gh tt r a j e c t o r y ) m i s s i o nsuccessfu l ly c o m p l e -t ed 18 Sep te mbe r1964 to 22 Se pte mb er1964.Mi c r o m e t e o r i dexper iment .Launched into orbi tsuc ces s fu lly16 Fe b r u a r y 1 96 5.Pa r a c h u t e r e c o v e r ysys tem eva lua t ionthrough mea ns ofcommand modulea i r d r o p.

Qualify LES, ELSsequence t imingdur ing abor t .Demo nst ra t ion ofl aunch e scape veh ic l es t r u c t u r a l i n t e g r i tyand recov ery of C /Mfollowing high-Qabor t . Successfu l lycomple ted miss ion8 December 1964 .C / M f o r p ad a b o r tevaluation.

P u r p o s eDevelopm enta l tool for use indeve lop ing sp ace c ra f t sys t e ms andpre l im ina ry checks in in t egra tedsys tems compa t ib i l i t y .Second boi lerpla te f lown forenv i ronmenta l da ta . The purposeof this vehic le and BP13 a r es i m i l a r .

To be ut i l ized for launch vehic lequa l i fi ca t ion and mic rom eteoro idexper iment .

To eva lua te pa rach u te recov erysy s t e m i n t he a i r .

To ver i fy LES, ELS , and can ardsys tem dur ing h igh-a lt i tude abor t .

Veri f ica t ion of L E S, E L S l u r i n ghigh-Q abort .

To quali fy LES, EL S sequencet iming , can a rd sys t em , dua ldrogue chu tes , and boos t p ro tec -t ive cove r dur ing pad ab or t t e s t .B P2 3 C / M r e f u r bi sh e d f o r p a dabor t t e s t .

B o i l e r -pla teNo.

B P 1 4

B P 1 5

B P 1 6

~ ~ 1 9

B P2 2

B P2 3

BP23A

T e s t S i teDowney,Cal i f .

C a p eKennedy,F l o r i d a


E l C e n t ro ,Cal i f .

WSMK,NewMexicoWSMR,NewMexico

WSMR,NewMexico

I


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Block I Boi le rp la t e Tes t Prog ram (Cont )

7-19. SPA CEC RA FT MISSIONS.7-20. Spa cecra ft mis sio ns, conducted with production spac ecraf t , a r e of a mult ipurposenature . The ini t ia l miss ions wi l l be conducted to veri fy product ion spac ecraf t s t r uc t uraintegr i ty , and systems operation and compatibil i ty. After the spac ecraf t s t ru c tu re andsy ste ms te st mission s a r e comple ted, a se r i es of unmanned miss ions wi l l be conductedto confirm sp acecr aft-la unch vehicle compatibil i ty and evaluate prelaunch, launch, m is -sion, and postmissio n opera t ions. Manned spac ecraf t miss ions wi l l be conducted toimp rov e perfo rma nce and confirm capabil i ty between man and space craft .

LaunchVehicleNone

Saturn

Sa turnIB andSaturnV(captivt e s tf i r ing)None

None

Sa turnIB

MissionDemonstrat ion ofequipment and han-dling capability forcommand module a ta s i te (s imula ted)recovery a s a des ignfor pickup equipment.Micrometeoroidexper iment usingNASA -installedequipment.Determina tion ofdynamic s t ruc tu ra lcompa tibility of te stS /C wi th Saturn IBand Saturn V launchvehicles

Definition of land ingp r o b l e m s b y d e t e r -mination and evalu-ation of loads imp os edon st r uc t ure due tolanding impa ct, andaccelera t ion andonse t r a t e s imposedon cre w by c re wcouch attenuationsys tem.Full - scale flotat ionand recovery testsfor s imula ted ent ryand abort condit ions.El l ipt ica l orbi ta lflight for CSM andLEM operation.

Pu r p o seTo dem ons trate pickup and handlingtechniques a re requ ired by NationalAeronautics and SpaceAdminist ra t ion.

To be uti l ized f or launch vehiclequalification and micrometeoroidexper iment .

Second dynamic test . Objectivesfor th is ground test wi l l be de t er-mined by National Aeronautics andSpace Administrat ion.

Tes t vehic le wi l l be impacted an u m b e r o f t i m e s i n o r d e r t o e v a l -uate loads imposed on st ruc turedue to landing impact and accel-era t ion, accelera t ions and onsetra te s imposed on crew by thecre w couch a ttenuat ion syste m,stab ility, and dyn amic s of thevehicle.

To determine f lota t ion charac ter-ist ics of command module.

An unmanned flight to evaluate S/Cand LEM propulsion performan ce.

Boi l e r -pla teNo.

B P2 5

BP26

BP27

BP28

BP29

BP30

Tes t S i t eHouston,Texas

CapeKennedy,Flor ida

MSFC,Alabama

Downey,Calif.

MSCHouston,Texas

CapeKennedy,Flor ida


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7 -21 . Each sp acec ra f t mis s i on i s dependen t upon the suc ces s of the p rev ious mis s io n , a san ove ra l l p r og ram of p ro gre s s iv e , manned , space pene t ra t ion i s p lanned to a f fo rd thef ligh t c rew maxim um fami l i a r i ty wi th p roduct ion space c ra f t ~ na ne uv e r s nd dock ing t ech-niques with the LEM. Manned mis s ion s wi ll pene t ra te de epe r in to space a s the p ro gr amp r o g r e s s e s . Manned space-f l ight ne tw ork techniques wi l l be employed during a l l ear thorb i t , t r ans luna r , and luna r o rb i t mis s ion s . The sys t em compat ibi l ity with Apo llo space -c ra f t w i ll be de te rmi ned dur ing th i s phase of the t e s t p rog ram . The knowledge gained bythe f light c r ew and engineer ing p .ersonne1 durin g th is phas e wi l l be analyzed for u se durin gmanned luna r su r fac e exp lora t ion.7 - 2 2 . BLOCK I SPACECRAFT TEST PROGRAM. The following i s a comple te l i s t ofApollo spacec ra f t , t he i r mis s ion s , and re la t ive da ta requ i re d to comple te the Block Iportio n of the Apollo pr og ra m. The l i s t i s s im i la r in inten t to tha t of pa rag raph 7 -18; thechrono log ica l o rd e r of spacec r a f t mis s ion s i s not in tended o r re f l ec ted in the a r ra nge men tof the list.

. ontinued7 - 11

LaunchVehic leNone( s e ef i g u r e7 - 6 . )

None

L i t t l eJ o e I1

None

None

Mis s ionD e t e r m in e s p a c e c r a f ts t r u c t u r a l v i b r a t i ona n d a co u st i c c h a r a c -t e r i s t i c s d u r i ng a l lphases of SPS ope ra -t ion , and pe r fo r m-anc e of e lec t r ic a lpower sys tem andc r y o g e ni c s t o r a g esubsys tem dur ingse rv ice p ropu l s ionand reac t ion con t ro ls y s t e m s o p e ra t io n .Block I1 propu lsiont e s t s .

Abort a t h ighd y na m ic p r e s s u r e sin t ransonic spee drange .

C / M fo r l and imp ac tt e s t s .S t a t ic a n d t h e r m a ls t r u c t u r a l t e s t s.

P u r p o s eTo ver i fy compat ib i l i ty of sp ac ecr af tS / M p ro p u ls i on s y s t e m ; e v a l u at eS / M s e r v i c e p r o p u ls i on s y s t e m a n dr e a c t i o n c o n t r ol s y s t e m d u r i n g m a l -funct ion , no r ma l , and mi s s i onprof i l e condi t ions . To evalua tein te r fac e compa t ib i li ty be tween a l lonboa rd sys te ms dur ing in teg ra teds y s t e m s t e s t ; e v al u at e p e r f o r m a n c eand compat ib i l i ty per ta in ing toground suppor t equ ipment, s a fe tyru l e s , ope ra t ing t echn iques , an dcheckout of appl icable sys tems .S / C 0 01 r e f u r bi s h e d f o r B l oc k 11p r op u l si o n s y s t e m t e s t s .

T o d e m o n s t r a t e s t r u c t u r a l i n t e g r i t yof product ion C /M un der h igh dyna-m i c p r e s s u r e a t t r a n s on i c s p e e d.T o d e t e r m i n e o p e r a t i o n al c h a r a c -t e r i s t i c s du r ing power on tumbl inga b o r t .E a r t h r e c o v e r y a n d i m p a c t t e s t s .

S /C fo r ve r i f i ca t ion of s t ru c tu r a lin teg ri ty and in t ram odula r com -patibil i ty of com bined modules t ru c tu r e s under c r i t i ca l load ings .

Space -c r a f t

No.001

OOlA

00 2

OOZA

004

T e s t S i t eP r o p u l s i o nS y s t e mDevelopmentF a c i l i t y( P S D F ) ,White Sands ,M i s s i l eRange(WSMR),NewMexico

WSMR,NewMexicoWSMR,NewMexico

Downey,Cal i f .Downey,Cal i f .


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Block I S p a ce c r af t T e s t P r o g r a m ( Co nt )

LauncVehic lNone

None

None

None

Mis s ionSta t i c t e s t s .

R e s e a r c h a n ddevelopmental toolf o r s y s t e m s e v al u -a t ion ( s t a t i cvehic le) .Acous t ic , waterimpac t , and pos t -l anding t e s t s .

T h e r m a l v ac u umt e s t s .

S p a c e -c ra f t

No.004A

006

007

008

T e s t S i teDowney,Calif.

Downey,Calif.

Pac if icOcean Tes tSi te

M S C , .HOUSon ,Texas andDowney,Calif.

PurposeVeri f ica t ion of s t ru c tu ra l integr i tyand intramo dular compatibil i ty ofcombined module s t ruc tur es undercr i t ic a l loading.House s pacec raf t No. 2 fo r ha rd -ware development tool.

Th i s spacec ra f t w il l s e rv e a dua lpurpose : module t ransmiss ib i l i tyand wat er impact and flo tat ionte s t s . Modu le t ransmis s ib i l i ty t e s twi l l de te rmine f ree - fa l l l a t e r a lbending mod es an d longitudinal andshel l modes , u t i liz ing two space-cr af t configura t ions . Configura tionA wil l incorp ora te launch escapetower a nd C/ M; configura t ion B willincorpora te C / M and S /M. Wate rimpa ct and f lo ta t ion tes t s wi l l incor -pora te C / M only. Purpose ofwa te r impac t t e s t i s to ve ri fys t r uc t u ra l in teg r ity of C / M andc re w suppor t sys tems dynamicsunde r shock cond i tions a t wa te rimpac t , and de te rmine ELSper fo rmance . F lo ta t ion t e s t s w i l ld e m o n s t r a t e C / M flotation andwater - t igh t in tegr i ty in varying seacondi t ions a s we l l a s c rew su rv iva lin a c losed modu le , and c rew eg re s sin varying sea condi t ions .Spac ecraf t 008 wi l l undergo bothmanned and unmanned deep-spaceenv i ronmental con t ro l t e s t s . Thef i rs t of these tes ts wi l l be conducteda t Space and In fo rma t ion Sys temsDivision, NAA tes t facil ity, Downey,Cal i fornia . After opera t ional check-out of ins ta l led sys t ems , spacec raf twi l l be shipped to MSC fac i l i ty a tHous t in , Texa s , for eva lua t ion


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Block I S p a c e c r a f t T e st P r o g r a m ( C on t)

. . ont inued7 - 1 3

M ~ s s l o n

S u p e r - c i r c u l a rh igh-hea t ra t e en t ryflight.

Qualification oflaunch escape con-figurati on of pro -duct ion spacecraf t .A s u p e r c i r c u l a rhigh-heat loadentr y f l ight.

A long-dura t ionorb i t a l f l igh t fo rCSM subsystemper fo rmance .

P u r p o s eand ver i f ica t io n of comple te sp ace -cra f t des ign under launch simulation,orb i t a l mis s ion s imulat ion , th e rm a linvest igat ion , sys te m fa i lu re inc r e -men ts , emergen cy ope ra t ions , modu lesepa ra t ion , en t ry s epa ra t ion , andr e c o v e r y a i d s c h e c k o u ~ .To eva lua te hea t sh ield pe r fo rm ance ,RCS and SPS opera t ions , SCS o p e r a -tion, open loop EDS and pa rti al EP Sopera t ion . To de te rmin e load ings e p a r a t i o n c h a r a c t e r i s t i c s a ndcommunica t ions pe r fo rm ance . TOdem ons t ra te opera t ion of recover ysys tem , launch vehic le and spac e-cra f t compat ib i l i ty , and cryogeni cgas s to rage sy s tem ope rat ion . Am i s s i o n p r o g r a m m e r , M od el M1 ,wi l l con t ro l S / C in - f ligh t ope ra t ions.A f t e r s t a t ic t e s t s a s S / C 004A, th isC / M wil l undergo an abor t t e s t andwil l be used a s a backup vehic le forf o r S / C 0 02 .

An unmanned flight to evaluatehea t sh ie ld pe r fo rm ance , EDS pe r -f o r m a n c e , and SPS propel lantre tent ion device . Determ ine S L As t r uc t u ra l load ing , s epa ra t ionc h a r a c t e r i s t i c s , p e r f o r m a n c e ofG&N, SCS, E CS, EPS, RCS, andte lecommunica t ions . To demon-s t r a te l aunch veh ic le and S I Ccompa tib i li ty , s t ru c tu r a l integ r ity ,C'/M entry, multiple SPS r e s t a r t s ,and recove ry . S / C wil l be contro l -led by model M3 m i s s i o n p r o g r a m e r .A manned fl ight to evaluate cre w-S/ C compa t ibi l i ty , c rew ta sks anda n d s u b s y st e m s p e r fo r m a n c e , m a n -ual , and backup modes of subsys temsepa ra t ions . To demons t ra te c losedloop EDS.

Spacec r a f tNo .

009

01 0

011

0 12

LaunchVehicle

S a t u r nIB

Lit t leJ o e 11

S a t u r nIB

S a t u r nIB

T e s t S i te

1

CapeKennedy,F l o r i d a

WSMR,NewMexico


CapeKennedy,F l o r i d a

Documents

Apollo Familiarazation Manual Boilerplate and Flight Assignments