AS-202 Technical Summary

8/6/2019 AS-202 Technical Summary

1/72

P r e p a r e d by:R - A E R O - P .R -AS TR -SR-PPIVE-VNCI

R - A S T R - S - 1 4 0 - 6 6A u g u s t 5, 1966

TEC HNIC AL INF OR MATIONSUMMARY

- Form 45 4 (Revised September 1 9 6 1 )


2/72

AS-202TECHNICAL INFORMATION

SUMMARYT h is r e p o r t o u t l i n e s , t h rou g h a s e r i e s o f s k e t ch es w i t h accompanying t ex t ,

the ge ner al f ea tu r es of Apol lo S atu rn Space Vehicle AS-202. The ske tche s i nth i s summary a r e devo ted p r i ma r i ly t o th e Launch Veh ic le , bu t a l s o p re sen tl i mi t ed i n o rma ti o n on t h e l au n ch p rep a ra t i o n s , t h e L aunch Fa c i l i t y , and t h eSp acec ra f t.

1. Miss ion Purpose :The b a si c purpos e of t h e AS-202 mi ssi on i s t o d emo n s tr a t e t h e

co mp a t i b i l i t y b e tw een t h e u p ra t ed Sa t u rn I l aunch ve h i c l e and the Apol loSp acec ra f t , and t o ev a l u a t e t h e pe r fo rman ce of t h e l au nch v eh i c l e an d s p ace c ra f ts ub sy st ems i n p r ep a ra t i o n f o r manned o r b i t a l mi ss i o n s . The mi ss io n 's purpose i sachieved th rough th e accompl ishment o f d e t a i l e d miss ion ob j ec t ive s .

2. Mi s si o n o b j ec t i v e s :a . D em on st ra te s t r u c t u r a l i n t e g r i t y a nd c o m p a t i b i l i t y of t h e l a u nc h

v eh i c l e and s p ac ec r a f t and co n fi rm s t r u c t u ra l l o ad s an d dy nami c ch a r ac t e r i s t i c s .b . Demonstrate s e p a r a t i o n o f :

(1) S-IB from S-IVB/Instrument Unit (IU )/S pa cec raf t .(2) Launch Escape Tower wi th boost protect ive cover from theCommand Module.(3) Command/Service Module from S-IVB/IU/Lunar Module Ad ap te r.( 4 ) Command Module from S e r v i ce Module.

c . V e r i fy o p e ra t i o n o f t h e fo ll o w i n g s ub sy st ems:(1) Launch v eh i c l e ; p ro p u l s i o n , g u id ance and co n t ro l , e l e c t r i ca l ,ins t ru me nta t io n, sequencing, and sec ure range sa f et y command.(2) Sp ac ec ra ft ; Command Module adequacy fo r r ee nt r y from low

e a r t h o r b i t , S e r v i c e Module p r o p u ls i o n ( i n c l u di n g r e s t a r t ) , e n vi ro n me n ta lco n t ro l (p res sur e and t empera tu re co n t ro l ) , communicat ions ( p a r t i a l ) , commandand S e r vi c e Module r e a c t i o n c o n t r o l , s t a b i l i z a t i o n and c o n t r o l , e l e c t r i c a lpower ( p a r t i a l ) , a nd e a r t h la n d in g .

d. Eval uate performance of th e spac e ve hi cl e Emergency Det ect io nSyst em i n a c l o s ed l o op co n f i g u ra t i o n .


3/72

e . Eva lua te performance of t h e Command Module he a t s h i e l d a t ah i g h h e a t ra te dur ing r een t ry .

f . D em on st ra te t h e m is s io n s u p po r t f a c i l i t i e s r e q u i r e d f o r l a u nc h ,mission operation and Command Module recovery.3 . PRINCIPAL DIFFERENCES BETWEEN AS-202 AND AS-201

a. Hardware:1. T e l e v i s io n s y st em l o c a t e d i n t h e I U and Spacec raf t Adapter f o r

v iewing Sp acec raf t s epa ra t ion and ada pter panel deployment .2. Thi rd th ru s t OK swi tch added t o S-IB Emergency D et ec tio n System.3 . F i l t e r s added i n C on t ro l S igna l P roces so r.4. Mod 2 Swi tch S e l e c to r s added (Mod I on AS-201).5. Secu re Range Sa fe ty System added (DRW - 13 on AS-201).6. R&D Command System de l e t e d from I U .7. One Control Accelerometer Assy. re lo ca te d (mounted on col dp la te ) .i n I U .8. Heav ie r spacec ra f t .

b. Systems:1. Emergency De tect ion Sys tem t o be f lown i n c l osed loop c onf igu ra t ion2. Ear ly Spacecraf t sepziration.3 . S-IVB bulkhead pres sur e t e s t and 75" r o l l maneuver af t e r Spa ce cra f t

s e p a r a t i o n .4. Three seconds between inbo ard and outboard en gine cu to ff . (6 sec .

on AS-201).5. Late r Eng ine Mixtu re R a t i o s h i f t .

4. M i s s i o n P r o f i l eThe Apollo-Satu rn 202 Mi ssi on w i l l be a non -or bi t al , unmanned, sup er-

c i r c u l a r e n t r y , " lo b- ty pe u f l i g h t . As-202 w i l l be launched from Launch Complex34 a t Cape Kennedy a t a la unc h azimuth of 100' E . of N . and r o l l e d t o a 105"f l i g h t a z im ut h a nd f o l lo w a n S-IB f l i g h t p r o f i l e c l o s e t o t h a t of a nominalo r b i t a l m is si on . Af te r S-IB se pa ra t io n, t he S-IVB/IU/Spacecraft i s p r o p e l l e di n t o a " lo b- ty pe r1 b a l l i s t i c t r a j e c t o r y . The S-IVB f l i g h t p r o f i l e i s opt imizedt o p rov ide maximum S pacec ra f t r e en t ry ve i oc i t y w i th i n t he r equ i red r een t ry .11 11g l oad ing and t o t a l r ange cons t r a in t s . F ol lowing S pacec ra f t s ep a ra t i o n t h eServ i ce Propuls ion Sys tem w i l l b e e x e r c i s e d f o u r t i m e s; two b u r ns t o e f f e c te n t r y c o n d i t io n s a nd two a d d i t i o n a l b ur n s t o d e mo n st ra t e r e s t a r t c a p a b i l i t y .


4/72

Ninety seconds a f t e r S-IVB e ngi ne cuto ff th e S-IVB LOX tan k w i l l be ven t edwhile the LH2 tank remains pre ssu riz ed. T h is t e s t may r e s u l t i n b ul kh ea d r e v e r s a land su bs eq ue nt d e s t r u c t i o n of t h e s t a g e p r i o r t o r e e n t r y . One hundred secondsa f te r S-IVB e ngi ne cu to ff t h e S-IVB w i l l be ro l l ed 75" clockwise (a s viewed fromthe r ea r ) f o r improved g round s t a t i o n t e l emet ry ac qu i s i t i on du r ing t he bu lkheadpressure experiment . This maneuver w i l l take about 150 seconds.

No a l t e rn at e miss ion i s plan ned f o r AS-202. A l l av ai la b l e Launch Vehic leper fo rmance has been a l l oc a t e d , excep t f o r p e r f o m a n c ~ ese r ves . L imit ed11one e ng in e o u t" c a p a b i l i t y e x i s t s d u r in g t h e l a t e r p o r t i o n of S- IB poweredf l i g h t . S hould S-IVB s t a ge underper fo rmance occu r , t he i n i t i a l S e rv i ce P ropu l s ionSystem burn w i l l b e e x te nd ed t o o b t a i n a n a c c e p t a b l e S p a c ec r a f t t r a j e c t o r y .

This mission w i l l e x e r c i s e a two ocean recovery force. T h is f o r c e i n c l u d e sthe At l an t ic Recovery Con t ro l Center lo ca ted a t Cape Kennedy and th e P ac i f icRecovery Co ntr ol Cent er a t Kunia, Hawaii. Normal r ec ov er y of t h e Command Xodu lei s p lanned i n t h e v i c in i t y o f Wake I s l and .

--

. 4rbond Ranqa ( ~ m )i


5/72

DISTRIBUTIOND I RDIR-TI - D I R

I - IB-MGRI - IB -BI - IB -GI-IB-TI-IB-S-IBI - IB -UI -KI-E-AI-MO-MGRI-KO-FI - M I CH-DR-DIRR- OMR-TOR-RP-DIRR-AERO-PR-P &VER-ASTRR-CCMP-RPR-ME-DIRR-QUAL- JR-TEST-SPAKSCMSFCIDAC throughR-ASTR-BV/DAC

DAC/HIBE-HIBM-HCCSDIM

D r . von BraunD r . ReesM r . NeubertGen. O1ConnorD r . MrazekD r . F a r i s h ( 5 0 )M r . JamesC ol . Te i rM r . V r e u l s ( 2 )M r . Dunlap (3)M r . F ike s ( 3 )M r . Thompson (3)M r . Simmons (3)M r . Montgomery (10)Mrs. Watson (25)D r . Speer (10)M r . Casey (10)M r . Quinton (25)M r . Weidner (2)M r . F e l lows (5)M r . RichardD r . S t u h l i n g e rM r . Teague (60)E ( A l l S u p e r v i s o r s )E ( A l l S u p e r v i s o r s )M r . Cochran (6)M r . Kuers (10)M r . Klauss (10)M r . D r i s c o l l ( 5)M r . J o n e sM r . Williams (250)M r . French (20)M r . P. Dixon ( 5 )M r . C. L. Mart in (20)M r . Robin (10)M r . J u e n g l i n g ( 5 )

A d d i t i o n a l c o pi e s o f t h i s r e p o r t may be o b t a i n e d f ro m t h e f o l l o w i n gp e r s o n n e l :

R-AERO-P R. Teague, 876-4443 Bldg 42001408R-ASTR- S E . Noel, 876-1860 Bldg 44871AA211R-P &VE-VNC 0. E . Moon, 876-5585 Bldg 461011091


6/72

Intentionally Left Blank


7/72

F i g u r eGENERAL

LIST O F FIGURESTitle P a g e

AS-202 Space Vehicle . . . . . . . . . . . . . . . . . . . . . . . . 8. . . . . . . . . . . . . . . . . . . . . . . .aunch Complex 34 9

LC-34 Integra te d Launch ESE Block Di agr am . . . . . . . . . . . 10LC - 34 P r ope l l a n t a nd P r e s s u r i z a t i on Subs ys t e m s . . . . . . . . . 11. . . . . . . . . . . . . . . . . . . . . . . .C-3 4 Configuration 12. . . . . . . . . . . . . . . . . . . . . . . . . .aunch Countdown 13SPA CE1 LAUNCH VEHICLE . . . . . . . . . . . . . . .ecur e Range Safe ty Command System 15Emergency Detec t ion System (EDS) . . . . . . . . . . . . . . . . 17. . . . . . . . . . . . . . . . . . . .-IB Stage Flight Sequencing 18. . . . . . . . . . . . . . . . . . .-IVB Stage Flig ht Sequencing 19. . . . . . . . . . . . . . . . . . . . . . .ra j ec t or y Informat ion 20Guidance and C ontrol Sys tem Block Diagr am . . . . . . . . . . . 23

. . . . . . . . . . . . .uidance and Control Syste m Informat ion 24. . . . . . . . . . . . . . . .ehicle Cont r 01 System Inf or rna ion 25

. . . . . . . . . . . . .ehicle Trackin g and Televisio n Sy ste ms 27. . . . . . . . .racking. Te lem etr y and Range safety' Cove rage 29. . . . . . . . . . . . . . . .pace Vehicle Weight vs Flight Time 31

S-IB STAGE. . . . . . . . . . . . . . . . . . . . . .-IB Stage Configuration 33. . . . . . . . . . . . . . . . . . . . . .-I Operatio nal Sequence 34. . . . . . . . . . . . . . . . . . . . . . . . .- I Engine System 35. . . . . . . . . . . . . . . . . . .- IB Stage Prope l lant System 37

. . . . . . . . . . . . .- IB s tag e T hrus t Vec tor Cont ro l Sys tem 39


8/72

LIST O F FIGURES

Figure T i t l e Page.. . . . . . . . . . . . . . . . . . . .3 S-IB S tage Measur ing Sys tem 40. . . . . . . . . . . . . . . . . . . .4 S- IB S tage Te le met r y Sys tem 41

25 S-IB S tage E lec t r ic a l Power and Dis t r ibu tion Sys tem . . . . . . . 42S- IVB S TAGE

. . . . . . . . . . . . . . . . . . . . . .-IVB Stag e Configura tion 45J - 2 Engine Sys tem . . . . . . . . . . . . . . . . . . . . . . . . . . 47

. . . . . . . . . . . . . . . . . . .- IVB Stage Prop e l lan t Sys t em 49. . . . . . . . . . . . .- IVB Stage Pro pe l la n t Ut i l iza t ion Sys tem 51. . . . . . . . . . . . .- IVB Stage T hrus t Vec tor Cont ro l Sys tem 53

. . . . . . . . . . . . . . . . . . . . .uxi l i a ry Propu ls ion Sy s te m 55S- IVB Stage Measur ing Sy s tem . . . . . . . . . . . . . . . . . . . 56

. . . . . . . . . . . . . . . . . . .- IVB Stage Te le met r y Sys t em 57S- IVB Stage E le c t r ica l Power and Dis tr ibu t ion Sys te m . . . . . . . 58INSTRUMENT UNIT . . . . . . . . . . . . . . . . . . . .nst rum ent Unit Configurat ion 61

. . . . . . . . . . . . . . . . .ns t ru men t Unit Measur ing Sys t em 62

. . . . . . . . . . . . . . . . .ns t ru men t Unit Te lem et ry Sys t em 63Ins t ru men t Unit E lec t r ic a l Power and Dis t ribu t ion Sys t em . . . . . 64. . . . . . . . . . . . . .U/ S-IVB E n v i r o n m e n ta l C o n t r o l S y s t e m 67NOSE CONE

. . . . . . . . . . . . . . . . . . . . .0 Spacecra f t 01 1 Configuration 6941 C / M UHF Up-Data L ink and Measurem ent Sum mary . . . . . . . . 7042 Spacecra f t Ins t rumenta t ion Sys t em (TM and Me as . ) . . . . . . . . 7143 S p a c e c r a f t E l e c t r i c a l P o w e r a n d D i s tr i bu t i on S y s t e m . . . . . . . . 72


9/72

LaonchVehicle 142.3'

-&Eight Separation PlanesLaunch Escapesystea 11.4' I 1

Apollo(Block 1)

Vehicle Overall LengthAS-Zo2 space Vehic le\


10/72

F i q u r e 2 Launch Cornplex 34


11/72

------- - - - - - - _ . - -r aunch Control Ce:n+er L C ~ ) utornatic Ground Control Station ( A G ~I (Block house)IIII

Launch Vehicle

Launch Director

Test Conductor

Instrument Unit

Stablization 6

%E ...~_ l e c+v i c a lguPpov+~~viprnenf

Figure 3


12/72

M S E F A C I L I T YPROPELLANT 6 P R E S S U R IZA TION SUBSYSTEMS- - -1N2 P n e u m a t i c C o n t r o l

I D i s t r i b u t o rStoraqe6,000 PSlG ,To RP-1 , LO)( 6-I

LH2 C o n t r o lGN2 50 PSlG

C onsoles* oI E nv i ronmenta lI- - - - - - - - - - - - - - - - - - - - - - - - - C ont ro l System

Gaseous Hydroqen &QGH2 I T o 5 - 1 V B S t a q eFrom Portable S t o r a q e * Pneumat ic Serv ic inqRecharqer 6,000 PSlG; I Valve Panelsf l

G a s e o u sHel ium C o m p r e s s o r s D

GOX I

H eS t o r a g e

LO X LOX( ~ o a d iq) IControl DLO X Transfer SubsystemPumPS I

Pumps ControlSubsystem

I

M S E ..- echanical S u p p o r tEquipment-

From SupplyTrai lers

Fiqure f I L C - 3 4 . P r o ellant andr*ocrurira8m ~ubsy


13/72

Q-eall f io tect ive cavev Re l a s e-

&pollo Access A ~ r n

S i n q rm MO. I- ~ r r v 1 c e 3he S - 1 0Covucavda ~ e o nd +he S-IB inslmrnedcompav~mer\+s.(A~Ccvd i ~ c o n n e 3 in 5c o o n i e t c ~ ~ l r ) l ~ J )

L C 54 Conf iquration


14/72

Manual Sequence I Automafic SequenceCounttime in Uoorr Caun4time in Seconds

Occurs : - - Mold o r recyc le +o 7-15 min.

I- F, TM , Prop., & # c / command checks81111% P ' w e v T v a n 5 te v 1e&r II

I P/Dpe\Ian) lrandev ~ k o c k sI = l o r e l0 Door II IMove sevvics srvoc)umcomplete 5-16 Lox Loadinq I II64 '~system o n

I Arimuth A U q r r m e n j mFind 4 4 ~ heck W

aro undusled prior 40 IA l l Enqinrs Ru~aunchday: I I

I

b rqs and Clush pad are4II-1635

I I- 2 8 s - 3 4 0I I I

Pvepavs)ien$ mpW./o~0 h h APvessvrixe tanks

Fi ore 6-9

No)P r 5-16Fool looding, I Powev hansfev4 - I V ~C T lord~nq, A 40idance mF.and LV ordinance inska~la-tion release

launch Countdown


15/72

LAUNCH VEHICLE SECURE RANGE SAFETY COMMAND SYSTEMSThe sec ur e range sa fe ty command system s on t h e S-IB and S-IVB st a ge s prov id e

a c ommu nica tion s l i n k t o t ra ns mit 'c omman ds f ro m gr ou nd s t a t i o n s t o t h e v e h i c l ed u r in g pow ered f l i g h t , p r o v id in g a p o s i t i v e means o f t e r min a t in g t h e f l i g h t of a ne r r a t i c v e h i c l e by i n i t i a t i n g em ergency en g in e c ut o f f a nd , i f n e c e s s a r y , p r o p e l l a n td i s p e r s i o n .

. Each powered st a ge c on ta in s two UKF r a d i o r e c e i v e r s. Both command receiverson each of th e two s t ag es respond t o th e same command s i gn a ls , each providin g ab ac ku p s y s t em f o r t h e o th e r .

The sa fe ty and a rming dev ice l oca ted on each s t ag e i s armed by a s ignalf rom th e b lockhouse be fore ve h i c l e ig n i t i on . Fo l lowing SyIVB cu t of f th eS-IVB rang e sa fe t y system i s "saf ed" by a command from Range Sa fe ty Co nt ro l t op r e cl u d e a c c i d e n t a l d e s t r u c t .


16/72

Ro t a r y So leno idsConta~ntnqe*plosiv . Icads

(bnttrry * ) L o w Tank5-fV0h$.3-16 t g

(eattery 4 I )1.0. o - 3 0 5 c C .boo waas ou t pu tpourer; then s w ~ t c h dto to,ooo watts

Secure Ron e S s W yCommand %phn 1


17/72

EMERGENCY DETECTION SYSTEM (EDS)The pur po se of t h e EDS i s t o sens e onboard emergency s i t ua t i on s which

a r i s e d u ri n g t h e b o os t ph as e of t h e f l i g h t .The EDS i s comprised of sens ors which de te c t mal func t ion s and log ic

c i r c u i t r y w hic h i n i t i a t e s p a c e c r af t d i s p l a y s a nd , i n two c a s e s , a u to m at i cab o r t o f t h e CM . With th e excep t ion of th e Q-bal l , mounted on top of t h eLET , t h e EDS s en s o r s a re l o ca t e d i n t h e l aun ch v eh i c l e . The system'sr e l a y l o g i c i s l o c at e d p r im a r i ly i n t h e I U EDS D is tr ib u to r and th e CMMiss ion Even ts Sequence Con t ro l le r .

The EDS ha s two modes of o pe ra ti on ; "manual", which gen er at es a b or tcu es and "aut o ma t ic " whi ch i n i t i a t e s f i r i n g o f t h e LES and CM s e p a r a t i o ni n th e case of two S-IB e ngines ou t or ang ular o ve rr at es d urin g S-IB pow-e r ed f l i g h t . F i gu r e 8 i s s im pl if ie d bloc k diagram of th e AS-202 EDS. Thea u t o ma t i c a b o r t i n i t i a t i n g p o r t i o n o f t h e sy st em c o n s i s t s of t h e l a u nc hv e h i c l e ' s r a t e sen s i n g s u bs y st em , t h e S-IB s t ag e t h ru s t s en s i n g s ub s ys t eman d t h e s i g n a l d i s t r i b u t i o n and p ro ces s i n g ha rdware whi ch s e r v i c e s t h e s ed e v i c e s .

The a n g u l a r o v e r r a t e s e n s o r s ( 3 p e r a x i s i n p i t c h , yaw, a nd r o l l )w i l l i n i t i a t e a ut om a ti c a b o r t of t h e CM d u r in g t h e p e r i o d t h e y a r e e n a bl e d( l i f t o f f t o abou t 135 seconds) whenever two sens ors i n any one ax is s imul -t a n e ou s l y i n d i c a t e e x c e s s i v e r a t e s . D e t e c t i o n of t h e o v e r r a t e s i s made byt h e s e n s o r sw i t c h c i r c u i t r y o f t h e C o nt r o l S i g n a l P r o c e s s o r i n t h e I U .The s e t t i n g s f o r t h e s e a ng u la r r a t e d e t e c t o r s a r e 5 d eg rees p e r s eco nd i np i tc h and yaw and 20 degrees per second i n r o l l . T h e m a j o r i t y v o t i n g o ft h e t h r e e s w i t c h o u tp u t s i n ea ch a x i s i s done by r e l ay lo g i c i n th e EDSD i s t r i b u t o r . A v a l i d ex ces s r a t e d e c i s i o n i s fo rward ed by t h e EDS D i s -t r i b u to r t o t h e CM M i ss i on Ev en ts S equenc e C o n t r o l l e r f o r a b o r t i n i t i a t i o n .

The S-IB s t ag e engine th r us t OK s e n s o r s ( t h r e e pe r e n g i ne on a l le i g h t e n g i n e s ) w i l l a l s o i n i t i a t e a b o r t d u ri n g t h e p er i o d t h ey a r e e na b le d( l i f t o f f t o ab o ut 1 36 s eco n ds ) when t h e v o t ed o u t p u t of t h e s en s o r s f romany two en gi n es i n d i ca t e s t h a t t h e t h ru s t o f t h o s e en g i n es i s below the8 9% l e v e l . T hese s en s o r s m o n i to r t h e H-1 en g i n e ' s f u e l pump d i s ch a r g e p re s s u re .M a j o r i t y v o t i n g of t h e t h ree s en s o r s fo r each eng i n e i s done i n th e EDS D i s t r i -b u t o r . A v a l i d two en g in es o u t d ec i s i o n i s s e n t t o t h e M i s si o n E v en t s Seq uenceC o n t r o l l e r f o r CM a b or t i n i t i a t i o n .

In ca s e o f au t o m a t i c ab o r t i t shou ld be no ted t h a t S-IB eng ine cu to f fcommand canno t be g iven u n t i l 60 seconds a f te r l i f t o f f . Af te r abou t 136seconds of f l i g h t , ab or t can be given only by ground command. A ft e r LETj e t t i s o n t h e SM p r o vi d e s t h e p r o p u l s i v e power f o r CM a b o r t .

ED5 Automatic ~ b o v t apability l&cJ60 sec.I II Vehicle Ouevates Auto ~ b o v +Enabled

I \ 3 5 .bsec . , II nuto A b o r t LJJR~OU -~ -10 nq. C u l o f Z ( Auto A b o r t wi4h 5-18 Lnq. cu to f f ' II 1 0sec. Enqine Oot capability

1 6 J I ~ n q . 0 ~ ~ M~l f ip le EnqinerOUT


18/72

Q-Ball L E S o v S P Sabort

Ground

hrame+evs ave: RF ~ b ~ r t5h .6' in P#V2o.H 2 ~e' inRO\ILaunch Director

Sa f e t y

the sinqle J-2

3 ea . l oca ted on each ofthe riqht H-1 enqines


19/72

ILIFTOFFI I IA Disconneci I U Umbilical 1I fO50c II II>1'EnqineO u t " c a p a b i l i t y II 1- j A u t o m a t i c A b o r t capability

I 1. Excessive anqular ra te s, 2. S - I B Two engine outI IProp. level s e n s o r a r m i n g -- 135.8 .I IA A n y prop . leve l sensor acSuates - 137.8I II A n b o a r d Enqine C u t o f f - 1 4 0 . 9I II A Open S - I V B LOX 6 L H 2 p r e v a l v e s -142.2I II E n a b l e LOX d e p l e j i o n c u t o f f -443.4I II A O u t b o a r d Enqine C u t o f f -443.9I II I ( - sec. 1 U l la q e r o c k e t f i r i q

Note: IApprox. t imes I I Ishown are in seconds I A S e p a r a t i o n Command - 144.7m e a s u r e d f rom II U umbilical I I R e t r o r o c k e t f i r inqdisconnect I I I

I I A Movie cameras jettisoned -169.7I II I1 II I

4 1 -ta r t of S t a r t of Start ofTime Base 1 Time Ba s e 2 Time B a s e 3Time Base Divisions

Fiqure 9 S - I0 StageFl i q h t Sequencinq


20/72

200--

Jettison LET@ 1 7 0 s

Sep. - 44.7s

It

" 08 I I I0 ~ 4 3 3 k r n 2,c)oQ 4,000 6 , m

Ground Range (km)Time of launch - - 11:30 4 ~ 1o 5 : 3 0 PM E 5 i~aunchAzimuth - - 100 O E of NFlight Arimufh - - 105' E o-fN~ u i c l a n c e reference release - - 5s before l iftoffS f a r t pitch program a+ L O + 10 sP i t c h +il+ arrest a t LO t 1365 , Pitch angle 60'S t a r t rail pr m at LO + I O ~ a t 17~or 5 sM a c h 1 af- LO + 6 5 5M a r q, a t L O t 795

Figure I 1 Traectory Information


21/72

GUIDANCE AND CONTROL SYSTEM (G&C)Fu n c t io n an d Desc r ip t io n

The G&C s y st em p r o v i d es t h e s e b a s i c f u n c t i o n s d u ri n g f l i g h t : ( 1) s e qu en c in gs i g n a l s , ( 2) s t a b l e p o s i t i o n i n g o f t h e v e h i c l e t o t h e command p o s i t i o n w i t h aminimum amount o f s los h in gsa nd bending , (3 ) a f i r s t s ta ge t i l t program whichg i ve s a n ea r z e r o l i f t t r a j 2 c t p r y t h ro ug h t h e a t m os ph er e and pr o du c es r e a s o n a b l eend condi t io ns a t Outboard Engiae Cutof f (OECO), (4 ) r edu ct i on of wind loa ds du r in gthe high dynamic pr es su re r eg io n , (5 ) s te er in g commands dur ing S-IVB bu rn whichg ui de t h e v e h i c l e t o a p r e de t e rm i n ed s e t o f e n d c o n d i t i o n s w h i l e m a i n t a i n i n g aminimum p ro p e l l an t t r a j ec to ry , ( 6 ) f i n a l c ut o ff s i g n a l , ( 7 ) a t t i t u d e s i g n a l s f o rth e sen s in g , co mpu tin g, and ac tu a t io n e lemen t s of t h e G&C system. A b lo ck d iag ramof t h e ha rdware u sed t o imp lement th es e fu n c t io n s i s shown i n F i g u re 1 2 .

The St a b i l i z e d Pl at fo rm (ST-124M) i s a t h r e e g i m ba l c o n f i g u r a t i o n w i t h g a sb ear ing g yro s an d acce l e ro me te r s mou nted o n th e s t a b l e e l emen t . Veh ic l e acc e l e r a t io n san d ro ta t io n s are s e ns e d r e l a t i v e t o t h i s s t a b l e e le me nt . Gimbal a n g l e s a re measuredby re du nd an t r e s o l v e r s an d i n e r t i a l v e l o c i t y i s o b ta i n ed f rom acce le ro me t e r h eadr o t a t i o n i n t h e f or m o f e nc o de r o u t p u t s ( a l s o r e d un d a nt ) .

The Launch Ve hi c le D ata Ada pte r (LVDA) i s a n i n p ut - o ut p ut d e v i c e f o r t h eLVDC- T he se t wo c om pone nt s a r e d i g i t a l d e v i c e s wh ic h o p e r a t e i n c o n j u c t i o nt o c a r r y o u t t h e f l i g h t p ro gr am . T h i s p ro gr am p e rf or m s t h e f ol l o w i n g f u n c t i o n s :(1) P ro cesses t h e in p u t s f ro m t h e ST-124K, (2 ) p e r fo rms n av ig a t io n ca lc u l a t io n s ,( 3 ) p ro vi de s f i r s t s t a g e t i l t p ro gr am , ( Se e F i g u r e 1 4 ) , ( 4 ) c a l c u l a t e s IGMs t ee r i ng commands, (5 ) re so lv es g imbal ang les and s te e r i ng commands i n t o t h ev e h i c l e s y s t em f o r a t t i t u d e e r r o r c ommands, ( 6 ) i s s u e s c u t o f f a nd s eq u e nc i n gs i g n a l s .

The C o n t ro l Acce le ro me te r s a r e sp r i n g mass d e v i c e s w hi ch s u p p ly s i g n a l st o the C ontro l Computer dur i ng S - I B b ur n. T he se s i g n a l s a r e p r o p o r t i o n a l t ot h e ae rodyn am ic l i f t f o r c e s a c t i n g o n t h e v e h i cl e .

The Control/EDS Ra te Gyro Package c on ta in s 9 g yr o s ( t r i p l e x r ed u nd a nti n 3 a x e s ) . T h e i r o u t p u t s go t o t h e C o n tr o l S i g n a l P r o c e s s o r (CSP) w he ret he y a r e v o t e d a n d s e n t t o t h e C o n t r o l Computer f o r d amping v e h i c l e a n g u l a rm ot io n. T he se o u t p u t s a r e a l s o p r o c e s s e d i n t h e CSP f o r u s e as an au to ma t i cab o r t p a r ame te r .

The C o nt ro l Computer se nd s commands t o t h e S-IB and S-IVB en gi neac t u a t o r s and t o th e C o n t ro l R e lay Packag es b ased o n s ig n a l s f ro m th e LVDAc o n t r o l a c c e l e r o me t e r s , a nd r a t e g yr os . T he se s i g n a l s a r e f i l t e r e d a ndsca led (See F i g u r e l3 ) , t h en summed i n mag n e t i c am p l i f i e r s . Th i s co mp uterprov ides red undant op er a t io n dur ing S-IVB bur n and coa st .

The Control Relay Packages accept Control Computer commands and relay thesecommands t o o p e ra te p r o p e l l a n t v a l v es i n th e Au x i l i a ry P ro p u l s io n Sys tem (APS).A l l re la ys and va lv es a r e redundant . The APS has 6 n o z z l e s ( t h r e e i n e a chmodule) which ope ra te spon taneo usly when f u e l and ox i d i ze r a r e mixed .


22/72

The 8 h y d r a u l i c a c t u a t o r s of t h e S - IB s t a g e a r e u se d t o g im b al t h e o u t-board eng ines and p rov ide con t ro l i n a l l axes . The two hyd r au l i c ac tua to r sof th e S-IVB st ag e ar e used t o gimbal t h e 5-2 eng ine and p rov ide c on t ro l i npi tch and yaw axes.

The Switch S el ec to rs a r e used t o r e l a y se quencin g commands from th e LVDAt o o t h e r l o c a t i o n s i n t h e v e h i c l e . The c u to f f s i g n a l and ti m e b as ed e v e n t sa r e i s sued t h rough t he S wi tch S e l e c to r s .Operat ion

The vehic le i s e rec t ed on t he l aunch pad wi th pos i t i on I a t a 100' E ofN azimuth . The S t ab i l i ze d P la t form i s al ig ne d t o 105O azimuth du rin g countdownand he l d i n a n e a r t h f i x e d p o s i t i o n , p e r p en d i cu l a r t o t h e g r a v i t y v e c t o r . Ar o l l p r e s e t t i n g of 5' i s u se d t o e l i m i n a t e t h e a t t i t u d e e r r o r w hic h w ouldr e s u l t f rom t h i s d i f f er en ce i n az imuth . The LVDC oper a tes i n ground ro ut in esp r i o r t o GRR and a t t i t u d e e r r o r s i g n a ls a r e s e t t o n u l l . A t t h e i n s t a n t ofGRR, th e p la t for m becomes space f ixe d t o es ta b l i s h the guidance coor d ina tesystem and th e LVDC en te r s t h e f l i g h t mode. I n t h i s mode acce l e romete rp r o c e s s i n g , s t e e r i n g , n a v i g a t i o n , t e l e m e t r y , a nd o t h e r f u n c t i o n s a r e pe rf or me de x a c tl y a s t he y a r e a f t e r l i f t o f f .

L i f t o f f s i g n a l (IU u m b il i c al d is c on n ec t ) i n i t i a t e s t im e b a s e 1. Tense con ds l a t e r , t h e p i t c h program s t a r t s a nd t h e i n i t i a l r o l l p r e s e t t i n g i sr e s e t t o z e r o. The v e h i c l e r o l l s i n t o a l ig nm e nt w i t h t h e p l a tf o r m a t1/second. There i s no ac t i ve path guidance dur ing S-IB burn . Cont ro l i smai ntain ed by gi mba l l ing t he fou r outboa rd eng ines on command from th e Co ntro lCompute r. S equenc ing s i g na l s a re i s sued t o t h e va r i ous swi t ch s e l e c t o r s t operform t ime dependent func t ion s .

Pro pel lan t l e ve l sens ing s i gn al and OECO ar e in te r r up ts t o th e LVDCwhich s t a r t t ime bases 2 and 3 . Pat h guidance (IGM) beg ins abo ut 29 secondsa f t e r OECO. S-IVB e ng ine cu to ff i s i s s ue d b as ed on t o t a l s p a c e f i x e d v e l o c i t yand s t a r t s t im e b a s e 4.

The APS i s u se d f o r c o n t r o l i n a l l a xe s d u r i ng S-IVB c o a s t .


23/72

Located on to p of .Launch kscapr l ower/

Transducer2 Z Z Z I T T L ~ ~ - I L - L / U U n I n m - I

UNIT- - ---A f o ED 5

~ i 5 t r iutor

Provides rol l controldurinq S - VB poweredC l i q h t an4 $ i t c h , yaw ,and roll con vet duvlnqcoosf.

To con-trol actuators+or enqiner I, 2 . 3 6

+_B0swivel anqle6Ocant angleInboard enqines3'cant angle to S - 1 6 systems

System lock Piaqram


24/72

v 5-1eControl Accel.* Sc ri q OF r eboa Pir d ' 0 eon re \ torqueaccJ\eva%on

Functional Diaqram of G$ C SystemsCOMPUTlN6 ELEMENTS3 ENSl NG ELEMENTS

comrncnd toincuyp vaS\icb( Rate Gyros 1 s4ab~ltt and v c d mwm d \gadsvehicle 'I a na u i a v rates I

LVDA /LVDC.Navi ation ~alculat ions~ ~ ~ c d d i o nF ~ e e v t n qcommands ba re d o nt i m e o r IGM.. a\cv la t ien of Y.benevahbn ofStabilized PlatformSe.nsinq.of s n ~ l a ror~enta on a velocityvala t ive t o the inev l ia lc o o r d i n a t e s y s t e m

I --- 'wid *8 =

Typical Shapinq Network Characteris tics - S-10BurnAmplitude I s t mode A .--I A A I L ?' . lwSha~i l 7a networkratio nrnpl. r.vmode

p, y ampl. ratio 0.1A .

Phasela4

~ .. ... ..p, y ampl. ratio

r n a s e-18004,e a q

AWI~I,"[.1 k (P;,~ phase laqbendirrq modes

Pitch and ya w attitude e r r o r ( 9 p , v )Shaoina network

N o t e : S-I8 4~ and S-lV8 'f'p, y , R f i l tersh a v e simi lar ch arac t e r is t i cs ;a l s o t r u e fo r 9 p , y , R f i l t e r s

,"" F r e g - c p s

? ~ p , ~ phase l a q.T p , y S h a p i n q network

AS-202 Co nt r o l System Design Obje ct ive sThe d e s i g n o b j e c t i v e s u s ed i n d et e r m i ni n g t h e c o n t r o l g a i n s a n d

shap ing ne tworks d u r ing bo th S-IB and S-IVB s t ag e bu rn a r e t o p rov id ea d e qu a te v e h i c l e r e sp o ns e a nd s t a b i l i t y ma r gi ns t hr ou gh ou t f l i g h t . P a s s i v es ha pi ng n et wo rk s a r e u sed i n t h e a t t i t u d e e r r o r and a t t i t u d e r a t e c ha n ne ls .A c t i v e s h ap i n g i s u s ed i n t h e acce l e r o m e t e r ch an n e l s . The n e t w o r ks a r etuned t o p r ov id e minimum phase l a g a t s l o s h f r e q u en c i e s c o n s i s t e n t w i t hg a i n s t a b i l i z i n g a l l b e nd in g modes e x c e p t t h e f i r s t be n di ng mode d u r i n gS-IB s t ag e bu rn . The f i r s t bend ing mode du r ing S-IB s t ag e bu r n i s p h as es t a b i l i z e d .

4uidance and ControlI ~ y s t e r n~nform o t m n I


25/72

Conhol 5u d ern Gain Factorsa o = deq /deqa, s deq /deq / Jq, : aq / m/s *

1.0 SEP. 5- IVB C.O.- -20 s -4005Axis ~ e r m5 .5 5o- +a I

and a1 t.0_ _ _ _ _ _ _ - 0.8 4 0 --- - - - ----- - a.0 . 7 aI6s Hob

I I-J 1736 - - - - - - ---+G c c X . EonCL ~ c + i J e I r - - p a ~ h uidance ac+ioe I1 L -- - - - - --- - - -1_ _ _ _ _ _ _ _ - _ _ - - - - - - - - - - -

Con+ra\ ~ a t e y r ~ s c4iue -3 -------------------I I

Pitch Procrvam

sI ~ R ~ C C

Vehicle Conkol System andPitch Proqram InForma~ion


26/72

VEHICLE TRACKING SYSTEMS1. Aiusa and.C-Band'Radar.Systems.

The Azusa g ro un d s t a t i o n d e te rmin es s u cces s i v e t r a j e c t o r y p o s i t i o n sof th e veh ic l e by con t inuous phase compari son between t he s ig na l s t ran smi t t edt o t h e r ec e i v e r f ro m t h e o nb oa rd t r an s p o n d e r. The C-Band Rada r Tr an sp on de ro nb oa rd t h e v eh i c l e p ro v i des (upon in te r ro ga t io n f rom th e ground) a s i ng lepu l se re p ly t o ground rada r system. T h i s s i g n a l i s fed t o t he g round computercomplex t o o b t a i n p o s i t i o n , v e l o c i t y , and acc e l e r a t i o n i n fo rma ti o n . T ra j e c t o ryda ta f rom th e l aunch veh ic l e Azusa and C-Band ar e p resen ted on p l o t t i ng b oardsf o r t h e r a ng e s a f e t y o f f i c e r t o u s e i n d e te r mi ni ng " r e a l t im e" v eh 'i cl e t r a j e c t o r yparameters . In a dd i t ion , the l aunch ve h ic le Azusa and C-Band ar e used f o r th ep o s t f l i g h t d e t er m i na t io n of t h e v e h i c l e t r a j e c t o r y .

2 . ODOP SystemT h e v eh i c l e ' s ODOP t ransponder t ra nsm i t s a con t inuous wave s ig na l

( a t 70 mc abo ve t h e r ece i v ed f r eq u en cy ) t o t h e g ro un d r ece i v i n g ' s t a t i o n sw he re t h e d o pp l er s h i f t (d ue t o t h e r a d i a l a c c e l e r a t i o n o f t h e v e h i c l e ) i s usedt o pr o v id e t r a j e c t o r y d a t a f o r t h e p o s t f l i g h t e v a l u a ti o n of v e h i c l e p e r-formance.VEHICLE TELEVISION SYSTEF

A t e l ev i s i o n camera and fo u r l i g h t s a r e l o c a te d i n t h e s p a c e c r a f t a d a p t erf o r v iewing Adapter pane l deployment and Spa cec raf t sepa ra t io n. The cameraco n t ro l u n i t and t r an s m i t t i n g equ ip ment a r e l o c a t ed i n t h e In s t ru men t U n i t .


27/72


28/72



29/72


30/72

SPACE VEHICLE WEIGHT VS. FLIGHT TIMEPropellant consumption during S-IB Stage flight ("145 seconds) is "886,000pounds and during S-IVB Stage flight (-457 seconds) is "226,000 pounds. Pro-pellant consumption during the 4 Apollo SPS burns (total of "326 seconds) is"21,500 pounds.

In case one engine of the S-IB Stage malfunctions and is cut off duringflight, the remaining engines will consume the propellant intended for the"dead" engine. Burning time of the stage would increase, and the overallvehicle performance loss would be minimized.Vehicle Weight Data (Approximate) PoundsTotal at S-IB ignitionTotal at liftoffTotal at S-IB O.E.C.0Total at S-IVB ignitionTotal at S-IVB cutoffTotal after CM/SM separationTotal after CM separation


31/72


32/72

S-IB STAGE STRUCTUREThe S-IB s t ag e co n s i s t s o f f o u r 7 0 - in ch d i am e t e r fu e l co n t a i n e r s m ou nt ed

a l t e r na te l y wi th f ou r 7.0- inch d iam eter LOX con ta ine rs a round a 105- inch d iam eterLOX co nt ai ne r . The co nt ai ne rs a r e supp orte d a t t h e b a s e b y a t h r u s t s t r u c t u r ea ss em bl y t o wh ic h a r e a f f i x e d e i g h t H-1 eng ine s . The sp id er beam assemblyp r o vi d e s t h e s up p o rt s t r u c t u r e a t t h e f o rw a rd en d o f t h e c o n t a i n e r s a n d s e r v e sa s a n a da p t e r f o r t h e S-IVB i n t e r s t a g e . E i gh t f i n s a r e mounted a t t h e b a s e oft h e S-IB s t a g e t o im pr ove ae ro dy na mi c s t a b i l i t y , a nd p r o v i d e p r e - f l i g h t s u p p o r t ,and holddown of th e ve h i c l e .PROPULSION SYSTEM

The f i r s t s t a g e of t h e la un ch v e h i c l e i s powered by a c l u s t e r of e i g h tRocketdyne H-1 e n g i n e s d e ve l op i ng a t o t a l s e a l e v e l t h r u s t o f 1 , 60 0 ,0 0 0 po un ds .Fou r en g i n es a r e m ou nt ed o u t b o a rd an d fo u r i n b o a rd ; t h e fo u r o u t b o a rd en g i n esa r e g im ba le d f o r v e h i c l e c o n t r o l . The pr o p e l l a n t s a r e LOX and RP-1.

EJECTABLE CAMERA CAPSULESTwo e j ec t a b l e cam eras a r e ca r r i ed o n bo ard t h e S-IB s t ag e f o r t h e p u rp o s e

of v iewing S-IBIS-IVB s t ag e sep ar a t io n and o t he r phenomena ass oc ia te d wi t hp e rf o rm a nc e o f t h e v e h i c l e d u r i n g s e p a r a t i o n . The ca me ra e j e c t i o n s y st e m c o n s i s t sof a h i g h - p r e ss u r e s t o r a g e s p h e r e , two s o l e n o i d c o n t r o l v a l v e s , two c am er a e j e c t i omechanisms, and th e nece ssar y va l ves , tub in g , and as so c i a t ed hardware .

The c am er a c a p s u l e s a r e mounted i n t h e s e a l p l a t e a t t h e t o p o f t h e S-IBs t ag e an d w i l l b e e j ec t e d t wen ty - f i ve s econ d s a f t e r S-IBIS-IVB s ep a ra t i o n . Thec a p s u l e s w i l l f o l l o w a b a l l i . s t i c p a t h t o a n a l t i t u d e of a p pr o xi m at e ly 1 4 ,0 00f e e t . A t t h i s p o i n t , p a ra c hu t es w i l l b e d epl oy ed t o d e c e l e r a t e t h e c a p s u l es .lota at ion bags (approx imate ly 20 i n c he s i n d ia m et e r w i t h a l t e r n a t e c o l o r e dp a n e l s of i n t e r n a t i o n a l or an ge an d s i l v e r ) a r e p ro v id e d t o ke ep t h e c a p s u l e sa f l o a t a f t e r i mp ac t.

Fo r r eco v e ry , t h e cap s u l e s a r e eq ui p ped wi t h SARAH t r an s m i t t e r s t h a t o p e ra t eon a fr equ enc y of 242 mc, a nd h av e a b a t t e r y l i f e of a p p ro x i ma t e l y 30 h o u r s . Thee f f e c t i v e ra ng e of t h e t r a n s m i t t e r s i s approx imate ly twen ty -f ive m i le s . I na d d i t i o n , a dye marker i s a l s o r e l e as ed t o a i d i n a e r i a l s i g h t i n g .


33/72


34/72

H-1 ENGINE OPERATIONA s t a r t s i g n a l i g n i t e s t h e s o l i d p r o p e l l a n t g a s g e n e r a t o r (SPGG) wh ic h

ac ce l e ra t e s t h e LOX and RP-1 pumps . Inc rea s in g fu e l p re ss u r e opens t he mainLOX v a l v e w hi ch , i n t u r n , o p en s t h e s equ ence v a l v e p e r m i t t i n g f u e l p r e s s u r et o r u p t u r e t h e h y p e r g o l i c c a r t r i d g e . P ri ma ry i g n i t i o n o c c u r s when t h e RP-1and h y p e r g o l i c f l u i d co n t ac t LOX i n t h e t h r u s t chamb er . The i n j ec t o r f u e lp r es su re opens t he main RP-1 va lve a n d . p r o vi d e s p r o p e l l a n t f lo w t o t h e l i q u i dp r o p e l l an t g a s g en e r a t o r (LPGG) wh ich s u s t a i n s t u r b i n e o p e r a t i o n .

The d i g i t a l c omputer i n i t i a t e s i n bo a rd e n g in e c u t o f f 3 . 1 s e c on ds a f t e rt h e p r o p e l l a n t l e v e l se n s o r a c t u a t i o n . O ut bo ar d e n g in e c u t o f f i s n o r ma l lyi n i t i a t e d by t h e LOX d e p l e t i o n p r ob e s , w i t h t h e f u e l d e p l e t i o n p r o b e s , t h ed i g i t a l co mp ut er , an d t h e t h r u s t OK s w i t c h e s p r o v i d in g ba ck up c a p a b i l i t i e s .B ot h c u t o f f s i g n a l s a r e r o u t e d t h ro u gh t h e S -IB S t a g e s w i t c h s e l e c t o r . Thecu t o f f s i g n a l o p en s t h e ex p l o s i v e l y a c t u a t ed C onax v a l v e e q u a l i z i n g t h e RP-1p r e s s u r e a t t h e m ai n LOX v a l v e . The v a l v e c l o s e s t o i n t e r r u p t f u e l f l o w andt e r m i n a t e e n g i n e o p e r a t i o n .

SPGG I g n i t i o nSPGG Combust i o nMain LOX Valv e (Open)Hypergo l Car t r i dge Rup tu resP r i m a r y I g n i t i o nMain RP-1 Valve (open)Ma in I g n i t i o n ( S t a r t )LPGG Op er at i o nMains t age Thrus tConax Valve Actuates

6h r us tI

0 1 2 3 0 i 21 sec . sec .I

set. set.I q n i t i o n L i f t o f f CutoffCommand Signal

- T im e from I g n i t i o n *Time from Cutof f

Fiaure 14 H - f Operational[


35/72

RP-I LOX

Pressure System

LOX Tank Mixture Rat ioPressurization LOX: RP-I , 2.23:l

Thrust chamber'R P - I Preheat 200,000 Ibs Thrust

Fisure 20 H - Enqine Sys t ems


36/72

S-IB STAGE PROPELLANT SYSTEMThe S-IB Stage propellant system is composed of five LOX tanks, four

RP-1 tanks, propellant lines, control valves, vents, and pressurizationsubsystems. The sumps of each group of tanks are interconnected to provideuniform propellant levels and pressures. Loading of LOX and RP-1 tanks iscontrolled by ground computers. After the RP-1 has been loaded and justbefore the start of LOX loading, ground source GN2 is bubbled through theRP-1 suction lines to prevent temperature stratification. At the start ofthe automatic sequence the RP-1 tanks are pressurized with ground sourceGN2. During S-IB burn, fuel tank pressurization is maintained by GHefrom two 19.3 cubic foot spheres located above two of the fuel tanks.Sround source helium is bubbled through the LOX lines and tanks at thestart of the automatic sequence to prevent temperature stratification inthe engine LOX suction lines. Prior to engine ignition the bubbling is dis-continued and the LOX tanks are pressurized with helium from a ground source.After liftoff, the LOX tank pressurization is maintained with GOX convertedfrom LOX in the heat exchanger.

I I Start Automatic (P


37/72

for R P - 1 TankPressurization

open - 67.5 psia 60 - 6 2 p s iclose - 64psia 59.0 psia

/RP-1 Tank (4 )

R P - I be low c o n t a i n e rLOX below container bottom atbottom at L i f to f f &5,700 Ibs.Lif to f f ~ 8 , 8 0 0bs

GHe from GSE for --initial LOX Tankp r e s s u r i z a t i o n

in f l iqht pressurization Total propellant a t l i f t o f f ^) 897 ,000 I b s -T o t a l propellant consumed after l i f to f f

N 886,000 bs.

Fiqure 21 P r o p e l l a n t S y s t e m


38/72

S-IB STAGE THRUST VECTOR CONTROL SYSTEMEach of the four outboard H-1 engines is gimbal mounted on the stage

thrust structure to provide engine thrust vectoring for vehicle attitudecontrol and steering. Two hydraulic actuators are utilized to gimbal eachengine in response to signals from the Flight Control Computer located inthe ~nstrument nit.The actuators are part of an independent hydraulic system on each

gimballed engine. Hydraulic fluid flows to the actuators from the highpressure accumulator and returns to the low pressure reservoir. Theelectric motor driven auxiliary pump operates only during prelaunch check-out of the thrust vector control system.


39/72

Low Pressure 53 p s i q- - - - - - - -

Vehicle ThrustGimbal Point Structure - ActuatorAttachment Point

movement as commandedby Flight Control ComputerHydraulic Actuator (2)

Electric MotorDrive at 11,300 -prnOutput 3.0 gpm

Actuators \

Inboard Enqine (4 )Fixed Position; ICanted Outboard 3"

Fiqure 2 2 Cont ro l S y s t e m


40/72

r >Summary of M e a s u r e m e n t s

'5-113 StaqeMaasurinq System

I n f l i q h t1. L i q . L e v e l

* - 128 block housa mea. arealso ~nfliqh*mea. Note :Theve w e r e -498 inFli1ht aud -176Lc measuramtnt on S-WlTo Rlockhouse th ru pre f l ightdata a c q u i s i t i o n system

T r a n s d u c e r o rSiqnal S o u rc e sT h e rm o c o u p l e

s t r a i n GauqeA c c e l e r o m e t e r

( V i b ra t i o n )Vol taqe ,S en so r , e t c .

Measur ing R a c k /\q n S-It3 StageS i q n a l s ( l i f t o f f , c.o. , I IVcltaqo IDividinql Ie t c . ) * etwork1 I

2 8 v d c I L - - _ J- 1 II II 1P o t e n t i o m ~ t e r y p e 0 - 5 V ~ C

b p re s s u re q a u q e , d Ilonq. accel., e t c . ) I I5 Vdc 1 I

S - 16-222

\

2 . T e m p e ra t u re 1653 . P r e g s u r ~ 9 84. S t r a i n 1245 . Vibration 636. Signals 637. Voltaqe, Currevt, r req . 268. Miscel laneous 20-

T o t a l .* 521LCC lockho house) -%68*-

1- I I

I IIL - - - - - l- o n t i n u o u s l iq ui d D i q i t a I Data TOl e v e l D T e l e m e t r yS y s t e m


41/72

Hardwire toB l o c k h o u s eA F 1

Digital Data PAM ~ M / F MAss'yinput

Remote

Antennas Command SignalsFrom S-10 St8qe9 ~ i i c h alectorSS - Sinqle Sideband S-18,'s-IVBFM - Frequency Modu l a t i o n Separa t ionDDAS - Diq i ta l Data Acquisition System CommandS tar t s timerPAM- Pulse Ampli tude Modu l a t i o nPCM Pu lse Code Mo d u l a t i o n Time* 'A s 'YTM - Te l eme t r y ,(L6 S QC ) Recordin)R F - Radio F r equency Stop record Command.o. + 39playback command see,sep. + 26 sec.4 /

I p u ~ i i i ~ e x e r peasur inqd i s tr i b u to t sDiqital Data

~ S I O W S ~ ~ ~Mult ip lexer

FromSwitch Selectorinput I

Recorder'$y/ ! i i redVibtationdot4 .kom mrsruvinq transtnittinqAss'ydi&l bu i ~ r sSj;FMA S ' y

Calibrator

iTo FI , F2 $ P1 Multiplexer

.c r

* ~ l s o ar ri e s m u lt i pl e xe ddata f rom F1 # F 2

4

s.16 ctaqeloremetry System

Tape $ o r recordinq,ASS^F

f

252 .4 r n ~-4 ~ s s ' y rF1 RF Infernal

240.2 mc switch;nq


42/72

To Se pa ra ti on EBW

5 - I V B Staqa

1 '28vdr + 5T vdcTo 5-16 Stage M a s t e rMeasuringSwitch Selector To both des t ruc t Voltaqesys tem controllers SU P iTO al l tailmeas. dist . ~ n s t r u m e * f

Com partmtnf F( Pressurized)- - - - - - - - - - - - - A

Siqnals f r o m Tail Area(UnpressurirePropu l~ i on System meas. racks and meas. racks andD i s t r i b u t o r

To TMSys tem

Tomeas. racks

Figure 25- -- II S-I6 Staqe E \ec i ' r i c~ l owerand D i s h i bution System


43/72


44/72

S- IVB STAGE STRUCTUREThe S-IVB Stage consists basically of an aft interstage, an aft skirt,a structure, a divided propellant container and a forward skirt.Aft Interstage The aft interstage, also referred to as the S-IBIS-IVBinterstago, is a semimoncoque structure which supports the S-IVB Stage, theInstrument Unit and the Apollo Spacecraft payload prior to the S-IBIS-IVBseparation. The aft interstage provides mounting facilities for retro-motors.Four Thiokol TE-29-IB solid propellant retro-motors equally spaced circum-ferentially provide thrust to impart a negative acceleration to the S-IBStage and the aft interstage after the explosive skin dutting separation atthe aft interstage/aft skirt interface.Aft Skirt The aft skirt is a semimonocoque structure which attachesto the end of the cylindrical portion of the propellant container. The aft skirthouses electrical and electronic components as noted in figures 32, 33, and 34.Three Thiokol TX-280 solid propellant motors equally space circumferentially prov

a positive acceleration to the S-IVB Stage to settle propellants for 5-2 enginestart. The aft skirt also provides mounting hardware for two attitude controlmodules diametrically opposed. Each module contains three TAPCO 150-pound thrust(vacuum) hypergolic CMMH and N204) rocket' ngines.Thrust Structure The thrust structure is a truncated cone with longi-tudinal stiffeners. The forward end (large diameter) of the cone attaches tangentially to the aft bulkhead of the propellant container. The thrust structureprovides attachment points for the engine gimbal mount and the hydraulic actuatorA single 5-2 rocket engine of 200,000 pound nominal thrust (vacuum) is installedon the centerline of the S-IVB Stage.Propellant Container The propellant container is an internally insulatedcylinder with hemispherical bulkheads at each end. An internal hemisphericalbulkhead with the concave side facing aft divides the propellant container intoan aft section for LOX and a forward section for liquid hydrogen. Eight coldhelium spheres located in the hydrogen tank provide LOX tank pressurization. Anambient spherical helium bottle mounted on the engine thrust structure providespneumatic control pressurization throughout the vehicle pressure system.Forward Skirt The forward skirt is a semimoncoque cylindrical structurewhich attaches to the forward end of the cylindrical portion of the propellantcontainer and supports the Instrument Unit and the payload. The forward skirthouses electrical and electronic components (most mounted on coldplates) and'provides external mounting for telemetry and command antennas.


45/72


46/72

5-2 ENGINE OPERATIONThe normal operating cycle of the 5-2 Engine consists of prestart, start,

steady-state operation, and cutoff sequences. During prestart, LOX and LH2flow through the engine to temperature-condition the engine components, andto assure the presence of propellant in the turbopumps for starting. Aftera timed cooldown period, the start signal is received by the sequence controllerwhich enei-gizes various control solenoid valves to open the propellant valvesin the proper sequence. The sequence controller also energizes spark plugs inthe gas generator and thrust chamber to ignite the propellant. In addition,the sequence controller releases GH2 from'the'start tank. The GH2 providesthe initial drive for the turbopumps that deliver propellant to the gasgenerator and the engine. The propellant ignites, gas generator output accel-erates the turbopumps, and engine thrust increases to main stage operation.At this time, the spark plugs are de-energized and the engine is in steady-state operation.

Steady-state operation is maintained until a cutoff signal is receivedby the sequence controller. The sequence controller de-energizes the solenoidvalves which in turn close the engine propellant valves in the proper sequence.As a result, engine thrust decays and the cutoff sequence is complete.


47/72

P r o p e l l a n t utilizationvalve regulates LO X#low t o minimize LHzand LOX res iduals a-1.cuto ff . Var ies mixtu reretlo *, f O %LH2b1

Pressur i za t ion

- - - - - - - - - - - - - - -

Thrust C h a m b e r

Mixture Rat ioLH2 circulates thruThrust chamber wallt o cool wall

200 ,000 Ibs Thrust


48/72

S- VB STAGE PROPELLANT SYSTEMThe S-IVB propellant system is composed of integral LOX/LH2 tanks, pro-pellant lines, control valves, vents, and pressurization subsystems. Loadingof the propellant tanks and flow of propellants is controlled by the propellautilization system. Both propellant tanks are initially pressurized by grounsource cold helium. LOX tank pressurization during S-IVB Stage burn is main-

tained by helium supplied from spheres in the LHi tank, which is expanded bypassing through the helium heater, to maintain positive pressure across thecommon tank bulkhead and to satisfy engine net positive suction head. The LR,pressurization strengthens the stage in addition to satisfying net positivesuction head requirements. After engine ignition the pressure is maintainedby GH2 tapped from the engine supply.S-IVB PROPELLANT LOAD AND OPERATIONAL SEQUENCE


49/72

LH2 Tank r--IVent Valve

(Pressure -tepped lowly to , I39 psia v e n t sethnqa t S-IVB i gn i i ion I GHz from J-2+300 sec.) / i n duringS - I V 8 burn fo rSpheres for LOX I I messu r i z a t i o nTank pressur izat ion (8),

-LOX Tan k- Vent ValveLH2 Fi l l f Drain

192,900 lbs at Iqn i t ion LOX Fi l l @ Drain

Helium & I J-2 EnqineI--LH2 Tank contains-1,000 Ib s at J-2 enginecu to f f . LOX remaininq a tJ-2enqine c u t o f f- 2,400 bs.

-

Helium . Heater c o n t i n u e s t opressurize LOX Tank beqinninq-10 sec. after mainstage start

Total propel lant at l i f t o f f - 2 3 0 , 4 0 0 Ibs.Total propellant consumed after l i f t o f f- 2 2 6 , 0 0 0 Ibs.

tank


50/72

PROPELIANT UTILIZATION SYSTEMThe propellant utilization (PU) system controls loading and engine

mixture ratios (LOX to LH2) to ensure balanced consumption of LOX and LH2.Probes mounted in the LOX and LH2 containers monitor the mass of the

propellants during powered flight. At PU activation (6.8 seconds after 5-2ignition), the probes sense the LOX overload and commands the engine to burnat the high rate engine mixture ratio of 5.5:l. When the high mixture ratiois removed, the PU system will then command the engine to burn the referencemixture ratio of 4.7:1, striving for simultaneous depletion of LOX and LH2for maximum stage performance.


51/72


52/72

S-IVB STAGE THRUST VECTOR CONTROL SYSTEMThe s ing l e 5-2 engine i s gimbal mounted on thy lo ng i tu d i na l ax i s o f

th e S-IVB Stage. Power f o r gim bal l in g i s s u p p l i ed by a h y d r a u l i c c o n t r o lsystem mounted on t h e eng ine.

P i t c h and yaw con t ro l , dur ing powered f l i g h t , i s mainta ined by ac tua toc o n t r o l of t h e e n g in e t h r u s t v e c t o r . R o l l c o n t r o l of t h e s t a g e i s maintaineby p r ope r l y s equenc ing t he pu l s e - f i r e d hype r go l i c p r ope l l a n t t h r u s t m o to r si n th e APS. When th e s ta ge en te rs t he c oa s t mode, th e APS th r u s t motorsc o n tr o l t h e s t a g e i n a l l t h r e e a xes .


53/72

Low P r e s su r e- 169 ps i 9 1Z i e


54/72

AUXILIARY PROPULSION SYSTEMThe APS c o n s i s t s o f two s e l f - c o n ta in e d a t t i t u d e c o n t r o l mo du le s mou nted

1 80 d e g r ee s a p a r t on t h e a f t s k i r t of t h e S-IVB s t a g e . Each a t t i t u d e c o n t r o lm odu le c o n t a i n s t h r e e t h r u s t m o to rs wh ic h u s e h y p e r g o l i c p r o p e l l a n t ( n i t r o g e nt e t r o x i d e (N2 O4 ) and monomethylhydrazine (MMH) . The t h r u s t m o t or s a re p u l s e -f i r e d a nd no i g n i t i o n s y s t e m i s r e q u i r e d . The th r u s t mo to r s p r o v id e p i t c h , yawa n d r o l l c o n t r o l d u r in g t h e S-IVB c o a s t mode of o p e r a t i o n , and r o l l c o n t r o l d u ri ngp o w e r e d f l i g h t s .


55/72

Heiqht -80"Width .v 23"

Outer Module ~&a l PS Propellant134bs .

Be l l ows( Pressur l zod\

Tank II II50 Ib. Thrust I I I

eparat ionPlane -

111 111 ILL

Veh ic le Yaws

II

V i ew f r om a f tlookinq fo rwa rd o rdownr anqe

Fiquve 31

Vehicle Pitches

1 1 Auxiliary Propulsion Swtarn I


56/72

Nde: Yheve were -468 inC~iqhtbnd -128 ~ c cn e l l u v e r n a n t ~On j - r v a * lu m m a r y of Measurements

T r an r d u cer or d

I n f l i q h tI. Liquid L eve l2 . T e m p e r a t u r e3. P r e s s u r e4, S t r a ~ n5 . V i b r a t i o n6. S i r ) n a l s7. a , e n t8 Misce l laneous

T o t a l

LCC (Bloc kh ou s e )

S i s n a l SourcesR e f e r e n c eTher mocouple

(6in forwsvd

S- IV6 .26

Ib37 qI t3878++ 11 ;*mii

r 1 5 5 ~ 1

Re s i s t a n c e Thermometer skirt/ 10 nA F ~ ~ i r t )Crystal Vibration Pickup

Strain Gauqer iqnals (switches,etc . )S i q n a l s ( sw i t ches , etc.)

Br idqe Boxes- I s o l a t i o nBoxes* D is t r ibu tor s( vol taqedividinq

networks)

Voltage- s o a r c e sL o t e n i i o r n e t c r T y p e

(Pr essur e Ga u q e , e t c - ) T o T M


57/72

An t e n n a s

P o w e r

Yo F - l , 1 , 3 , 5-1 & P-1

f r o m .-\O+ Used switch S e l e c t o rI Du r i n g FliqhtFrom TnputsS-1 Multiplerer


58/72

Note : h044 f o v ~ a r dnbtrdbqc ComponentsA r e Mounted On Coldp la tes

A f t Skirt--

C r 4Battery f I Battery *220 vdc 28 vdc70 amp. hr. 1.9 amp. hr.

L To Ranqe

56 vdc14 amp. hr.

To Ranqe S a f e t y* S y s t e m NO.i

Meas . Voltaqe TO Meas.* Systems28 vdc

47 amp. hr.

-...- .- S a f e t yv S y s t e m

S-\vB Staqe Elechical ?Power and ~ i r t v i b u t i o n @em

Ground P ower Distrihrr.tor No.2P O I * Q ~

Ground .fI P ow e r D i s t r i b u t o r -- rounPower Distr ibutor PoweTo ToP PU TO Meas.Forward Skirt Systems---I_ -__-___- - - - - - -- - - - - - - - - - - - - - - - - - -

28VDC

1TO Contro lRelay Packaqa

v +Sequencer

)

VTo S - IVBSystems

t

v

From 1Switch TO Sw i t c hSelector Selector

Co n t r o lD;s+ribuior

Chilldown Sys.(Fuel +foxidizer)TOUl\aqe To

Pressurizat ionS y s .

Enqinet

ToAux. Hyd.Sys .V To

To EDS'ITo J-2


59/72

I n t e n t i o n a l l y L e f t Blank


60/72


61/72

ControlCornputow IU7 8

Splice0), comb

LZ)

-

3L in .-


62/72

* 174 b lockhouse meas . are a l s o u s e das in f i q h t meas.Thcve weve -3 0 3 infliqh+ and N \ T tLcc mea s u v emed ~on 5-1U.201u mma r y of M e a s u r e m e n t s

To o the rmea s u r inq racks

In4 ghtVol taqe,Current i Freq.Pos. Anqular Veloc i ty- -Temperature - - . .. .Pressu re f Flow Rate--

Used f o r g r o u nd/ heckout o n l yT r a n s d u c e r o rSiqnal Sources

ThermocoupleAcce le romete r( Vibra t ion)Er ro r S iqna ls( compu te r 4p la t fo rm )

- - - - - - -

( T o t a l - 9 )

S i q n a l s ( p r s t M o ti on ,Separat ion, etc.) 20vdc I L - - A I- 1 II IPotent iometer Type 0 - 5 v d c I I( pvess. q a u e ,io*q. acce?, ete.) 5 vdc I- IL - - - J ToDiqital OataGuidance Sys+em * T e l e m e t r yystem

S-IU-203-244557

F i q u r e 36

V i b r a t i o n - . - - - - - - - 6Guidance $ Co n t ro l - - - 46Dis c re t e S iq n a l s , - - - - 57M i s c e l l a n e o u s - . - . 20

298L C C ( lockh house)- - 182.

Inshumen+ UnitMeasuvinq ~ ~ c + c r n


63/72

5-10 Prop l e v e l S - l V B enqine C - 0 .sensor activation + 38.3 sec .Playback Stops:

- Recordtno, Stops: S - l V 6 enqine c . o5-16 O E C O + 68.3 sec.Inputs From

From Calibrator Cal ibra torSwitch selector- c ~ ~ + ~ ~ ~,,it --m *To F1, F2, S-1 & P-1Ass'yC

Fiqure 37


64/72

Aux. Pw r . To C-Band Radar,Azusa,TV cameva and Meas. racks.

II nstrument Unit ElactvicalPower and D i d v ibufi on Iystem

4To B a t f e r y51-124M 2, ,,.,PlatCovm 300 H~(ac power),t Ground powerZB v d c-

B a t t e r y28 v d c

300 Amp Hr .TOWDAt

4 IC o n t r o l I P o w e r 4 56vdc ' 5 6 vdcD i s t r i b u t o r Dist r ibutor 28 vdc Power\ SUPP'Y

A A A A l ,.

C . 2Batlevy TO Battery28 vdc coolinq 28 V ~ G

I 3 0 0 Amp. t\r. Pump 300 A m p . H r . TO Spacecra f tContro l and Q - B a , \Computer

v D a t aA d a p t e r EDS- i s t r i bu to r9 *I u 4 aSwitch Selector

'IS-16and S-\VBstaqesVST- 124 M pl&bvmelectvonic assy .

as . racks andas . transducers

'IC o q t r o lProces

vs - I V BStaqevS-I8Staqc


65/72



66/72

ENVIRONMENTAL CONTROL SYSTEM (ECS)Heat generated by the electronic equipment located in the S-IVB forwardskirt and the IU is absorbed by circulating a methanol-water solution throughthe coldplate network.Prior to liftoff, a temperature controlled methanol-water solution issupplied and circulated through the coldplates from the GSE. After liftoff the

ECS is a selfcontained unit which begins operation 3 minutes after liftoff whenthe sublimator is activated.


67/72


68/72

SPACECRAFT DESCRIPTIONSp ace cra ft 011, f o r Mission AS-202 i s composed of a Launch Escape Tower,

Command Module, S e r v i c e Module, and Lun ar Module Ad ap te r.Command Module (CM)The CM i s made up o f a n i nne r s t r uc tu re , o r p re s su re ve s s e l , a nd an

o u t e r s t r u c t u r e . A l a y e r o f i n s u l a t i o n s e p a r a t e s t h e i n n e r and o u t e r s t r u c -t u r e s . The h e a t s h i e l d ( o u te r s t r u c t u r e ) c o n s i s t s o f : A f or w ar d h e a t s h i e l d ,a c rew c ompa rtmen t he a t sh i e ld a nd a n a f t he a t sh i e ld . A b l a ti v e m a t e r i a l i sbonded t o a l l h e a t s h i e l d s t a i n l e s s - s t e e l , b r a ze d honeycomb s t r u c t u r e .

Ser vic e Module (SM)The SM i s a c y li n d r ic a l s h e l l made up of aluminum, honeycomb-sandwich

pan e ls and forward and a f t bulkheads . The SM pr op uls ion en gin e gimbal i sa t t a c h e d t o t he a f t bu lkhe ad . Below th e SM gimba l, t h e e ng ine noz z l e e x t e ndsi n t o t h e a d a p t e r ar e a . The SM i s a t ta c h ed t o t h e CM b y t h r e e t e n s io n t i e s .Exp losive c ha rge s s e pa r a t e t h e se t e ns io n t i e s f o r SM/CM se pa ra t i o n .

Lunar Module AdapterThe Lunar Module Adapter jo in s th e SM t o t h e S-IVB/IU and, i n some fu t u r e

m i s s i o n s , w i l l enclose the Lunar Module .Spa c e c ra f t subsys t e ms inc lude t he fo l l owing :a. Launch escape subsystemb. Emergency de te ct io n subsystemc . E l e c t r i c a l power subsyst emd. Ma s t er e ve n t , s e que nc e c o n t ro l l e re . Envi ronmental co nt ro l subsys temf . Communication subsystemg. Ins t rum enta t ion subsys temh. S t a b i l i z a t i on and c on t ro l subsyst e mi. Serv ice prop uls i on subsystemj . Reac t ion cont ro l subsys temk. Earth landing subsys tem1. Mission Control Programmerm . Impact and recovery subsystemn. S t r uc t u re subsyst emo. He at sh i e ld6 8


69/72

A~ B ~ I I M SF C )Pitch ControlM o t o r \Tower JotfisonM o t o r

Note :This i s the heiwiest 5p.c~ c*aFI- lanned f r r +he uprated Saturn 5proqramRecover y antennas ( 3)

(o n parachute deck - dep loyed a f te rm a i n parachute deployment )

L a u n c h Escapetower (LET)

Comrnaqd -LET/CM Sep. P l a n eModule (CM) antennaantennas ( 4 ) - m o u n t e df lushEM/ SY SIP.Plane - A $ )

,

SM reset ioncontroln q i n a o d ul esystem (RCS )4 )-e-,ie.\ g4rd:y3I I I

Launch0Escape

Posi t ion of panelsa f t e r 5 M / Adapte rSeparation - panels

,/ t r a i n s are locateda r o u n d t h eData: p e r i p h e r y o f each

:panel. These a r e

* O f . 8 4+ . used t o s e p a r a i e th eS M f r o m the adapter:A t L.O. -56,9001bs.LET - B,500 l bs ..CM - 1f.800 IbS.* S M - 23 , 000 Iba . cameraAdapter -- 5,700 Ibs.

Spacecraft 011ConFiqoration

69


70/72


71/72


72/72

To Reaction Control SystemFuel Dump f s q u e n c e r s

To EOS,ELS, Loqic To f\iqht,#Miss i on sequancora, Pert lbndtnqGimbal ~ o n h o lt busu p r ~ q h h n qsy +em (comm nicdiont t QqulpY t

Command Module I I , , , , , , , , , , * , , , , , , ,I

Documents

AS-202 Technical Summary