as-202 press kit

8/4/2019 As-202 Press Kit

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' -NA'I ' ,NAL AER / ' iAJIICS A Y D SPACE ADMINISTRATION Am 2-41 5lELSJg 2-69'_AS+1INCTON D 29546

FOR RELEASE: SUNDAYAugust 21, 1966ELEASE NO: 66-213 .PROJECT: Apollo/Saturn 202

(To be launched noe a r l i e r than Aug. 25)

C O N T EN T S

U0 UCCESSION N U M B E R )0D- (PAGES)

I THRU)

(CODE)

(CATEGORY)312

(NASA CR OR TMX OR AD NUMBER)

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RELXASE NO: 66-213APOLLO SATURN

HEAT SHIELDIN ORBIT TEST

The t h i r d unmanned Apolloflprated Saturn I f l i g h t w i l lbe launched no ea r l i e r than Aug. 25. Thfs w i l l be the secondf l i g h t t e s t of t h e Apollo spacecraft command and servicemodules and the t h i r d f l i g h t t e s t of the Saturn I rocke t i n p re -pa ra ti on f o r manned rnissicns or bi ti ng the Earth.

The 17,825-mile flight w i l l c a r ry the spacecra f t three-q u a r t e r s of t h e way around the Earth.t h e n o r th c e n t r a l P a c i f i c about 300 miles southeast of WakeI s l a n d .

Landing w i l l be i n

The National Aeronautics and Space Administration w i l llaunch t h e space vehicle from Launch Complex 34, KennedySpace Center, Fla. , a t l2:3O a.m. EDT to provide a longper iod of dayl ight for spacecraf t recovery opera t ions .f l i g h t w i l l take almost 93 minutes.

The

The mission i s t h e second performance check of theApollo command module ablative heat sh ie ld . The shield w i l lbe subjecte d t o extended high hea t loads -- about 23,000BTU/per square foot -- r e su l t i n g from a reentry path resemblinga " ro l l e r c o a s t e r " r i d e on Earth.

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-2 -On the first unmanned Apollo mission last February,

the heat shield underwent high heating rates at a verysteep angle. The reentry trajectory in this mission will belonger and shallower to produce very high heat loads.

The two types of trajectories represent reentry heatingconditions encountered in manned Earth orbital missions.For lunar landing mission reentry, the spacecraft heat shieldwill be tested next year on Saturn V missions.

The Apollo/Uprated Saturn space vehicle stands 224 feethigh (launch vehicle is 141 feet and spacecraft 83 feet).Total weight on the launch pad will be 1,326,400 pounds(launch vehicle is 1,269,500 pounds and spacecraft 56,900pounds).

The Apollo command module, although unmanned, is a fullyoperational spacecraft except for crew couches and a fewdisplays for pilots. The guidance and navigation systemand fuel cell electrical power system will undergo theirfirst flight test.

The Apollo Emergency Detection System will be tested inthe automatic mode. It will automatically initiate firing ofthe spacecraft launch escape system and separation of thecommand module if two of the Saturn first stage engines fail,or if a guidance failure causes excessive pitch, yaw and rollduring first-stage powered flight.

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-3-On manned missions , the emergency detection system can

c

opera te au tomat ica l ly or i t w i l l s i g n a l th e crew to i n i t i a t ef i r i n g of the escape system.detect ion system i s located pr imari ly i n the Sa turn vehic leinstrument uni t .

Relay logic of the emergency

The f i r s t t e s t of S-Band communications w i l l be conductedon the mission, although i t w i l l n o t be the prime method ofai r- to -g roun d communications, The Apollo Un if ied S-Bandsystem w i l l be fully opera tion al f o r Saturn V manned missionsi n 1958.

The 21,500 pound thrust service propulsion system enginew i l l be f i r e d four t imes i n f l i g h t f o r a t o t a l of more than f i v eminutes. On Apollo lunar landing missions, t h i s engine w i l lp r o v i d e t h r u s t f o r t h e s p a c e c r a f t t o cor rec t ve loc i t i e s en rou tet o th e Moon, break into lunar o r b i t and r e t u r n t o Ear th .

A s t r u c t u r a l t e s t of th e common bulkhead se p a ra t in g th eSaturn second s tage pro pel lan t tanks w i l l be conducted af terthe s tag e se par ates from the spacecraf t . Similar t o t hecheck on the second Uprated Saturn I mission, I t i s designedt o determine the strength o f t h e sandwich-l ike s t ructurewhich in su la te s th e l i qu id oxygen a t minus-297 minutes degreesF. from supercold liquid hydrogen a t minus-423 degrees F.

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cGround tests and the previous flight test show that the

bulkhead will withstand pressure differentials of about 34pounds per square inch -- more than three times normaloperating conditions.stage reenters the atmosphere over the Atlantic.

Maxirmun pressure is expected as the

Pressure differential reached will depend on the amountof liquid oxygen remaining in the tank.whether this will cause the stage to break up as it didin the previous Saturn flight last month.

It is not known

S i x movie cameras and one television system will recordA t o t a l of 2,158 measurementsata (See Cameras, Page 23 ).

will be recorded during the mission, 863 from the Apollospacecraft and 1,295 from the Saturn.

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS)

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Y-5-

THE FIISSIONCountdown for the Apollo/Uprated Saturn (AS -202 ) v e h ic l ea t Launch Complex 34 w i l l begin about 25s hours be fo re l i f to f f .

During t h e early phases of the count f i n a l checks of th e space-c ra ft , ordinance arming and mechanical work on the launchv e h ic l e w i l l be accomplished.v e h i c l e w i l l begin six hours before scheduled l i f toff .Liquid hydrogen load ing t o the second stage w i l l begin fourhours before launch.

Liquid oxygen loading t o both stages of th e Saturn launch

Hatches of the sp a c e c ra f t w i l l be sealed 45 minutes beforel i f t o f f , a n d 15 minutes l a t e r the Apollo access s w i n g armon the umbi l ica l tower w i l l be re t rac ted .Terminal phase of the countdown w i l l begin 30 minutesbefore launch. A t 2 minutes 43 seconds be fore l i f t o f f thecountdown w i l l go on automatic sequence.The vehicle w i l l be held on th e pad f o r abou t th reeseconds a f te r the e i g h t f i rs t -s tage e n g in e s i g n i t e t o a s su res t a b l e combustion. It w i l l l i f t of f the pad on an azimuthof 100 degrees East of North, r o l l to 105 degrees and begint o p i t c h o r tilt along the f l i g h t path, a so u th e a s t e r l ydirection from Cape Kennedy.The f i r s t stage burns f o r 2 minutes 23.7 seconds and thes t a g e i s separated. The booster propels the vehi cle t o a35-mile a l t i t u d e and 35 miles down range.about 270 miles downrange near Antigua.

o f th e f i r s t s t a g e w i l l record separa t ion and i g n i t i o n ofthe second stage (See Cameras, P a g e 23).th e spacecraft launch escape system i s j e t t i so n e d , Theengine burns f o r about 7 minutes 23 seconds producing thrustt o c a r ry t h e v e h ic l e t o a 135-mile al t i tude some 969 milesfrom the launch si te .

The stage impactsTwo recoverable movie cameras mounted on the forward end

A f e w seconds a f t e r the second stage J-2 engine ignites,

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-6 -About 10 seconds a f t e r secondc r a f t s e p a r a t e s from the stage andA television camera mounted i n the

s t age cu to f f t h e space-Saturn instrument unit .ins t rument uni t w i l lrecord movement of the spacecraft lunar module adapter panelsas they fold back t o fr ee the sp ace cra ft , The adapter w i l lhouse t he lu na r module on l a t e r E a r t h o r b i t a l f l i g h t s andlunar landing missions. Sign als from the camera w i l l bemonitored and recorded a t the Ant igua t racking s ta t ion (SeeCameras, Page 23 ).

The pres su re t e s t o f the second stage common bulkheadw i l l begin 90 seconds af ter spacecraf t separat ion.liquid oxygen tank vent valve w i l l be opened and t he l i qu idhydrogen tank vent valve w i l l be closed.th e pressure d i f f e r en t i a l ac ross the bulkhead t o increase ,The amount of increase w i l l depend on the amount of liquidoxygen remaining i n th e tank. M a x i m u m pressure i s expectedt o be reached as the sta ge ree nte rs th e atmosphere over theAtlantic Ocean.

TheThis w i l l cause

A f e w seconds a f t e r spacecraf t separat ion the 21,500-pound thrust service module propulsion engine w i l l be f i redf o r th e T i r s t time. This burn of th re e minutes 35 secondsw i l l boost th e spacec ra f t t o i t s peak a l t i t u d e of 706 m i l e sover South Afric a about 41 minutes a f t e r l i f t o f f .

The second se rv ic e pro pul sion engine burn, of one minute28 seconds, w i l l occur approximately 25 minutes l a t e r over theIndian Ocean near the Western t i p o f Austra l ia .About 10 seconds la te r , the t h i r d and fo ur th burns, eacho f th re e seconds dura tion, tak e place. These a r e t o t e s t t her a p i d r e s t a r t c a p a b i l i t i e s of th e engine.The s pa ce cr af t guidance and c on tr ol system w i l l o r i e n tt he spacec ra f t f o r se para ti on of the cormnand and s e rv icemodules about two minutes af t e r th e f ou rth ser vic e pr op uls ion ,burn. The 100-pound th ru st se rv ic e module re ac ti on co nt ro lengines a re f i r e d t o separate it from the corumand module.A f e w seconds af ter separa t ion the command module w i l l beor ien ted for the long shallow reentry . From an a l t i t u d e of

400,000 f e e t i t w i l l descend t o 218,000 f e e t a t a speed ofmore than 19,000 m i l e s per hour. A t t h i s time th e guidanceand navigation system w i l l i n i t i a t e t h e re a ct io n c o nt ro lsystem t o modulate the l i f t vector and the spacecraf t w i l ls k i p back t o an a l t i t u d e of about 264,400 f e e t ,-more-


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-7-From t h i s a l t i t u de "he f in a l phase o f r e e n t r y b e g a s a t* a ve lo c i ty about 16,000 m i l e s per hour,The apex cover of th e space cra ft w i l l be j e t t i soned t odeploy the two 13-foot diameter drogue parachutes a t 23,850f e e t a l t i t u de .

are deployed a t 10,350 feet. Splashdown i s expected onehour, 32 minutes, 54 seconds a f t e r l i f t o f f .The th re e 83-foot diameter main parachutes

The predicted landing point f o r the mission i s a t 17degrees 9 minutes N l a t i t u d e and 171 degrees 87 minutes Elongi tude, locat ed i n the downrange po rt i on of t h e terminallanding foo tpr int . The terminal landing "fo otp r in t" i s ana rea 3,500 n au ti c a l miles long, varying between 200 and 300n a u t i c a l m i l e s i n w i d t h cutting between th e Caroline andMarshall I s l ands w i t h impact point 300 miles southeas t of WakeI s l a n d i n th e North Cent ra l Pac i f i c ,The a i r c r a f t c a r r i e r , USS Hornet, two des t roye rs andseven C-130 aircraf t comprise the Department o f Defenserecovery fo rce i n the a rea. The USS Hornet w i l l be a t thepredicted impact area,Should the spacecraft 's guiaance system f a i l , a b a l l i s t i cr e e n t r y w i l l be achieved and landing w i l l be i n the uprangep o r t i o n o f t he long foo tp r in t , This impact point i sapproximately 1,000 m iles uprange i n th e vi ci ni ty of theCarol ine I s lan ds , nor th o f New Guinea.Af ter recovery the Command Module w i l l be taken toDowney, California, f o r p o s t - f l i g h t analys is by NASA andNor th American Aviation engineers.

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24.324.526.1349.555052.5501 35

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. -8e TLIGHT SEQUENCEHour Minutes Seconds Event

Lif t -offPitch and roll maneuver initiatedR o l l terminatedMaximum dynamic pressure (alti tude7.8 miles, 2.5 m i l e s downrange,veloci ty 1,010 m i l e s per hour).Pitch terminatedF i r s t stage inboard engines cutoffF i r s t stage outboard engines cutoff( a l t i t u d e 35 m i l e s ; 35 m i l e s down-range, ve loc i ty 4,150 mph)Second stage u l l a g e ro c k e t i g n i t i o nF i r s t stage separa tesSecond stage ignit ionCamera capsule ejected fromseparated S-IBLaunch escape system jettisonIn i t i a t e a c t i v e g uidanceSecond sta ge engine cutof f (a l t i tu d e135 m i l e s , 969 m i l e s downrange,veloci ty 14,300 mph)Separat ion of spacecraft fromSaturn second s tageFirst burn Service Propulsion SystemEngine (SPS), 215 secondsSecond stage bulkhead t e s t beginsF i r s t burn concludedApogee reached, 706 s t a t u t e m i l e s

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-9-Hour Minutes Seconds Event111111111

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380836454959025816175638363658005254

RCS ullage burnSecond burn SPS, 88 secondsSecond SPS burn concludedThird SPS burn, 3 secondsThird SPS burn concludedFourth burn SPS, 3 secondsFourth SPS burn concludedCM/SM separation attitudeCM/SM separation sequence starts(150 seconds RCS burn SM)CM/SM separationCM reentry attitudeCM at 400,000 foot altitudeBlackout beginsBlackout endsApex cover jettisonedDrogue chute deployedMain chute deployed at 10,350 feetSplashdown

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-10-M I S S I O N CONTROL AND TRACKING

The Manned Space Flight Control Center a t the MannedSp ac ec ra ft Center, Houston, w i l l co nt ro l t he mission froml i f t o f f through recovery of th e sp ac ec ra ft , The secondf l o o r Mission O peratio ns Control Room w i l l be used as i twas f o r th e Apollo/Uprated Saturn I missions l a s t Februaryand Ju ly ,

Real-time in -f li g h t an al ys is and monitoring of th e onboardsystems by f l i g h t cont ro l l e r s w i l l be accomplished through datat r ansmi t t ed from A i r Force Eastern Tes t Range and the NASAManned F li gh t Tracking Network tra ck ing f a c i l i t i e s .S t a t i ons pa r t i c ipa t i ng w i l l be Kennedy Space Center,P a t r i c k AFB, and Merritt Island i n Florida; Bermuda; Grand

Bahama Island; Grand Turk I s l a n d ; Antigua; Ascension Island;Pr et or ia , South Af ric a, and Carnarvon i n Aust ra l i a .I n t h e At la nt ic Ocean, the tra ck ing s h i p Rose mot Victor

w i l l monitor spacecraft separat ion I n addi t ion to rece iv ingother t e lemet ry data. Two t r a c k i n g s h i p s i n th e westernP a c i f i c w i l l be the Coastal Sentry Quebec, which w i l l monitorsepa ra t i on o f th e command and s er v ic e modules be fore reen t ry ,and the Wheeling.

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PRELAUNCH CHECKOUTThe upra ted Sa turn I launch veh ic l e -- f i r s t s t age (S-IB),second stage (S-IVB), and instrument unit ( I U ) -- a r r i v e d a t Cape

Kennedy i n January and February. They were erected ins ide t h eCanplex 34 s e r v i ce s t r u c t u r e in March.The Apollo spacecraft,command module, s e r v i c e module andlu na r module adapter, ar ri ve d at t h e NASA Kennedy Space Centeri n A p r i l . The coamand module underwent extensive environmentalcon t ro l system checks and was taken t o the pyrotechnic installa-t i o n b u i ld i ng where it was mated w i t h th e launch escape system.A f t e r receiving and inspection, t h e service module was takent o Complex 16 on Cape Kennedy f o r checks of i t s secondary propul-s i o n system. Then it was re turned to t h e Kennedy Space Center f o r

f u e l c e l l i n s t a l l a t i o n and tests i n an a l t i t u d e chamber which sim-u l a t e s t h e near-vacuum of space.The l una r module adapter and t h e se rv ic e module were matednear th e end of June. Mate of t h e Apollo modules with the launchveh ic l e was accomplished i n ea r ly Ju ly .Tests of th e integrated launch vehicle and spacecraft fol-lowed a t Complex 34.conducted by th e launch team about three weeks before the sched-uled launch date. During t h e demonstration, a c t u a l countdownwas fol lowed t o ig n i t ion and l i f t o f f . This included loading th e

launch vehicle with cryogenic propellants -- l i q u i d oxygen andl i q u i d hydrogen.A fu ll -s c al e countdown demonstration was

A s i n p re vi ou s Uprated Saturzl I flights, much of th e check-out of both launch vehicle and spacecraft was accamplished throught h e us e of computers. Launch ve hi cle auto mat ic checkout -- al-ready used t o a great extent i n Apollo spacecraft tests -- w i l lbe progress ive with each succeeding f l ight .The Saturn V launch vehicle, f o r th e most part, w i l l s i g -n i f y th e u l t ima te in automatic checkout whenmost of i t s prepara-t i o n i s accomplished through th e use of mmputers, Two RCA 1 1 0 - A

computers, one located a t th e base of the laun ch pad and one i nthe launch control center are u s e d for checkout of the Saturn.Spacecraft computer checkout uses a system called ACE/SC(acceptan ce checkout equipment f o r spa ce cra ft) , The ACE systemprovides re l iable , instantaneous, accurate checkout of the sys-t e m s w i t h computers, display consoles and recording equipment,

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ACE, a l so used a t spacecraf t c ontra c tor p la nts and a t N A S A ' sManned Spacecraft Center, Houston, i s manufactured by GeneralE le c t r i c , Apollo Support Department, Daytona Beach, Fla.

While automatic checkout of t h e various systems of t h e space-c r a f t a n d the launch vehic le are be ing carried out independentlya t t h e Kennedy Space Center and on t h e launch complex a t CapeKennedy interface instrumentation joins t h e tw o systems f o r a pic -t u r e of the ov era l l pre launch preparat ion .APOLLO SPACECRAFT

The spacecra f t cons i s t s o f two modules which are fastenedto g et h er i n tandem, t h e Apollo command and se rv ic e fnodules, Thelaunch escape Sys tern i s atop the command module. A n adapter sec-t i o n is l o c a t e d between t h e se rv ic e module and t he launch veh ic lewhich w i l l house t h e l u n a r module on future Apollo flights.

Command ModuleAlthough this i s an unmanned mission, the instruments andequipment i n th e tbmmand m o d u l e w i l l be f u l l y o p er at io n al , withthe exception of a f e w as t ronau t -o r ien ted d i sp lays ,of a pressurized compartment of aluminum honeycomb and an o u te rh e a t s h i e l d of s ta in le s s s t e e l honeycomb.

I t cons i s t s

Shape : Conical (cone)H e i g h t : 11.5 f e e tD i a m e t e r a t base: 13 f e e t

Launch w e i g h t : 11,900 ( inc luding RCS prope l lan t s )Outer dtructure :

Inner compartment :

Insu la t ion :

Stainless s t e e l braze d honeycombbonded between aluminum alloy sheets.An a b l a t i v e material which variesfrom 1/2 i nc h t o 2-1/2 inches i sappl ied t o e n t i r e o u t er s u r fa c e,Aluminum honeycomb bonded betweenaluminum alloy sheets. Thicknessranges from 1-1/2 inches a t baset o 3/4 inch a t forward bulkhead.A two-layer micro-quartz f i b e r i n -su l a t i o n 1/2 inch- th ick separatesthe walls of the inner and outers t ruc tu res .

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-13-.E l e c t r i c a l : Six s i lv e r oxide -z i nc batterieswith a capaci ty of 40 ampere hoursprovide entr y, po st landing andpyrotechnics energy.

Service ModuleThe se rv ic e module I s an unpressur ized cyI indr ica1 s h e l lwhich houses t h e main propulsion engine, pr op el la nt tanks, e l ec -t r i c a l power system, rea ct i on con trol engines and p o r t i o n of theenvironmental control system i n a s i x pie-shaped sec t ion . Threef u e l ce l l s , e ach with the capabil i ty of producing 1,420 watts,w i l l f l y on t h i s mission.Shape : CylinderH e i g h t : 24.6 f ee t ( i nc lud ing main propul-sion engineDiameter : 13 f e e t

9,800 pounds23 000 oundsLaunch weight: &St ruc tu re :

Elect r ical power:

Aluminum honeycomb panels one incht h ic k b o l te d t o six s o l i d aluminumf i e l d beams t h a t are chemicallymil led t o wi th in .007 inches (seventhousandths) .The el e c t r i c a l energy source fo rthe s pa ce cra ft throughout the m i s -s io n u n t i l t h e command module sep-ar at es from th e s er vi ce module i sprovided by t h e three f u e l c e l l s .

Spacecraft Lunar Module AdapterT h i s adapter jo in s th e se rv ic e module and t h e S-IVB i n s t r u -

The adapter i s 28 f e e t h i g h and tapers from 22 f e e t a tment unit. In f u t u r e fl ights i t w i l l house the l u n a r module,b u t on t h i s f l i g h t an aluminum a l loy brac ing i s included i n i t splace.t h e ins trument un i t end t o 13 feet where it a t t a c h e s t o t h e s e r -vice module. I t weighs 3,700 pounds. I t con sis ts of four alum-inum honeycomb panels a t tached by hinges t o the lower end of theadapter. The pane ls may be sep arate d by e xplo sive charges andopened pe ta l - l ike t o expose th e lunar module preparatory t o CSMl u n a r module docking on future f l ights .

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MAJOR APOLLO SPACECRAFT SYSTENSBoost-Protect v e Cover (BPC)The boost -protect ive cover pr ot ec ts th e command module fromaerodynamic heating during boosted f l i g h t and from heat and sootfrom th e launch escape and j e t t i s o n motors of t h e launch escapesystem. I t i s made of ab la ti v e co rk and Teflon-impregnated glassc lo th supp orted by g l a s s honeycomb i n t h e upper portion. It isj e t t i s o n e d w i t h the launchescape system a t 268,000 f e e t a l t i t u d el e s s than three minu tes a f t e r l i f t o f f .

Launch Escape System (LES)The launch escape system i s 33 f e e t t a l l a n d c o n s i s t s of a nescape motor, p i t c h co ntr ol motor, tower j e t t i s o n motor, towerrelease mechanism, cana rd subsystem and Q - b a l l assembly. I tweighs about 8,500 pounds.

3 inches long and burns about 4,700 pounds of s o l i d pr op el la ntt o p rovide 155,000 pounds of thrust.The launch escape motor i s 26 inches i n diameter, 15 f ee t ,

The pi t ch con t ro l motor i s nine inches i n diameter, 22 i n -ches long, and burns s o l id prop ellan t .The tower je t t i s o n motor i s 26 inches i n diameter , 47 incheslong, uses s o l i d pro pel lan t and develops about 33,900 pounds oft h r u s t . I t removes t h e LES af te r the second stage i g n i t i o n .The tower release mechanism co ns is ts of fo ur explosive b o l tswhich separate j u s t b ef or e the j e t t s i o n motor o r escape motor i g -n i t e s t o d etach t h e LES from t he command module.The canard subsystem i s mounted i n t h e pi tc h cont ro l motorhousing near t h e top of the launch escape system. Each of twowing-like canard su rf ac es i s about 18 inches wide and 24 incheslong. The aerodynamic surfaces are deployed by explosives 11

seconds a f t e r t h e escape motor f i r e s during an ab ort . They s ta -b i l i z e th e command module b lun t end forward pr i o r t o drogue chutedeployment.The Q - b a l l assembly i s a t the top of the launch escape sys-t e m and con tains pressu re sensors t o determine f l i g h t angles ofa t t a c k and dynamic pre ssu res during launch or launch ab or t.

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Command Module Guidance and Navization SystemThe system c o n s i s t s of i n e r t i a l , computer and op ti ca l sub-systems. During t h i s unmanned mission t h e optical subsystems,telescope and sextant, w i l l be i n a c t i v e .A c o n tr o l programmer w i l l perform t a s k s normally done byt h e a s t ro n a u t s .The computer w i l l be ac t iva ted t o de te rmine spacecra f tv e lo c i t y and a t t i t u d e and reentry angle.

Command Module A t t i t u d e Control and Stabil izat ion SystemThe system, composed of 1 2 s m a l l rocke t eng ines ins ta l l edi n independent , id en t i ca l s e t s o f six, provides onboard propul-s i o n f o r po s i ti o n in g r e e n t r y i n t o t h e Eartn's atmosphere. Fastac t ing va lves enable t h e engines t o b e f i r e d i n s h o r t b ur s ts t o30 p e r second t o po s i t i on t h e spacecra f t p rec i se ly dur ing reen t ry .Thi r ty b u r s t s (p u l s e s ) pe r second i s about t h e r a t e a spark plugf i r e s i n a n automobi le engine opera t ing a t 3,000 r e v o lu t i o n s perminute, o r about 70 mph.Thrust : 93 l b s . p e r engineLength : 11 inchesDiameter: 5 inchesWeight : 8.3 l b s .P ro p e l l a n t s :

Components :

Monomethylhydrazine ( f u e l ) andn i t ro g e n t e t ro x id e (o x id i z e r ) .Combination i s s to r a b l e a nd hyper-g o l i c - 270 l b s . on t h i s mission.Ablative t h r u s t chambers, f a s tact i ng valves , and detachable nozzleextension.

Pulse frequency : 30 cyc les per second

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E a r t h Landing System (ELS)Besides t h e sequence controller , t h e E a r t h landingsystem cons i s t s of two ny lm co ni ca l r ibbon drogue parach utes13 f e e t i n di amete r; t h r ee r ings lo t nylon p i l o t chu tes, sevenf e e t i n diameter; and t h r e e ri ng sl ot , nylon main chutes83.5 f e e t i n diameter.A t 24,000 f e e t a l t i t u d e , a f t e r reent ry , a barometr icswi tch ac t iv a t es pyro technics which j e t t i s o n t h e apex heats h i e l d t o uncover th e parachutes.Two seconds l a t e r t h e drogue chutes are deployed by mor-t a r t o s t a b i l i ze t h e spa cec raft blun t end forward. The droguesare reefed f o r e i g h t seconds, the n f u l l y opened by reef ingc u t t e r s .The p i l o t c h u t e s are deployed about 10,350 f ee t , p u l l i n gt h e three main parachutes from t h e i r conta iners . The mainc h u te s a l s o are reefed f o r e i g h t s econds u n t i l c u t t e r s permitt h e large canopies t o open ful ly .The VHF recovery and su rv iv al antennas and a f l a s h i n gl i g h t are deployed a f t e r the main chutes dis reef , t h e sur -v iv a l and recovery beacons begin ope rat ion befor e touchdown.I f t h e space craf t l ands w i t h i t s apex end i n t h e water,t h e con t ro l programmer w i l l s i g n a l a pump one minute a f t e rsplashdown t o i n f l a t e one of three f l o t a t i o n bags. r'iveminutes l a t e r , i f t h e spacecraf t i s s t i l l not upr ight asecond pump i n f l a t e s a n ot he r bag, and if necessary f iv e minutesl a t e r t h e t h i r d bag w i l l i n f l a t e .When upr ig h t, ot he r aids , such as t h e H F t r a n s m i t t e rand f lash ing l i g h t begin operation.

Power Supply SystemPower f o r t h e spacecraf t w i l l be furn ished by two of threef u e l c e l l s c a r ri ed i n t h e se rv ice module. Maximum grosspower of these two un i t s i s 2,840 watts ( 2 9 v o l t s ) , The

c e l l s weigh 240 pounds each and use oxygen and hydrogen asr eac tan t s .and 60 pounds of l i q u i d hydrogen ( i n two tanks9 w i l l be ca r r i edThe t h i r d fuel c e l l w i l l not fh nct ion during t h i s mission.A t o t a l of 672 pounds of liquid ox gen ( i n two tank

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.

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Service Module Main Propulsion System (3PS)s p a c e c r a f t v e l o c i t y a f t e r launch vehic le separa t ion .This system p ro vi de s t h r u s t r e qu i re d f o r l a r g e c h w e s i n

I n o r b i t a l m iss io ns t h e SPS w i l l be used f o r o r b i t a lchanges and r e t r o f i r e , and on a lunar journey w i l l providemidcourse corrections and veloc i ty changes f o r en ter ingand leaving lunar orbit.Two e l e c t r ic a l ly operated servo-ac tuators provide theSPS engine with the capab i l i ty o f gimballing ac t ion . SPSprope l l an t s ( fue l and ox id ize r ) a r e kept t o the bottom of th etanks fo r proper f low in to engine pumps by maneuvers per-formed by th e S M react ion control system.During t h i s f l i g h t t h e r e s t a r t ab le eng ine w i l l be f i r e d

four sepa ra te times f o r a t o t a l of 5 minutes and 25 seconds.D E S C R I P T I O N :

Engine Th ru s t

Propel lan ts

21,500 poundsEngine i s capable of operat-ing f o r 12 and a half minutesin va r ious time incrementsinvolving up t o 50 separateperiods of operat ion.7,500 l b s . o f UCsvIH ( fue l )15,180 l b s . of ni t rogente t rox ide (ox id ize r )

Height 12 f e e t 7 inchesWeight 770 l b s .

Service Module Reaction Control SystemSixteen small rocket engines are used t o car ry out u l -lag e requirements, perform st a b i l i z a t i o n maneuvers dur ingf l i g h t and t o s ep ar at e se rv ic e and command modules p r i o r t o

ree ntry . They a r e arranged i n c l u s t e r s of four .F UNCT ION:

D ES C R I P TI O N :Number

Posi t ioning of SM, ullagerequirements for SPS pro-p e l l a n t s , s e p a r a t i o n SMCM

16 c lus t e red i n four quadrants-more -


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.-18-

Propellants

SizeWeightThrust

Nitrogen tetroxide and hydrazine50-50mission

8 b s . carried on this14 inches long, largest diametersix inches5 pounds100 l b s . (each engine)

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Canar ds (deployed1

LES - CM separation

CM - SM separatio

(without boost protect ive-more -

APOLLO SPACECRAFT

In

cover)


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-19-

THE UPRATED SATURN I LAUNCH VEHICLEThe Uprated Saturn I launch vehicle was conceived i n1962 a t t h e NASA Marshall Space Flight Center as t h e quickes t ,most rel iable , and most economical means of prov id ing a ve-h i c l e w i t h greater payload ca pa bi l i ty than t h e S a t u r n I f o rs u b o r b i t a l and o r b i t a l Apollo missions before t h e Saturn Vwould be a v a i l a b l e.The design was based on u s i n g two exis t ing stages ofSaturn I and Saturn V vehic les , redesigned Saturn I boos te r( t h e S-IB stage) and t h e t h i r d stage (S-IVB) and instrument

u n i t from the Saturn V.The concept pe rmi t t ed r a p i d development of t h e vehic le ,and maximum u s e of d es ig ns and f a c i l i t i e s from o the r Sa tu rnprograms saved t i m e and money.Two Uprated Saturns launched ea r l i e r t h i s year onFeb. 26 and July 5 cont inued the s t r ing of 10 Saturn I successes.The Uprated Saturn I , including two stages and an ins tru-ment unit, i s 141 f e e t t a l l .spacec ra f t t h e en t i r e space veh ic le s t ands 224 f e e t h ighon t h e launch pad.

i n diameter.

Mated w i t h th e 83-foot Apollo

F i r s t stage -- The 202 stage is 80 f ee t long, 213 f e e tD r y w e i g h t Is 91,600 pounds.Design changes have been made i n th e Saturn I boos te rt o r ed uc e w e i g h t . However, th e f i r s t stage f o r t h i s f l i g h twas one of two booste rs i n the ser i es i n i t i a l l y designateda par t of t h e Saturn I program and some of t h e w e i g h t reduc-ing changes were not incorporated.The second f l i g h t Uprated Satu rn I stage, flown i n Ju ly ,was t h e f i r s t of t h e boos te r s inco rpo ra t ing v i r tua l ly a l l of

t h e weight redu cti on changes. Dry weight of t ha t stage,86,200 pounds, w a s reduced by about 20,000 pounds over t h ebas ic S-I. This w a s done by redesigning t h e f ins, removinghydrogen vent p i p e s and br ackets unnecessary t o t h e new de-s ign, re s i z i ng machine par ts I n t h e t a i l s e c t i o n assembly,redesigning t h e s p i d e r beam and modifying t h e prope l l an ttanks.-more-


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. -20-Ei g h t H-1 engines producing a t o t a l thrust of 1.6 mill ionpounds power t h e stage. The engines, made by Rocketdye,burn l i q u i d oxygen and RP-1 fue l ,minutes of operation, t h e stage bums 40,000 gallons(270,500 pounds) of R P-1 f u e l and 64,OOO gallons (611,000pounds) of l i q u i d oxygen, t o reach an al t i tu de of about 35miles a t engine cutoff,

I n approxlmately 22

Four of t h e Rocketdyne H-1 engines are mounted i n asquare pattern i n t h e center of the stage's thmst s t ruc tu resect ion, The other four are mounted i n a square pa t te rnnear t h e outer edge of th e thrus t s t ruc ture , The outerengines are equipped w i t h independent, closed-loop hydraulicsystems which gimbal t h e engines as much as eight degreesf o r ve h ic le f l i g h t direc t ion control ,The stage i s made up of eight 70-inch diameter propel-

The center tank and four of t h e outerl a n t tanks (Redstone type) surrounding a single 1E-inch( J up i t e r type) tank,ones hold l i q u i d oxygen, and t h e other four contain RP-1(kerosene). The tanks are interconnected a t th e bottcm t oprovide t h e c a p a b i l i t y of completing th e mission In caseone engine f a i l s , This capabi l i ty was demonstrated i n twoSaturn I f l ights ,C h r g s l e r assembles t h e stages a t the NASA-Michoud

Assembly F a c i l i t y i n New Orleans and t e s t s them a t the NASAMarshall Space F l i g h t Center, Huntsville, Ala.Second stage -- The stage i s 58 feet long and 21.7 feeti n diameter, I t s Rocketdyne 5-2 engine, powered by l i q u i dhydrogen and oxygen, generates 200,000 pounds thrust, Afterf i r s t stage burnout it l o f t s t h e spacecraft t o about 135

m i l e s a l t i t u d e ,Dry w e i g h t of the stage, including t h e interstage uhlchconnects th e f i r s t and second stages, i s 29,700 pounds, Thestage op er at es about 7.5 minutes t o achieve or bi ta l speed

and a l t i tude , but w i l l not o r b i t on t h i s f l i g h t , The 5-2engine w i l l burn approximately 60,000 gallons (36,000 pounds)of l iqu id hydrogen and some 20,000 gallons ( l g 0 , O O O pounds)of liquid oxygen,Douglas Aircraf t Co, builds t h e second stage a t I tsHuntington Beach, C a l, ,f ac il it y and t e s t s it a t t h e Sacra-mento T e s t Center.


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APOLLO/SATURN IB SPACE VEHICLE- -

LAUNCH ESCAPE MOTORLAUNCH ESCAPE TOWERCOMMAND MODULE ------ - 12' SPACECRAFTiSERVICE MODULE ----ADAPTER - --- --- -INSTRUMENT UNIT

GUIDANCE SYSTEMTELEMETRY EQUJPHENTPOWER SUPPLY BATTERIES

r - -ND INVERTERSS- IPB SECOND STAGE

11-2 ENGINE200,000 LBS.TOTAL

, ,/'A' !;--. _ .* - _1 I n-.

_ _ _ ___ITHRUST LLOX/LH2 1S-IB FIRST STAGE- - - - - +

8/H-1 ENGINESl,600,000LBS. TOTALTHRUSTLOXhP-1

imLAUNCH WEIGHT 1,312,300 IJ~S.

-----+ 83'13' 1

1 IS-IE[BSTACE 1i8iLAUNCHVEHICLE141'

I

1i

II1

IS-IB AGE80'

I

- - - i -.ASPACE VEHICLE

Iiji

I

I

II!Ii224'11ii!!

,IiI

IIi~

I!i

I

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. -21-Instrument Unit -- The 260-inch diameter instrumentu n i t i s three feet high and weighs 4,500 pounds.unpr essur ized , load-supporting s tr u ct u re of sandwich-typebonded cons tr uc ti on . Honeycomb-panel "cold plates" areattached t o welded brackets on th e i n t e r i o r s k i n . Thee lec t r i ca l and electronic equipment i s mounted on the platesf o r coo l ing purposes.

It i s an

The instrument unit has the e l e c t r i c a l and mechanica lequipment which guides, co ntr ols and monitors ve hic le per-formance from l i f t o f f u n t i l a f t e r i n s e r t i o n of th e payload.It c o n t r o l s f i r s t stage powered f l i g h t , stage separa t ion ,second stage powered f l i g h t , and fur ther f l i g h t t o t h e p o in tof payload separa t ion .O n t h i s mission t h e ins t rument uni t w i l l c o n t ro l t h evehicle through second stage powered f l i g h t . Some ten secondsla ter th e spacecraft i s separated.Equipment i nclu des guidance and con tro l , e l e c tr ic a l ,measurement and telemetry, radio frequency, instrumen tat ion,range safe ty command system, environmental control, andemergency detection systems (EDS).Systems include t h e ST-124-M-I11 i n e r t i a l p la tf or m,the launch vehic le d i g i t a l computer and th e e l e c t r i c a l equip-ment r equ ire d f o r launch vehic le performance.The ins t rument uni t w a s designed by t h e Marshall Center.In te rn at io na l Business Machines Corp., Federa l Systems D i -v i s io n , i s t h e I U c o n t r a c to r f o r fabr ica t ion , system t es t -ing, and in te gr at io n and checkout w i t h the launch vehic le ,w i t h major elements coming from Bendix, IFM, Elec t ron icCommunications, Inc .

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-22-

LAUNCH COMPLEX 34The AS-201 space ve h ic l e w i l l be launched from Complex 34,Cape Kennedy, th e pad used for t h e f i r s t four Sa tu rn I

launches and t h e f i r s t Apollo/Uprated Saturn I l a s t Jan. 26,The complex c o n s i s t s o f a 430-foot diameter launch pad,a mobile se rv i ce s t ru c tu re ? a launch control center andrelated ground support equipment, v eh ic le s er vi ce systemsinc luding RP-I (kerosene) fuel, liquid oxygen and l i q u i dhydrogen used f o r l aunch vehic le cool ing and p ressu r iza t i on .Prepara t ions are d ir e ct ed dur in g checkout, countdown andlaunch from a dome-shaped launch cont ro l cen ter l oca te d about1,000 f ee t from t h e pad. The cont ro l center (b lockhouse)is cons t ruc ted of s tee l and concrete w i t h a roof designed t o

withstand pressures of 2,188 pounds p er square inch -- w e l labove safety l i m i t s f o r t he 3OO-man crew i n s i d e , i n eventof an exp los ion i n t h e pad area.The mobile s t r u c t u r e i s wheeled i n t o place during launchpreparat ions and rolls back 680 f ee t from the pad about threehours before l i f t o f f , It s tands 310 f e e t h igh and weighs some3,500 tons, Seven f i x e d platforms and e i g h t enclosed, re-t r ac tab le working areas are i n t h e s e r v i c e s t r u c t u r e , Theseg i v e t h e service crew access t o a l l sec t ions of t h e launchvehic le and spac ecraf t,Hurricane doors, 44 f e e t t a l l , provide weather pro-t e c t i o n f o r t h e f i r s t stage, and re t rac table silo sec t ionsprovide s imi lar c o ve r f o r t h e S-NB, inst rument uni t andspacecraf t . Following t h e successfu l Sa turn I ser ies ,Complex 34 w a s modified f o r t h e Uprated Saturn I program.The work i nc lu de d i n s t a l l a t i o n of doors capable of prot ect ingt h e f i r s t stage from hur ric ane winds, s i l o s f o r t h e upperstages and spacecraft , a new anchoring system f o r the ser-v ic e s t ruc tu re? r einforcement of s t r u c t u r e s , frames and pro-p e l l a n t systems,Addi t iona l m odi f ica t ions were made t o t h e swing arms,

instrumentation, pneumatics and environmental control systemf o r the Saturn,Modif icat ions requ i red t o "man ra te" Complex 34f o r t h e Apollo program in clu de d i n s t a l l a t i o n of a spacec ra f taccess arm and a h i g h speed e l ev a t or i n t h e umbi l ica ltower f o r t h e f l i g h t crews.

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-23-CAMERAS

Motion PicturesSaturn Fi rs t S tage

Two 16 rm M i l l i k e n movie cameras mounted on t h e f o r -w a r d end of th e f i r s t s tage will record f i r s t and seconds tage separat ion, operat ion of t h e second s tage u l l a g erockets and 5-2 engine igni t ion .

The cameras w i l l begin operating approximately threeseconds before s tage separa t ion and w i l l be ejected 25 se-conds a f t e r separa t ion a t an a l t i t u d e of about 49 miles .The cameras are enc losed i n waterproof capsules. Thecapsules have a l u m i n u m s h e l l s and s t a i n l e s s s t e e l nose sec-ti o ns , qu ar tz windows, r e e n t r y equipment and reco ver y a id s.Dur ing descent, paraballoons i n f l a t e a t approximately14,000 f e e t t o keep th e capsules a f l o a t . Radio beacons anddye markers w i l l ass i s t an A i r Force recovery team t o locatethem.These camera systems were flown on the previous UpratedSat ur n mission s. One camera was r e t r i e ved on each f l ig h t .Chrysler Co r p . assembled and t e s t e d the camera packagesf o r t h e NASA Marshall Space F l i g h t Center.

SpacecraftFour 16 mm Milliken motion picture cameras w i l l be mountedi n th e Command Module t o reco rd in st ru men ts , chute deploymentand reentry. One camera will be mounted on the f l a t p l a t ei n t h e egress ha tch ( i n the nose of th e CM) t o r ecordj e t t i s o n i n g of t h e Apex cover, parachute deployment and reentry.The second camera is on a p a l l e t where t he right astronaut couchwould be located, and w i l l r e c o r d l i f t o f f and r e e n t r y throught h e right-hand window. Two Instrument cameras, one on the leftand one on the center, w i l l record instruments and d i sp laysduring the f l i g h t .Camera/Location Speed/Timing

1)Apex - egress hatch 32 FPS - reentry-30,000 f t . t osplashdownT p lus 72 t o splashdown2 ) Astro - r i g h t window 10 FPS - l i f t o f f to T p l u s 10

3) Instrument - l e f t p a l l e t 10 FPS - T-45 t o T Plus 10 andand c e n t e r o t h e r s i g n i f i c a n t p e ri o ds-more-


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-24Televis ion

A small t e l e v i s i o n camera mounted on a cross beam a topth e inst rument un i t will photograph the movement of th esnacecraft- lunar module adapter panels as t h e y f o l d back t ofree the spacecraf t ,

The panels w i l l enclose t h e Apollo l u n a r module on latermissions. They are hinged about seven fee t above the i n s t r u -ment u n i t and are t o f o l d back some 35 degrees,A n assembly of eight m i r r o r s w i l l al low the forwardpoin t ing camera t o record t h e movement of a l l four panels .Four l ights, one on each panel, wlll i l luminate the areaduring camera operation.The camera w i l l be turned on a t l i f t o f f a n d w i l l operate12-15 minutes, It may photograph clouds and th e Earth as

commercial scan rates, 525 l i n es and 30 frames a second, Thet r a n s m i t t e r i s located i n th e instrument u n i t ,thestage f a l l s back i n t o t h e atmosphere. It has standard

The Ant igua t racking s ta t ion w i l l monitor the trans-mission and record it.The General Electrodynamics Corp. b u i l d s t h e t e l e v i s i o nsystem under th e d i r e c t i o n of the NASA Marshall Space FlightCenter.

APOLU) PROGRAM MANAGEMENTThe Apollo/Saturn program i s d i r e c t e d by Dr. George E.Mueller, Associate Adminis t ra tor f o r Manned Space Fl igh t ,NASA Headquarters, Wash., DOC., Apollo Program Director i sMaj, Gen. Samuel C. P h i l l i p s , USAF, NASA's Off ice of MannedSpace F l i g h t , E, E, Christensen is Director of Mission Opera-tions,The Marshall Space Fl ig ht Center, Hun tsvil le , A l a . , isrespons ib le for development of the Saturn launch vehicles .

Dr. Wernher von Braun i s Director of t h e Center.The Manned Spac ec ra ft Center, Houston, i s respons ib lef o r development of t h e Apollo spacecraft , crew training andi n - f l i g h t m i s s i o n c o n t r o l from th e Manned Flight MissionCont rol Center lo ca te d a t MSC. Dr, Robert R. G i l r u t h i sCenter Director,The John F. Kennedy Space Center, Cape Kennedy, Fla. I sres po nsi ble f o r Apollo/Saturn launch operation s.R, Debus i s Center Director. Dr. Kurt

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. -25-The Goddard Space Flight Center, Greenbelt, Md., i sGesponsib le f o r management of the NASA Manned Space Fl ig h tTracking Network, D r , John F. Clark is Director .Mission Officials:Mission Director - Brig . Gen, C. H. B l e n d e r , USAF,Mission OperationsNASA Headquarters, Wash., D.C.Launch Director - Rocco A. Petrone, Dir ecto r of LaunchOperations, Kennedy Space Center, Fla.Fl igh t Di r ec to r - John D. Hodge, F l i g h t Operations,MSC, HoustonManager, ApolloSpacecraft Program - D r . Joseph F. SheaMSC, HoustonManager, UpratedSaturn I LaunchVehicle Program - Lee JamesMSFC, Huntsv i l l e

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J

-26 -c

MAJOR APOLLO/SATURN IB CONTRACTORSSATURN I B

F i r s t Stage

H - 1 Engines

Second Stage

5-2 Engine

Chrysler Corp.Space DivisionN e w OrleansRocketdyne DivisionNorth American Aviation, Inc.Canoga Park, C a l .Douglas A i r c r a f t Co., Inc.Miss i le & Space Systems D i v .Huntington Beach, C a l .Rocketdyne DivisionNorth American Av iat ion , Inc.Canoga Park.

Instrument Un it In te rn at io na l Business MachlnesCorp.Federal Systems Divis ionHuntsv i l le , A l a .

Eclipse Pioneer Div.ST-124M I n e r t i a l Bendix Corp.Pla tform i n theInstrume nt Uni t Teteboro, N.J.Apollo Spacecra f t

Command Module, Serv ice Space & Information Systems Div.Module and L E M Adapter North American Aviat ion , Inc.Downey, C a l .Subc ontr acto rs f o r Major Spac ecra ft Systems

Abla t ive Heat Shie ldMaterial Wilmington, Mass.Brazed Honeycomb Panels

Avco Research and Development Div.Aeronca Manufacturing Co.Middletown, Ohio

Command Module A t t i tude Rocketdyne Div. of North AmericanControl and St ab i l iz a t i on Aviat ionEngines Canoga Park, Cal.

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-27-

c

Communications & Data Collins Radio CooSystem Cedar Rapids, IowaControl Programmer Autonetics Div. of North

Earth Landingchute) SystemEnvironmentalSystemFuel Cell

Launch EscapePitch Control

American AviationAnaheim, Cal.(Para- Northrop Corp., Ventura Div.Newbury Park, Cal.Control AiResearch Div. of' Garret Corp.Los Angeles

Pratt and Whitney Div,United Aircraft Corp.Hartford, Conn.and Lockheed Propulsion Coo,Motors Redlands, Cal.

Service Module ReactionControl System Van Nuys, Cal.The Marquardt Corp,Stabilization and Con- Honeywell, Inc.trol System MinneapolisTelemetry Data Pro- Radiation Inc.cessing System Melbourne, Fla.Tower Jettison Motor Thiokol Chemical Corp.Elkton, Md.

Apollo Guidance and Navigation SystemDesign and Development Instrumentation LaboratoryMassachusetts Institute of Tech-

Cambridge, Mass.nologyManufacture, assembly, A C Electronics Div. of Generaltesting and subsystem Motors Corp.integration MilwaukeeSubcontractors - Space and Information Div.Digital computer and Raytheon Companydisplay keyboards Sudbury, Mass.Optical subsystem Kollsman Instrument Corp.(sextant telescope) of Standard Kollsman Industries, IncSyosset, N.Y.

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Ground Support EquipmentApollo Spacecraft General Electric Co.Acceptance Checkout Apollo Support Dept.Equipment (ACE) Daytona Beach, Fla.Saturn l l O A Checkout Radio Corporation of AmericaComputer and Displaysys tems Van Nuys, Cal.Aerospace Systems Div.

-End-

as-202 press kit

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