apollo 5 press kit

8/8/2019 Apollo 5 Press Kit

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0WL AEkONAKICS A ND SPACE ADMNlSTR4TlON W O 2-4153

WASHINGTDN,D .C. 20546 W O 3-6525

FOR RELEASE: THURSDAY P.M.January 11, 1968

RELEASE NO: 68-6K

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NA TIO NAL AERONAUTICS A N D SPACE ADMINIS TRATION W O 2-4155WASHINGTON,D .C . 20546 TELS' W O 3-6925

FOR RELEASE: T i s D A Y P.M.January 11, 1968

RELEASE NO: 68-6

APOLLO 5 FIRST LUNAR MODULE TEST IN SPACE

The f i r s t t e s t i n space of the Apollo spacecra f t lun ar

.module, th e vehi c le designed t o land two as t ron aut s on th e

Moon, i s scheduled t o t ake p lace no e a r l i e r than Jan. 18.

The u n m m e d E a r t h - o r b i ta l t e s t f l i g h t , designated

Apollo 5, w i l l be launched from Complex 37 a t Cape Kennedy,

Pla., by an Uprated Sa tur n I pockete Th e IH w i l l not be

Peeovered.

The lunar module i s one of three t h a t make up the Apollo

spac ecra ft . The ot he r two -- t h e comaand module and t h sservice moGule -- have been succclssfuully te s t e d i n s pace %nprevious unmanned rnisaiona and w i l l not be flown i n Apollo 5.


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The lu n a r module, weighing 31,700 pounds with pr op el la n ts ,

i s made up of two stages. The descent st ag e powers t h e

module from l un ar o r b i t t o th e Moon's surface. I t a l s o

serves as a launching pad f o r the ascen t stage, which l i f t s

t h e module from t h e Moon back t o t h e command and s e r v i c e

modules In lunar orb i t .

Object ives of t h e Apollo 5 f l i g h t a r e t o v e r i f y opera t ion

of t h e descent and ascen t propulsion systems inc luding restart

and l u n a r module s t r u c t u r e ; evalua te luna r module staging and

e v a l u a t e launch v e h i c l e performance.

Major even ts and maneuvers of Apollo 5:

About 54 minutes a f t e r launch th e lu na r module w i l l

se pa ra te from the second st age of th e Saturn and w i l l coas t

i n an o r b i t of 120-by-93-nautical mil es (138-by-107-statute

m i l e s ) , During t h i s and o the r coas t ing per iods the l u n a r

module reaction control system w i l l m a i n t a i n v e h i c l e 8 t t l t u d e .

and s e t t l e main engine pr op el la nt s t o th e bottom of tanks .

The second stage of t h e launch vehicle w i l l perform a

propel lan t dump t e s t about one revolu t ion a f t e r separa t ion

from t h e l u n a r module. The t e s t I s designed t o remove t he

remaining liquid hydrogen and liquid oxygen propellants

through the engine.


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The d e s c e n t a nd a s c e n t p r o p u l s i o n s y st em s i n t h e l u n a r

module w i l l be ope ra ted two t imes each .

The f i r s t o p e r a t i o n of t h e d e s c e n t p r o p u l s io n s y s te mw i l l

be a b ou t 4.5 h o u rs a f t e r l i f t - o f f . T h i s w i l l c o n s i s t o f a

26-second burn a t 10 p e r c e n t o f r a t e d t h r u s t of 10,500

pounds and then a b u i l d u p t o 92.5 p e r c e n t . The t o t a l b ur n

time, 38 seconds , w i l l change t h e o r b i t o f the l u na r module

t o 178-by-116-naut ical miles (206-by-134-s ta tu te mi les ) .

T h i s o p e r a t i o n of t h e d e s c en t p r o p u ls i o n i s t o s im u l a t e

t h e Hohmann (minimum energ y) burn t o be used i n t h e lu n a r

m is sio n t o t r a n s f e r t he lunar module from s. c i r c u l a r o r b i t

a b o u t t h e Moon t o a t r a j e c t o r y tow ard t h e l u n a r s u r f a c e.

A second descen t p ropu l s ion sys t em burn t akes p l ace some

36 minu tes l a t e r t o s i m u la te t h e t h r u s t l e v e l s p lanned f o r t h e

pow ered d e s c e n t p o r t i o n o f t h e l u n a r l a n d i n g m i ss i on . The

s y s t e m w i l l b u r n f o r a t o t a l . o f 12 .5 m in u te s i n c l u d i n g 10

s e c o n d s e a c h a t 10, 50, 30, 40 a nd 20 p e r c e n t t h r u s t l e v e l s

and f i n i s h i n g up w i t h t h e 92.5 p e r c e n t r a t e d t h r u s t l e v e l .

T h i s b u r n w i l l p l a c e t h e lunar module in a 172-by-166-naut ical

m i le (198-by-192-s ta tu t e m i l e ) o rb i t .


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The ascent propulsion system engine operation will beginsimultaneously with tennination of the second descent burn.

This will be a "fire-in-the-hole" burn (while the descent and

ascent stages are still attached) and stage separation will

occur. After this 5.25-second burn the descent stage will be

in a 172-by-166-nautical mile (198-by-192-statute mile) orbit

while the ascent stage will orbit at 172-by-167-nautical miles

(198-by-193-statute miles).

he ascent propulsion system will be operated one

revolution later. During this burn a test will determine

reaction control system operation using propellants from the

ascent propulsion system tanks which are interconnected to

the reaction control system tanks. The second ascent

propulsion system burn will be for 450 seconds to simulate

ascent from the Moon's surface in a lunar mission and will

place the ascent stage in an orbit at 440-by-170-nautical

miles (507-by-196-statute miles).


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Schedule of LM-1 events i n Apollo 5:

Time afterL i f t off Propulsion Duration O r b i tH r s . Min. Sec. Event System of Burn Naut ica l Miles00: 54 : 0 Se pa ra ti on from Reac tion 15 Sec. 120-by-93

Second Stage Control t o t a l i ntwof i r i n g s

First DPS. S r n Descent

Second DPS B u r n Descent

F i r s t APS Burn Ascent

Second APS f3urn Ascent

38 Sec. 178-by-116

12.5 Min. 172-by-166

5.25 Sec . 172-by-167(AscentStage)

7.5 Min 440-by-170(AscentStage)

The two op er at io ns of t h e desc ent and ascent propuls ion

systems w i l l complete th e primary missi on of b.pollo 5 but

ad di t i on al t e s t s may be conducted i n t he remaining seven-hour

l i f e t i m e o f th e l un ar module systems. The as ce nt st ag e i nexpected t o remain i n or b i t about two years, and th e descent

stage about three weeks. The launch ve h ic le second s t a g e

w i l l orb i t on ly abou t 18 hours.

A t t h e end of t h e i r o r b i t a l l i f e t i m e s t h e la un ch v e h i c l e

second st ag e and th e asc en t and descent s t ages w i l l r e e n t e r t h e

E a r t h ' s atmosphere and disintegrate.


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Launch veh ic le f o r th e Apollo 5 mission w i l l be t h e

Uprated Saturn I (AS-204) or i gi na l l y scheduled f o r t he f i r s t

manned Apollo miasi on i n Februa ry 1967. Following t h e f i r e

i n which A stronauts V i r g i l I . Ctrissom, .Edward H. White, I1

and Roger B. Chaffee were k i l l e d , the launch vehic le w a s

demated and removed from Complex 34 and re-erected on

Complex 37 f o r t h i s f l i g ht .

The launch veh ic le c o n s i s t s of t h e f i r s t (S-IB) stage

which develops 1.6 m i l l i o n pounds t h r u s t a t l i f t - o f f , t h esecond (S-IVB) s t a g e of 200,000 pounds t h r u s t i n space, and

a n instrument u n i t .

Apollo 5 w i l l no t ca r ry the f u l l Apo llo spacec ra ft .

Atop the instmrment un'it i s the spacecraft lunar module

ada pte r, which houaes t h e lu na r module (No. I ) , and a nose

cone. h n a r Module 1 w i l l not have i t s landing gear. I tw i l l c a r r y a mission programmer i n place of a st ro na ut s t o

c o n t r o l t h e s p a ce c r af t .

D i rec t to n of t h e Apollo Priogram, t h e United Sta tes t

e f f o r t t o land men on th e Moon and r et ur n them s zf el y t o

Earth before 1970, i s t h e r e s p o n s i b i l i t y o f t h e Office of

Manned Space Flight (OXSF), National Aeronautics and Space

Admin.istration.


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NASA8 s Manned Spacecraft Center (BE&), Houston, i s

resp onsib le f o r development of t he Apollo spac ecra ft, f l i g h t

crew training and mission control.

The NASA Marshall Space Flight Center (MSFC), Huntsville,

i s res pon sib le f o r development of t he Satu rn launch

vehicle.

The NASA John F. Kennedy Space Center ( w c ) , Kemedy

Space Canker, Fla. , ha s charge of Apollo/Saturn launch

operations.

NASAt s Goddard Space Flight Center (OSFC), Qmenbel t , Md.,

manages the -Harmed Space Flight Network under the d f rec t ion

of t h e Off ic e of Tracking; and Data Ac qu is it ion (OTDA),


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APOLU) 5 BACKGROUND INFORMATION

Spacecraft (M-1) Apollo 5 MissionLunar Module 1 ( ~ 4 - 1 ) co ns is ts of an ascent and a

descen t st age , th e two joined by fou r explos ive b o l ts anda n umbi l ica l. The s tages operate as a s i n g l e u n i t o r t h eascent s tage funct ions a lone.

Ascent S ta e The asc en t st ag e i s d iv id ed i n t o f i v e%+I-t r u c ura ar ea s t h e crew compartment, midsection, a f tequepment bay, ta nk and equipment mountings, and t h e o u te rakin and insula t ion. .

The crew compartoient i s a pressur e-t ight u n it some92 inches i n d iameter. S t r uc tur a l in t er f ace between th ecrew compartment and the midsection i s the forward midsectionbulkhead. These two se cti on s co ns ti tu te th e e n t i r e pressuri zedvolume a vai lab le f o r crew operat ion i n th e .IM.

The a f t equipment bay i s an aluminum alloy frame secunedt o t h e a f t midsection by aluminum al lo y trusswork. Theunpressurized compartment contains a se r i e s of co ld r a i l sf o r s t n c t u r a l mounting and thermal control of e lec t ron foeauipment, and tub ul ar tr us se s f o r tankage support. Th ecomplete ascent stage i s covered w i t h a thermal and meteoroids h ie ld of t h i n aluminum o r aluminized Mylar o r both.

Descent Stage: The main load-ca-rrying.stmcture of th edescent stage i s two pa.irs of p ar a ll e l beam i n cruoLfomarrangement, pl us upper and lower decks and enc los ur e bulk-haade of aluminum a l l o y i n conventional skin and st r i n g e rco ns tr uc ti on . The middle compartnen'c, fo me d by the crossedpairs of beams, con tain s th e descent engine. The ar ea s oneach s id e of th e ce nte r s t ru ct ur e house th e fou r main descentpropel lant tanks .

Addit ional support and s t r u t assemblies a r e secured t ot h e main beams t o f o m diago nal bays or quadrants . Viewedfrom to p o r bo'ctax, t h e stage f o m s an octagon. Owtriggers

extending from the ends of each pair of beass provide thef o u r poln ts of a t tachment t o the spacecraf t rt.I adap te r (SLA) .The landing gear l a not ca r r i ed on IE5-1


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A P O L L O 5 MISSION

LUNAR MODULE (LM-1)

S-BAND STEERABLE

D F l ANTENNA(2)

C-BAND ANTENNA(4)

'AGE


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1 . I N E R T I A L t J E AS U R IN G U N I T2. DOCKING HATCH3. D O C K I I G TA RG ET R E C E S S4. FUEL TANS (RCS)5. HELIUP.1 PRESSURE

REGULATING HODULE6 . AFT EQUIP/- iEXT6AY7. H E L I U t l TA NK ( R C S )

8. O X I D I Z E R TAN K ( R C S )9 . FUEL TANK

1 0 . ASCENT ENGINE COVER11 . CRE'J COI+IPARTbIEFIT1 2 . FOR!IARD INTERS TAGE FIT T IN G13 . I N G R E S S I E G R E S S H AT C H1 4 . CABIN WINDO!415. ALIG;I; ,!ETIT OP TI CA L TE LE SC OP E1 6 . EIIDSECTION

ASCENT STaGE

-mare-


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A F T I N T E R S TA G E F I T T I N G

FUEL TANK

ENG IN EMOUNT

PLSS, S-BAND AilTENilASTORAGE BAY

DESCENT EIiGINE

STRUCTURAL SKIN

1IISULATIOT.t

THER;IAL SHIELD

FOE.IA2D IPITET,ST.ASE FITTITI2

OXIDIZE? T

FUEL TAlUK

12. ,BATTERY STORAGE BAY

13. OXYGEN TANK

14. HELIUM TANK/CRYOGENIC

15 . DESCENT EhGINE SKIRT

16 . TRUSS ASSEMBLY (LEG GR)

17. LANDING RADAR ANTENNA

18 . S G I E N T I F I C E Q U I P I tE i lT BAY19 . GI F IaAL RING20 . ADAPTER ATTACHIIENT PO INT

21. OUTRIGGER

2 2 . OXIDIZER TA:II

apollo 5 press kit

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