Extensions of Saturn

8/4/2019 Extensions of Saturn

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D O U G L A S P A P E R N O . 4045

SATURN STORY DOCUM~NTUnive rs i i~ f Alabama RerelvLh /Ins;;iuieHistory of Science & Technoiog>, G ~ ~ ~ , ~

-r

Doc. No. -.-..---

E X TE N SIO N S O F S A T U R N

P R E P A R E D BY:JACK L. BROMBERGV I C E P R E S I D EN T - A SS IS T AN T G E N E R A L M A N A G E RA N D

T. J. GORDOND I R E C T O R - A D V A N C E S A T U R N

A N D L A R G E L A U N C H S YS TE M S

P R E P A R E D F O R P R E S E N T A T I O N TO :I N T E R N A T l O N A L A S T R O N A U T I C A L F E E E R A T I O NM A D R I D , S P A I N

O C T O B E R 10-15 . 1966

DOUGLAS M/SS/LE 6ZSPACE SYSTEMS D/V /S /ONSPACE SYST EMS CENTER - HUNT INGTO N BEACH, CALIFORNIA


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ABSTRACT

T h i s p a pe r d i s c u s s e s t h e p o s s i b l e a p p l i c a t i o n s of S a tu r nv e h i c l e s t o f u t u r e s pa ce e x p l o r a t i on . P o t e n t i a l m i ss i on su t i l i z i n g Apollo der i ved hardware a r e examined. Research ,d ev el op m en t, an d o p e r a t i o n s i n e a r t h o r b i t a s w e l l a s l u n a rexp lor a t i on , unmanned and manned in te rp la ne ta r y ex plo ra t iona r e re vi ewe d. These hypo the t i c a l mi s s ions a r e d i sc us se di n t h e c o n te x t o f t h e p r e s e n t a nd p o t e n t i a l c a p a b i l i t y oft h r e e c o n f i g u r a t i o n s o f t h e S a t u r n v e h i c l e ; a n u p r a te dSa tu rn I , a t h re e - s t a ge Sa tu rn V and a four-s tage Sa tur n V .

NOTE: Work pres ent ed h er ei n was conducted by th e DouglasMissiles and Space Systems Division under company-sponsoredres ear ch and development funds . There fo re , th e conceptsand o b j e c t i v e s d e s cr i b ed w i t h i n t h i s pa pe r r e f l e c t t h eo p i n i o n s o f t h e a u t h or s an d d o n o t n e c e s s a r i l y c o n s t i t u t eendo rs em en t by NASA, t h e A i r F o r ce , o r a ny o t h e r U. S.Government or ga ni za ti on . The nominal perfor mance numbersp r e s e n t e d a r e t y p i c a l o f t h e c u r r e n t c o n f i g u r a t i o n s an dp o s s i b l e f u t u r e v e h i c l e c o n f ig u r a t i o n s .


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EXTENSIONS OF SATURN

INTRODUCTION

The l a n d i n g o f A p o ll o o n t h e l u n a r s u r f a c e w i l l re pr es en t th e accompl ishment ofa m aj or U n i te d S t a t e s g o a l i n s p a c e . I t was a g oa l which was bra vel y s t a t e d andbo ld ly pu r sued. The r e sou r ces accumula ted i n accompl ish ing t h i s goa l w i l l b eab l e t o s e r ve t h e Un i t ed S t a t e s and t h e wor ld i n mi s s ions even more complex andperhaps u l t im a t e ly more impor tan t t ha n Apo llo . These r e sou rces i n c lude l aunchf a c i l i t i e s , t r a c k i n g s ys te m s, v e h i c l e p r o p u l s iv e t e c hn i q u e s, i m po rt an t te ch no -lo g i ca l and manufac tu r i ng compe tence, knowledge o f t h e func t i o n ing and l im i t a -t i o n s o f man i n s p a c e , a nd t a l e n t a nd e x p e r t i s e t un e d t o t h e n e e ds o f t h e s pa c ep rog rams. C ont inued use o f t he se Apo llo p roduc t s and ca pa b i l i t i e s w i l l make itp o s s i b l e f o r t h e U ni te d S t a t e s t o p ur su e a dva nc ed g o a l s w i th ou t t h e n e c e s s i t yf o r d u p l i c a t i n g t h e i n v e s tm e n t w hic h w i l l l e a d t o t h e s u c c e s s f u l a c co mp li sh me nto f A po ll o. The p o s s i b l e a p p ro a c he s o u t l i n e d a r e c o n si d er e d t o b e a l o g i c a le x t e n s i o n o f c u r r e n t know ledge e x t r a p o l a t e d t o f u t u r e s p ac e r e qu i re m e n ts .

T hr ou gh ou t t h i s p a p er t h e g e n e r a l pe rf or ma nc e o f t h r e e v e h i c l e s w i l l be d i s cus sed .T he se v e h i c l e c o n f i g u r a t i o n s a r e shown i n f i g u r e 1. The f i r s t i s a s ta n da rdt h r e e - s t a g e S a t u r n V, t h e s ec on d i s a f ou r - s ta g e c o n f i g u r a t i o n o f S a t u r n V anduses a C e nt au r a s a t y p i c a l example o f t h e f o u r t h s t a g e . The t h i r d c o n f i g u r a t i o ni s a s t a n da r d up r a t e d S a t ur n I v e h i c l e . The d e t a i l s o f t h e s e c o n f i g u r a ti o n s andt h e i r pe r formance a r e we l l known. B r i e f l y , t h e s t a n d ar d S a t u rn V veh i c l e we ighsapproximate ly 2 .9 m i l l i o n k g ( 6 . 4 m i l l i o n po un ds) a t l i f t - o f f a nd c an p l a c e o v e r118 ,000 kg (260 ,000 pounds) i n ea r t h or b i t o r 43,000 kg (95 ,000 pounds) t o escapev e l o c i t y . The up ra t ed S a tu rn I can p l ace 16 ,700 kg ( 3 7, 00 0 p ou nd s) i n e a r t h o r b i t .These veh i c l e s w i l l be ex t remely impor t an t i n accompl i sh ing f u t u r e space goa l s .

F ut ur e a c t i v i t y i n s p ac e c an b e g ro up ed i n t o t h r e e r eg im es o f e x p l o r a t i o n : r e s e a r c h ,development and ope ra t i ons i n ea r t h o r b i t ; unmanned and manned in te rp la ne ta rye x p l o r a t i o n , an d l u n a r e x p l o r a t i o n . We w i l l r ev ie w t h e p o s s i b l e a p p l i c a t i o n o fApo llo -de rived ha rdware t o fu tu re mi s s ions i n t h e s e t h r e e c a t e g o r i e s o f s pa ceo p e r a t o n .


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EARTH ORBIT

The pe rfo rmance o f t h e t h ree - s t age and pos s ib l e fou r - s t age con f igu ra t i on o fS a t u r n V i s shown i n f i g u re 2. The two-stage upra ted Satu rn I v e h ic l e i ssummar ized i n f i gu re 3. I n e a ch i n s t a n c e it i s p o ss ib l e f o r t h e s e v e h ic l e s t oa c h i ev e o r b i t a l v e l o c i t y w i th o n l y tw o s t a g e s . The u p r a t e d S a tu r n I can boos to v e r 1 6, 70 0 kg ( 37 ,0 00 p ou nd s) t o l ow e a r t h o r b i t a t low i n c l i n a t i o n s a n d t h eS a t u r n V , 117,500 kg (260,000 pounds). The S-IVB st a g e as employed i n Sa tu rn Vi s capab l e o f r e s t a r t . Our pe rformance s t ud i es have shown th a t when h ighera l t i t u d e s a r e r e q u i r e d , p a yl oa d c an b e i n c r e as e d by f i r s t e n t e r i n g a l o w e a r t ho r b i t and t hen accompl ish ing a Hohmann t r an s f e r t o a h igher a l t i t ud e . The pe r -f or ma nc e a c h ie v ed i n t h i s S a t u r n V m i s s io n i s shown i n f i g u r e 4. Note i n t h i sf ig u re th a t approximate ly 31,500 kg (70 ,000 pounds) can be p laced t o synchronouso r b i t u s i ng S a t u rn V.

The e a r t h e s c a p e c a p a b i l i t y o f S a t u r n ca n b e s i g n i f i c a n t l y augmented i f t h ev e h i c l e i s u s ed i n c o m bi na ti on w it h an upra t ed S a tu rn I launch . For example,i f a p o r t i on o f t h e p ay lo ad i s b oo st ed t o e a r t h o r b i t o n an u p r a t e d S a t u r n I an dt h e r e m ai ni ng p o r t i o n o f t h e p ay lo ad i s l aunched wi th Saturn V , t h e two pay loadscou ld r endezvous and dock i n ea r t h o r b i t . The Sa tu rn V/S-IVB would th e n pr ov ideescape ene rgy wi th i t s second burn. While a s ta nd ar d Satu rn V can launch43,000 kg (95 ,000 pounds) t o e scape ve loc i t y , t h e rendezvous mi s s ion dep i c t ed i nf i g u r e 5 can escape 54 ,500 kg (120 ,000 pounds) , an inc re ase of about 25 perc ent .I t i s s i g n i f i c a n t t o n o t e t h a t t h i s t y p e o f mi ss io n do es n ot r e q u i r e a ny a d d i t i o n a lh ar dw a re ; r a t h e r t h e g a i n i s a c h i ev e d by u s i n g e x i s t i n g S a t u r n h ar dw ar e i n t h eapp rop r i a t e s equence .

I n c e r t a i n f l i g h t s o f u p r at e d Sa tu rn I and Saturn V , i n b o t h t h e A p o ll o a ndfo llow-on programs, t h e upper or S-IVB s ta ge s ar e expected t o remain i n o r b i ta f t e r p r o p e l l in g p ri ma ry p a yl oa ds i n t o t h e i r m is si on t r a j e c t o r y ( s e e f i g u r e 6 ) .Such e xpe nded o r s p e n t s t a g e s c o u ld be p r o f i t a b l y u t i l i z e d i n s c i e n t i f i c e x pe r i-ments , tec hno logy development , and sometimes even op er at io na l sup port . Thus, itappear s t h a t t h e expended S-IVB s t a ge s , r a t h e r t han d r i f t i n g unused i n space , mayb e a p p l i e d t o a n e n t i r e l y new s e r i e s o f s ec on da ry a p p l i c a t i o n s .

Due t o i t s l a r g e volume a n d o t h e r u ni qu e c h a r a c t e r i s t i c s , t h e d r i f t i n g S-IVBst ag e can prov ide some r a t he r economicai and use fu l s er v i ce s and accommodat ions


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NOMINAL SATURN V THREE & FOUR STAGE PERFORMANCE(LAUNCH AZIMUTH 90" - ORBIT INCLINATION 28 .5")

HYPERBOLIC EXCESS VELOCITY , V (1000 FPS)NOTES: WHERE: (UPS r 305)

1. COPLANAR DIRECT ASCENT V, =VE HIC LE CUT-OFFLAUNCH FR OM E. T.R. VELOCITY INERTIAL,( FT I S E C )2. PARKING ORBIT ALT ITUDE - ESCAPE VELOCITY ATI W N . MI. Vest= A C U T- OFFALTITUDE (FT'SECIV a ) = G3 ENERGY PARAMETER

FIGURE 2

NQMINAL UPRATED SATURN I PERFORMANCE

35

30

25

2 0

15 - HREE STAGE-- WO STAGE

10100 SO0 1000 1500 2000 2500ALTITUDE (N M I)

(KM 1 1 85)FIGURE 3


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SATURN V HOHMANN TRANSFER PAYLOAD CAPABILITYPAR KI N G O R BI T AL T I T U D E (N. MI.)

INJECTION INTO/ rlmL ORBIT

P A Y L O A D (1000 LBS)(K g x 453)

FIGURE 4

PAYLOAD RENDEZVOUS MODE

FIGURE 5

5


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APPLICATIONS OF THE SATURNS-IVB SPENT STAGEFOR SCIENCE, TECHNOLOGY, AND OPERATIONAL SUPPORT

FIGURE 6i n s pa ce . An example of a sp e n t S-IVB a pp l i c a t i on t h a t c an be c ons ide re d i s ano r b i t a l rendezvous and launch technology exper iment in volvin g two S-IVB's .

O r b i t a l Rendezvous and Launch Technology

Many of t h e f u tu r e programs be ing s t u d i e d i n v o l v e o p e r a t i o n s s uc h a s v e h i c l er en d ez vo u s, d o ck i n g, o r b i t a l c h ec ko u t, r e s t a r t , a nd l a un c h. I n r e c e n t y e a r s ,t h e r e h a s b ee n a c ons ide ra b l e g rowth i n i n t e r e s t c on ce rn in g o r b i t a l a ss em bl yand r e u s e o f v e h i c l e s f o r s u ch a p p l i c a t i o n s a s M ar ti an Fl yb y, l a r g e o r b i t a lr e s e a r c h l a b o r a t o r i e s , o r b i t a l l au nc h f a c i l i t i e s , and s pa ce l o g i s t i c s s ys tem s.I n d i c a t i o n s a r e t h a t t h e s e s ys tem s w i l l be de ve loped subse que n t t o t h e Apo l loPr og ram i n t h e n i n e t e e n s e v e n t i e s an d n i n e t e e n e i g h t i e s . T h e r e f or e , it i si m p o r t an t t h a t t h e v a r i o u s t e c h n o l o g i e s i n vo l ve d i n s uc h f u t u r e s y st em s b e a tl e a s t b r o ac he d o r e l e m e n t a l l y de ve lo p ed a s soo n a s p o s s i b l e .

The programs fol low ing Apollo w i l l undoubted ly i nvo lve a g r e a t va r i e ty o f s c i e nc eand technology exper iments . I n t h e te c hno logy a r e a , t h e e xpe r ime n ts c ould ra ngef ro m t h e t e s t i n g o f s p ac e e f f e c t s on c om ponents t o l a r g e s c a l e o p e r a t i o n a l


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e xp er im e nt s i n v o lv i n g e n t i r e v e h i c le s . S i nc e t h e r e i s c on s i de r a b le i n t e r e s ti n u t i l i z i n g c u r r e n t v e h i c l e s a s much a s p o s s i b l e t o p e n e t r a t e new te c hn ol og yand mi s s ion a re as , t h e spen t S-IVB a f f o rd s an exce l l en t exper imen ta l r e sou rce .

I n v ie w o f f u t u r e s p ac e sy st em o b j e c t i v e s , we f e e l t h a t c o n s i d e r a b l e r e s e a r c hand development shou ld be conduct ed i n t he f i e l d s o f o rb i t a l r endezvous, dock ing ,a nd r e s t a r t ; p a r t i c u l a r l y t h e a s s o c i a t e d m e ch an ic al , h y d r a u l i c , p n eu ma ti c,e l e c t r i c a l , and e l e c t r o n i c i n t e r a c t i o n betw ee n v e h i c l e s i n s pa c e.

A gr ea t amount o f da t a on t h e bas i c hardware and t echn iques i nvo lved i n o r b i t a lo p e r a t i o n s c an be a c q u i r e d th r ou g h t h e j o i n t l a un c hi n g an d i n t e r a c t i o n o f t woup ra te d Sa tu rn I/S-IVB s t a g e s , accompanied by a manned Apo llo Command and Se rv ic eModule ( s ee f i g u r e 7 ) . I n t h i s h y p o t h e t i c a l e x pe ri me n t, t h e f i r s t o f t wo up r a t edS a t u r n I v e h i c l e s u s e d w ould l a un c h a n S-IVB w hic h i n j e c t s i t s e l f i n t o o r b i t w i t happ rox imate ly 8,600 kg (19,000 pounds ) o f r e s i du a l p ro pe l l a n t s , ve ry s i m i l a r t ot h e experiment f lown on Veh icle AS-203. The second upr ate d Satu rn would req ui rea Command and Se rv ice Module launched t o in te rc ep t t h e f i r s t o r unmanned ve hi c l es h o r t l y a f t e r c om ple tio n of i t s f i r s t o r b i t ; s i m il a r t o Gemini 7 and 6 miss ion .The manned v eh ic le would be f lown t o a po s i t i on s l i g h t l y below and ahead of th et a r g e t v e hi c l e , u si ng f u l l J-2 engine th r u s t of 885,000 newtons (200,000 pounds) .Gross t e rm in al rendezvous would be accompli shed wi th t h e J-2 engine o p e r a t i n g i nan i d l e mode a t app roximately 26 ,500 newtons (6 ,000 pounds) t h ru s t and br ing th ec h as e v e h i c l e 90 m e te r s ( 3 00 f e e t ) i n f r o n t o f t h e t a r g e t v e h i c l e . Micro-rendezvous and docking would be accompli shed wi th t he au xi l i ar y prop uls ion systemo f t h e ch a se v e h i c l e u nd er d i r e c t a s t r o n a u t o bs e r v a ti o n . A f t e r d oc k in g , a453 kg/min (1 ,000 pounds per minute) pro pe l la n t t ra n sf e r exper iment would beperformed, fol lowe d by a 5-2 engine checkout , countdown, and r e s t a r t . It appearsf e a s i b l e t o b u rn t h e J- 2 e n gi ne f o r a p pr ox im at el y t e n s e c o n d s , i n such a r e s t a r t .T hi s t h r u s t c ou ld b e us ed t o e i t h e r p ar k t h e v e h i c l e i n a h ig he r o r b i t o r pe rhapsd e o r b i t i t f o r d e b r i s c o n t r o l o r i n a re c o v e ry e x pe ri me nt .

Performing t h i s k ind of exper iment would penn i t development of t echnology le ad ingt o s t a g e a s se mb ly i n e a r t h o r b i t a nd te c hn o lo g y e xp e ri m en t at io n w i t h l a r g e s c a l ep r o p e l l a n t t r a n s f e r , b o th i m po rt an t f a c e t s o f f u t u r e s pa ce o pe r a t i o n s .


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S-IVB LARGE SPACE VEHICLESRENDEZVOUS AND D O C K I N G

BOOST TRAJECTORY7 0 F LV

POSITION OF OTV -END OF 1ST ORBIT\\

\

HOURS I/

/BOOST /

/ /\.--/F OTVS-IVB OTV /OLV MISSION

PROFILE

MODE 1

Ts

AP OLL O SERVICE/COMMAND MODULO LV

MODE

L

*----?qq'\4\;I ..

4

O T V = O R B I T A L T A R G ET V E H I C L EO LV = ORBITAL LAUNCH VEHICLE

FIGURE 7


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INTERPLANETARY EXPLORATION

The S a t ur n v e h i c l e f a m i l y c an s i g n i f i c a n t l y c o n t r i b u t e i n t h e p u r s u i t o f i n t e r -pl an et ar y go al s both f o r manned and unmanned miss ions . In th e ca se of unmannedpro bes , t h e Voyager payload f o r f l i g h t s t o Mars and Venus aboard Saturn V couldbe cons ide red i n t h e e a r l y and mid -70' s. A p o s s i b l e c o n f i g u r a t i o n i s shown i nf i g u r e 8. Here t h e t h re e - s t age S a tu rn V i s u se d t o d e l i v e r two p ay lo ad s t o M ars.The payloads themselves have been conceived a s f ly by spa ce cra f t which sep ar a teand mon i to r s o f t l and ing modu les. Depending on t h e exac t na tu re o f t h e t r a j e c t o r ychosen , Saturn V can boo st approximately 34,000 kg (75,000 pounds) of payload ona 150-day Mars t r i p .

Unmanned In terp lanetary Explora t ion

The Sa tur n famil y of ve hi cl es ca n perform missions demanding even more bo os te renergy tha n Voyager . We have analyzed , f o r example , t h e use of Saturn V i nth ree - s t a ge and fou r - s t ag e modes i n mi s s ions t o a l l o f t h e p l a n e t s , t h e a s t e r o i d s ,f l i g h t s to w ar d t h e s u n, f l i g h t s o u t - o f - t h e - e c l i p ti c and beyond t h e s o l a r s ys te mi t s e l f . I n d is c us s in g t h e p o t e n t i a l pe rform ance of t h i s v e h i c le i n t h e s eadvanced mi s s ions , r e fe ren ce w i l l be made t o cu r ren t con f igu ra t i ons . The f i r s - to f t h e s e i n c l ud e d i n o u r s t u d i e s i s t h e s ta n d ar d S at u rn ;V us in g t h e Voyagersh roud, shown i n f i g u r e 9. The upper s tag e here cont a in s about 18 ,200 kg(40 ,000 pounds) h igh energy prop el l an t and has a th ru s t o f 133 ,000 newtons(30,000 pounds) . Th i s s t age i s rough ly equ iva l en t t o t oda y ' s C en t au r . Somepos s ib l e f u t u r e unmanned i n t e r p l a ne t a r y mi s s ions a r e r ev iewed i n t u rn .

P l a n e t a r y E x p l or a t io n

F l i g h t s t o Mars a nd Venus r e q u i r e l e s s e n er gy t h a n o t h e r p l a n e t s . A s o ur i n t e r e s tbeg ins t o ex t end beyond t h e nea rby p l an e t s , we w i l l f i n d t r i p t im e i n c re a s i ng a ndpay load capac i t y o f l aunch syst ems d imini sh ing . F or example , a t r i p t o Ju p i t e r ,a p a r t i c u l a r l y i n t e r e s t i n g t a r g e t b ec au se of i t s m ass, w i l l r equ i re app rox imate ly750 days on a s imp le Hohmann t r an s f e r t r i p t r a j ec to ry . The t h ree - s t a ge S a tu rn Vveh i c l e cou ld de l i v e r a 10,800 kg (24 ,000 pound) pay load on t h i s m i s s ion ; t h i spayload could be incr eas ed t o 16,300 kg (36 ,000 pounds) by us in g a four-s ta geS a tu rn V. I f p a y l oa d s o f t h i s ma gn itu de a r e n ot r e q u i r e d , a p p r e c i a b l y s h o r t e r


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POSSIBLE VOYAGER PAYLOAD ARRANGEMENT

FIGURE 8

4th STAGE FOR SATURN V FOR DEEP SPACE MISSIONS

FIGURE 9

10


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t r i p t imes can b e ach ieved a s shown i n f i g u re 1 0 . Note th a t w i t h t h e fo u r -s t ag eSa tu rn V co n f i g u ra t io n , t h e t r i p t ime can b e r ed u ced by o n e-ha lf and a p aylo adof 5,800 kg (13,000 pounds) i s s t i l l a v a i l a b l e .

.'

Comet I n t e r c e ~ tSh o r t p e r io d co mets r e t u r n ev e ry s ix o r sev en y ea r s and have a p h e l i a c l o se t oJ u p i t e r ' s o r b i t . These comets i n p a r t i c u l a r w i l l p ro vid e good t a r g e t s f o r p ro b ev e h i c l e s o f t h e f u t u r e b ec au se t h e i r o r b i t s a r e known and t h e i r a r r i v a l t i me s a r epr ed ic ta b l e . The Comet Encke i s a good cho ice f o r a comet in te rc ep t miss ionbecause it i s a s s o c i a t e d w i t h f o u r l a r g e m et eo r s t re a ms a nd t h u s w i t h a l a r g eq u a n t i t y o f m e t e o r i t i c m a t e r i a l . It i s a l s o t h e c l o se s t t o e a r t h , a b ri g htc om et , a n d p r o vi d e s t i m e , p r i o r t o p e r i h e l i o n , a v a i l a b l e f o r d a t a re c ov e ry .Encke has a sh or t per iod which prov ides many launch oppo r tu n i t ies . I t should beemp hasized th a t , en ro u te t o th e comet, v e ry v a lu ab le in fo rma t io n can beco l l ec t ed o n a l l a sp e c t s o f sp ace env iron ment o u t s id e th e p lan e -o f - th e -ec l ip t i c .

The th ree -s tag e Sa tu rn V can boo st 10,000 kg (22,000 pounds) on an in te rc e ptt ra j e c t o r y wi th Encke and t h e fo ur s ta ge veh ic l e , 15 ,400 kg (34 ,000 pounds) . Thet r i p t im e f o r t h i s m i ss i on i s ap pr ox im at el y 1 00 d ay s. P a r t i c u l a r l y i n t e r e s t i n ge x pe r im e nt s c o u l d b e pe rf or me d r e l a t i n g t o t h e d e t er m i na t i on o f t h e comets t ru c t u r e , p l asma in t e r ac t i o n s , and ch emica l co mp o si t io n . FoT' example, physicalins tru me nta t io n could be employed which might confirm or r e f u t e th e " icy conglom-er a t e" model concep t now thought t o rep res en t comet s t r uc tu re .

As te ro id Miss io ns

Between t h e o r b i t s o f Mars and Ju p i te r revo lve thousands o f smal l bod ies c a l le da s t e r o i d s , p l a n e t o i d s o r m in or p l a n e t s . Some a r e o n l y a few m i l e s o r l e s s i nd i a m e t e r ; w h i l e Ce r es , t h e l a r g e s t , i s n e a r l y 925 km (50 0 mi l e s ) ac ro ss .

Typica l a s te ro id exper iments would in c lude measurement o f mass d i s t r i bu t i on ;o p t i c a l s p e c tr o gr a p hi c e xp er im en ts r e l a t i n g t o ph y s i c a l p r o p e r t i e s o f t h ea s t e r o i d s , c he mi ca l a n a l y s i s of t h e p a r t i c l e s i n v o l vi n g t h e rm a l n e u tr o n a c t i v i t y ,neut ron cap tu re , gamma ra y an al ys is , gas chromatography, X-ray f lu ore sce nce , e t c . ,t o de termine organ ic and inorgan ic composit ion of some smal l cap tured as te ro id s ,measu rement o f in t e r p la n e t a ry magn et ic f i e ld s , i n t e r a c t io n o f th e so la r p la sma


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T R I P TIME VS P A Y L O A D C A P A B I L IT Y

w i t h t h e a s t e r o i d s , e q u i li b r iu m t em p e ra tu r e i n t h e b e l t . A l l w i l l b e of v i t a ls c i e n t i f i c i n t e r e s t . T e le v is io n p i c t u r e s o f t h e a s t e r o i d s may l e a d t o g r e a t e rund ers t andi ng of t h e process es of format ion of th es e anomolous bodies and t h es o l a r s y st em i t s e l f . Sa tu rq V can p lace a 3,200 kg (7,000 pound) payload p as tt h e a s t e r o i d C e r es a nd t h e f o u r -s t a g e v e r s i o n c an b oo s t 1 0, 00 0 kg (22,000 pounds)T h i s m i ss i o n i n v o l v e s a t r i p t i m e o f 200 d a ys .

800- 700uP SATURN V-

FOUR STAGE

Sola r P robe

CT4= 300z41= 2001?.lJ&f 100

A probe toward th e sun wou ld have a s i t s ob j e c t i ve s t h e de t e rmina t ion o f :1. S p a t i a l and t e mp o ra l v a r i a t i o n o f d i s t r i b u t i o n , e ne rg y s p e c t r a , and

t r a j e c t o r i e s o f s o l a r p a r t i c l e s .2 . Type o f p a r t i c l e m a t t e r , i . e . , e l e c t r o n s , p r o t o n s , n e u t ro n s a nd

h e a v i e r i o n s .

0 5 10 15 20 25 30 35 40PAYLOAD (LBS) x 103(Kg 453)FIGURE 10

.-

3. The s p a t i a l an d t em p o ra l v a r i a t i o n of m ag ne ti c a nd e l e c t r i c a l f i e l ds t r e n g t h s a n d d i r e c t i o n s .

4. I n t e r a c t i o n s betw een p a r t i c l e s and f i e l d s .

NOTE: PERFORM ANCE DATA BASED ON 90' LAUNCH AZIMUT HCOPLANAR DIREC T ASCENT LAUNCH FRO M EASTERN -TEST RANGE

5 . Exte n t o f t h e l ower f re quenc y e l e c t roma gne t ic r a d i a t i o n f rom th e sun .


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The c lo s e r a p ay lo ad i s p l aced t o th e su r f ace o f th e su n, t h e more ene rg ydemanding t h e mis sion . A so la r p robe f lown t o . 2 AU and boosted by a four-s t a g e S a t u rn V can weigh 6,700 kg (14,000 pounds); on a missi on t o .12 AU, afour -s tage Sa turn V can boo st 2,500 kg (5,500 pounds). The t r i p t imes a sso c ia t edwi th the se miss ions a re 80 and 75 days , res pec t ive l y .

Out-of- the-Eclipt i c Probes

A l l p l a n e t s o r b i t i n p la ne s t h a t a r e i n c li n e d l e s s t h a n 7 de gr ee s f rom t h ee c l ip t i c p l an e ex cep t P lu to which i s i n c l in ed 1 7 d eg rees . To d a t e , s c i e n t i f i cmiss ion s have b een l im i t e d t o n ea r th e e c l ip t i c p l an e. Space ex p lo ra t io n in toh ig h e r in c l in ed o r b i t s ( o u t -o f - th e - ec l ip t i c ) a r e most d es i r ab l e , bu t h ig h erb o os t v e l o c i t i e s a r e r e q u ir e d .

An out -of -th e-e cl ipt ic probe would determine whether s o l a r phenomena, such asth e so la r wind , p o ssess sp h e r i ca l symmetry o r a r e co n fin ed ch ie f ly t o th e p lan eo f t h e e c l i p t i c . The probe w i l l measure s o l a r phenomena, inc ludi ng so la r storms,e l ec t ro m a gn e ti c a nd e l e c t r o s t a t i c f i e l d s , h i gh e n er gy p a r t i c l e s and p er h ap s ,X and Gamma Ray measurements towa rd and away from th e sun. By making th e s emeasu rement s i n a p l an e in c l i n ed s ig n i f i ca n t l y o u t -o f - th e - ecl ip t ic ( 10 ' - 45 ' ,a t h i r d dimension would be added t o ou r knowledge of so la r system physics.

I f t h e m i s si o n w ere d e f i n ed a s r e q u i r i n g an o r b i t a l t r a j e c t o r y i n c l i n a t i o n 30't o t h e e c l i p t i c w i th a r a d i u s from t h e sun e qu al t o t h a t o f t h e e a r t h ' s o r b i t a lra d i us , a pay load of about 545 kg (1 ,200 ~ o u n d s ) ou ld be boosted by t h e four -s t a g e S a t u rn V. The mission i s q u i t e s e n s i t i v e t o i n c l i n a t i o n a ng le and i f t h emiss ion i s f lo wn a t 2 5' i n c l in a t i o n , p ay lo ad w i l l r i s e t o 5 ,450 kg (12,000 pounds) .

&

Em lo ra t i on of Earth/Moon L ibra t ion Po in ts

S ta b le g r a v i t a t i o n a l p o in t s ex i s t be tween two p lan e ta ry b od ies . These points,known a s t h e L /L " Tro ja n" p o i n t s , a r e e s t a b l i s h e d by t h e r e s t r i c t e d t h r e e body4 5g r a v i t y c a s e . The most in te re s t in g examples o f na t ura l bod ies t h a t occupy po i n tsL4 and L a r e th e "h o ja n " a s t e ro id s , which a r e i n th e Su n- Ju pi te r sys tem. Fo r5t h e e a r t h and moon, t h e p o i n t s a r e l o c a t e d i n t h e p la n e t h a t i n c l ud e s t h e e a r t h /moon ax i s l i n e an d th e lu n a r o rb i t . Each p oin t l i e s a t t h e apex o f an eq ui -l a t e r a l t r i a n g l e w i t h t h e moon a nd t h e e a r t h a t t h e o t h e r two a pe xe s ( s e ef i g u r e 1 1 ) .


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EARTH-MOON LIBRATION POINTS

II

FIGURE 11Access t o ear th /moon L4 and L would i n v o l v e s p ace f l i g h t f ro m t h e e a r t h5s i m i l a r t o t h a t f o r a l u n a r m i s s io n , e xc e pt t h a t t h e r e would be a n a bs e nc e o fa t t r a c t i n g f o r c e s a s t h e s p a c e c ra f t a pp roa che d t h e L p o i n t .

I n a t y p i c a l m is si on a s a t e l l i t e would b e p la ce d a t t h e L4 o r L p o in t s; t h i s5body c o u l d p e r s i s t i n s t a b l e m ot io n a bo ut t h e e a r t h a t t h e s e tw o p o i n t s . Thes a t e l l i t e would p ro vi de d a t a on t h e g r a v i t a t i o n a l f i e l d s s u rr ou nd in g t h e e a r t hand moon and any cy cl ic phenomena a ss oc ia te d wi t h the se f i e l d s . I t might alsomake measurements t o de te rmine th e conc en t ra t ion , s i z e , and mass o f t he p oss ib led u s t c l o u d s ( co smic d e b r i s ) c en t e r ed a t t h i s r eg i o n . T hese ex pe r iment s cou l dprov ide va luab le in fo rmat ion abou t th e o r ig in o f t h e moon and th e s o l a r system.

S a t e l l i t e s l o ca te d a t t h e l i b r a t i o n po i nt s (L4 and L ) n o t o nl y have s c i e n t i f i c5v a l u e , b u t may a l s o h ave p o s s i b l e p r ac t i ca l ap p l i c a t i o n s . T hese b o d i e s co u ld b eused a s a communicat ion re la y s t a t i on f o r deep-space p robes o r manned l and ingson ot he r p l a ne ts , th us minimizing t h e long di s t an ce communication problem. Theymay a l s o be used as a "warehouse" t o s t o r e equ ipment dur ing th e es tab l i shm ent o fa l u n a r b a s e .


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The s tand ard Saturn V can p l ace34 ,00 0kg (76,000 pounds ) a t t h e ea r th /moonl ib r a t i o n po i n t s and t h e fou r - s t age ve r s i on , 38,500 kg (85 ,000 pounds ) .

Probes-Out-of-the-Solar Svstem

The n e x t s t e p beyond e x p l o r a t i o n o f t h e s o l a r s y st em i s e x p l o r a t i o n o f i n t e r -s t e l l a r space. Th i s t yp e o f m i s s ion env i s i ons an i n s t rxnen t ed probe boos ted t o'-a v e r y h i g h v e l o c i t y , 16,750 mete r/se c (55,000 f t / s e c minimum) which w i l l a l l owit t o e sc ap e t h e s o l a r s y ste m. This type of probe w i l l p ro vi de t h e f i r s t d i r e c ts t udy o f t h e i n t e r s t e l l a r medium. Such p robes w i l l c o l l e c t s c i e n t i f i c d a t a oncosmic ra ys , s t e l l a r dus t and o th er g al ac t i c phenomena and may prov ide new clue st o t h e o r i g i n and n a t u r e o f t h e u ni ve r se . A lso d e t a i l e d tr a c k i n g of t h e o r b i tof t h i s p r ob e may a i d i n t h e d e t e rm i n at i o n o f a d d i t i o n a l s o l a r s ys te m p l a n e t s .

The s c i en t i f i c obse rva t i ons t h a t cou ld be pe rformed on a probe escap ing t h es o l a r s y s te m a r e e s s e n t i a l l y t h e same a s t h o s e o n t h e o u t- o f - t h e - e c li p t i c p r ob e s.However, in s t ea d of obse rv ing th e in terp lanetary medium as a f u n c t i o n o f a n g l efrom t h e e c l i p t i c , t h e pr ob e w i l l s tudy t h e i n t e rp l an e t a ry medium a s a f u n c t i o n

,

of d i s t an ce f rom t h e sun . These obse rvat i ons would inclu de:

1. Veloc i t y and den s i t y o f t h e so l a r wind and t he boundary between t hes o l a r w ind a n d t h e i n t e r s t e l l a r medium.

2. Neu t ra l gas a toms and molecules .3. G r a d ie n t s i n t h e i n t e n s i t y o f g a l a c t i c c osmic r a y s .4 . Solar cosmic rays .5 . Magnet ic f i e l d a s so c i a t e d wi th s o l a r w ind, bo th be fo re and beyond

so l a r wind t e rmina t i on .6 . G a l a c t i c ma gn et ic f i e l d .7 . I n t e n s i t y a nd v e l o c i t i e s o f m e te o ro i ds .8. S earch f o r p resence o f t r ans -P lu to p l a ne t s and p l an e t s l oca t ed

beyond Pluto.

The four -s tag e Satu rn V can pl ac e 5,750 kg (13,000 pounds) on an ex tr a- so la r systemf l i g h t . However, w i th t h i s payload weigh t t he f l i g h t t imes t o r each beyond t heo r b i t o f P l u t o a r e q u i t e l a r g e ; a p pr o xi m at e ly e l e ve n y e a r s . I n an e xc e ss v e l o c i t y


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mission some of th e payload could be t rade d fo r sho rte r f l ig h t t ime. Forexample, i f th e payload i s re s t r i c t ed t o 450 kg (1 ,000 pounds) , f l i g h t t ime t ot he o rb i t o f P l u t o d rops t o 7.5 years .

Thus, t he Saturn V vehic l e i n a th ree-s tage or four-s t age conf igura t ion cans a t i s f y th e complex requi rements p resented by th e goa l o f sc i e n t i f i c exp lora t ionof our so la r system. The performance of th es e veh icle s i s summarized i nf i g u r e 1 2.

Manned Interplanetary Explorat ionThe Saturn V c l a s s ve hi cl e can be used t o send men t o Mars and Venus i n f ly bymissions. For a ty pi c al miss ion, we have s t ud i ed t he u se o f t h e Sa t u rn V i nmanned plan eta ry ex plo rat ion mission s, employing a six-man sp ac ec ra ft , flown pas tth e p lane t Mars i n th e 1977 t ime per iod . Thi s miss ion involves ear t h o r b i tassembly of f ue le d S-IVB's wi th a spa ce cr af t whose desig n i s evolved from aManned O r b it a l Research Lab space s t a t i o n module and a n Apollo command modulewi th s ui ta bl e mid-course and ret ropro pulsio n added.

In th e miss ion envis ioned ( f i gur e 131 , th re e Sa turn V vehic l es l aunch fue ledS-IVB's in to ear th or b i t . The S - I n ' s a r e docked wi th a Support Orb i ta l Dock(SORD) which serves a s an o r b i t a l docking and checkout s t a t io n. The SORD pro-v ides forward acce le ra t io n fo r p rope l l an t se t t l i ng pr io r t o S-IVB venting . Themaneuvering of t h e S-IVB t o rendezvous i s accomplished by a je t t is on ab le cryogenics ta ge made up of hydrogen/oxygen p ro pe ll an t co nt ai ne rs and two RL-10 eng ine s( CUSS ) . After th e f i r s t S-IVB has ente red or b i t , th e CUSS i s removed and th efol lowing S-IVB's a r e launched and mated with t h e f i r s t . A fou r t h Sa t u rn Vl aunch p l aces t he m i ss ion spacec ra f t i n t o o r b i t . Thi s un i t i s maneuvered t orendezvous and dock by anothe r CUSS. Thus, t h e s ta ck assembled i n or b i t i scomposed of t h r e e S-IVB's, a miss ion module and a na vi ga tio n and pro pul sio nmodule. The hardware i n o r b i t i s shown i n f ig ur e 14 . The s p a ce c r af t i t s e l f i sshown i n f ig ur e 15.

It may be s een th a t t h e s pa ce cr af t i s composed of a probe room, from which Marsexperiments ar e launched during th e passage of t h e pla net , a co nt ro l room con-t a i n i n g a b io s h i e ld f o r p r o t e c ti o n a g ai n s t s o l a r f l a r e s d ur in g t r a n s i t , a c e n t r i f u g e


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TY PIC AL H lGH ENERGY MISSION EXAMPLESMISSIONCATECORY

PLANETARY PROBECOMET INTERCEPT

ASTEROIDSOLAR PROBEOUT-OF-THE-ECLIPTICOUT-OF-THE-SOLAR-SYSTEM

I 1 1 I I I IIT0 - INTERPLANETARY TARGET DISTANCE FROM THE SUN (A.U.)ITT - INTERPLANETARY TRANSIT TIME (DAYS)a INCLINATION OF THE FLIGHT PLANE TO THE ECL IPT K PLANE

AVAILABLE PAYLOAD (LBSI

LIBRATIONPOINT EXPLORATION

V- = HYPERBOLIC EXCESS VELOCITY =


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ELEMENTS OF THEMANNED MARS FLYBY PROGRAM

PRE-MISSION SUPPORT MISSION SUPPORT"

MISSION

FIGURE 135-1118-1596

ORBIT LAUNCH VEHICLE AND SUPPORT ELEMENTS

SORD CONCEPT( S U P P O R T I N GO R B I T A LD O C K )e

TY P lC A L(MOR L CONCEPT)

i RETROI ABORTPROP. MOD.A P O L L O C I M (6M A N )O R B I T A L T U G C U S S

FIGURE 14


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MISSION MODULE SPACECRAFT

ACCESS HATCH- r U X I L I A R Y A I R LO C KECLS COOLING

WRTABLE AIRLOCK GASEOUS OXYGEN & N ITR OGEN

APOLLO DOCKIWGCONE & CRBT ENTRANCE SOLAR CELL ARRAY

N A VIGA TION MOD U LE

i!

L K f / \1 E c L sA D IA TOR s - I v BISOTOPE H EA TIN GC I R C U I TLAB ECLS

EXPER IMEN T MOU N T1 N G B OOMSH M G A R E C L S A I RD ISTR IB U TIO N D U C T C ONTR OL MOMEN T GYR O

FIGURE 15

INTERPLANETARY MISSION PROFILE

FIGURE 16

19


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f o r p r od u ci ng p e r i o d i c g r a v i t y ex e r c i s e f o r e ach crewman d u r i n g f l i g h t , and anau x i l i a r y p r o p u l s i o n sys tem f o r p r o v i d in g mi d- co urse co r r ec t i o n s . The Apolloi t s e l f i s c a r r i e d w i th t h e s p ac e cr af t f o r e v en t ua l r e t u r n th ro ug h t h e e a r t h ' sa tmosphere . A r e t r o g r ad e m odule a t t a ch ed t o t h e A po ll o p r o vi d e s b r ak i ng i n t h ev i c i n i t y of t h e e a r t h . The m is si on i t s e l f i s d e p i ct ed i n f i g u r e 1 6 . F l i g h t t i m ei s approx imate ly 670 days . The s c i en t i f i c o b se r v a t i o n s a r e co nd uc ted t h ro u g ho u tt h e e n t i r e f l i g h t ; t h e most i n t e n s i v e pe r io d of I4ars exp l o ra t io n i s accompl ishedd u r i n g t h e s ev e r a l d ay s o f t w i l i g h t f l y b y . A f t e r p a s s i n g M ars , t h e sp ace c r a f tswings ou t toward th e as te ro id b e l t . The r ecovery sequence o f th e Apollo space-c r af t * i s s i m i l a r t o t h a t p lan ne d f o r t h e l u na r f l i g h t . I t i s s i gn i f i c an t t o n o tet h a t i n t h e 1977 t ime per i od , th e miss ion descr ib ed can be accompli shed wi thsp ac ec ra f t weig hts approaching 91,000 kg (200,000 pounds) . Through t h e in t ro -d u c t i o n of e a r t h o r b i t r end ezvo us t e ch n i q u es , S a t u r n V can p rov ide a verys i g n i f i c a n t co n t r i b u t i o n t o manned so l a r sy st em ex p l o r a t i o n .

The en ergy re qui rem ent s of a manned Mars l a n di n g a pp e ar t o r e q u i r e t h e u s e o fa n u c l ea r u pp er s t ag e . F or t h i s m i s s i o n , u p r a t ed Sa t u r n V f i r s t a nd s eco nds t a g es co ul d p l ace n u c l ea r s t ag e s i n o r b i t w hich co ul d b e a s semb led by t h et ech n i q u es o u t l i n e d f o r t h e Mars f l y b y m i s si o n . T hu s, t h e ex p e ri en ce g a i n ed i na ss em bli ng s t a g e s f o r t h e c he mic al f l y b y mi ss io n i s d i r e c t l y a p p l i c ab l e t o t h el an d i n g m i s s i o n .

LUNAR EXPLORATION

A f t e r t h e A po ll o l u n a r l a n d i n g i s completed follow-on programs w i l l u s e t h e S a t u r nA p ol lo ha rd ware t o i n i t i a t e an ex pan ded sur v ey o f o u r s a t e l l i t e . The moon o f f e r st h e promise t o man of t h e disc overy of t h e mechanism of human and pl an et ar yc r e a t i o n . I n t h e l u n a r s u b s o i l , we may f i n d samp le s o f p r o t o l i f e drawn fr om t h eea r l y ea r t h envi ronment. P ro fe ssor Urey has hypo thes ized , f o r example , ea r l yd ep o s i t i o n o n t h e moon o f w a te r fro m t h e e a r t h co n t a i n i n g p r i m i t i v e l i f e sp eci mens .Knowledge of t h e vol ca ni c o r non-volcanic na tu re of t h e moon may shed l i g h t onw he th er t h e moon o r i g i n a t e d fro m t h e e a r t h o r was cap t u r ed a s a p a s s i n g c e l e s t i a lbody.

The moon may ev en t u a l l y o f f e r a p l a t f or m f o r m anu f ac t u ri n g and r e se a r ch w hichc an no t b e e a s i l y a cc om pli sh ed on e a r t h o r i n e a r t h o r b i t . I n t h e r e s e a r c h a r e a ,


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fo r example , h igh vacuum on th e l un a r sur face co,uld p rove t o be be ne f i c i a l i nm a t e r i a l s r e s e a r c h , h e a t t r a n s f e r , t h i n f i l m t ec h no lo g y, w eld in g r e s e a r c h ,c o o l i ng a p p l i c a t i o n s , vacuum d i s t i l l a t i o n , s u p e r - co n d u c t iv i t y , e t c . The l u n a renvi ronment may o f f e r advantages t o spe c i a l i zed manufac tur ing p roc ess es , bu tt h e s e w i l l be co s t ly . For example, i t i s p o s s i b l e t o e n v i s io n m a nu f ac tu r in gand a ssembly of syst ems nea r abs o lu t e ze ro involv ing th in f i lm dep os i t i on ,vacuum welding, e t c . On th e backs ide of th e moon, l a rg e ra di o ast ronomyt e l e s c o p e s w ould be s h i e l d e d f ro m t h e r a d i o n o i s e o f t h e e a r t h , a n d , i f o n t h eda rk s i de , f rom the rm a l ag i t a t i o n . An op t i ca l t e l e sco pe of course would no tbe impeded by an a tmosphere and t h e low lu na r gr av i t y would permi t use of la rg eap e r t u r e s . S ince t h e moon ro t a t e s once pe r month ra t he r t han once pe r day , t h eprob lem of t r a ck in g i s much s imp l i f i e d i n bo th ra d i o and op t i ca l as tronomy. Themass of t h e moon i s g r e a t compared t o a n a r t i f i c i a l s a t e l l i t e . T h e r e fo r e , t h e s ed e l i c a t e s c i e n t i f i c i n s t a l l a t i o n s w ould n o t b e s u b je c te d t o a b e r r a t i o n s in du ce d

*b y m o ti on of t h e man i n p r o x im i ty t o t h e i n s t r u m e n t. E v e k t u a ll y a l u n a r s t a t i o ncould prov ide a long te rm ea r t h communica tion re la y po in t . Perhaps some dayt h e moon i t s e l f m i gh t p r o v e t o b e a d va nt ag e ou s a s a n i n t e r p l a n e t a r y l a u n c h in gs i t e .

With ex t ens ive use o f t h e Sa turn Apol10 ha rdware i n l un a r ex p lo ra t i on , one cane n v i s i o n new co n c ep t s w hich c an a d d a p p r e c i a b l y t o t h e u t i l i t y of t h i s u s e . Asl u n a r e x p l o r a t i o n p ro ce ed s t h e S a tu r n V v e h i c l e c an be u s ed t o d e l i v e r p ay lo a dst o l u n a r o r b i t and l au nc he d i n p a i r s t o d e l i v e r a s t r o na u t s .and s u p p li e s t o t h elu n ar su rf ac e. An unmanned, cargo -carry ing Sat ur n V , f o r example, cou ld l andalmost 13,600 kg ( 30 ,0 00 ~ o u n d s ) f s c i e n t i P i c a nd o p e r a t i o n a l e qu ip me nt f o rl a t e r u s e b y a s t r o n a u t s l a n d in g v i a LB4.

I n fo rm a ti on o n d e t a i l e d c h a r a c t e r i s t i c s o f t h e l u n a r s u r f a c e an d s u b su r f ac es t r u c t u r e s i s n eeded f o r t h e d e s ig n o f t h e equipment p l an ne d f o r t h e s e f u t u r eprograms. Surveyor has a l read y prov ided ce r t a in da t a on t h e l una r sur face andw i l l s u p pl y more i n t h e f u t u r e ; h o we ve r, i t s p ay lo ad c a p a b i l i t y p r e c l u d e sde l iv e r y of s i g n i f i ca n t se i smologica l equ ipment . Along wi th Surveyor , t h e LunarO r b i t e r w i l l p r o v i d e h i g h r e s o l u t i o n p h o to g r ap h i c d a t a on t h e l u n a r s u r f a c e .

Some da t a should be a va i l a b l e f rom both of t he se sys tems l a t e i n 1966. Althought h e Surveyor cannot de l i v er a heavyweight se i smic shock source and rec ord ing


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equipment, it could probably emplace a seismic recorde r by 1947, i f t h e shockgen era t ion i s assigned t o another system such as a spe nt Satu rn V/S-IVB st ag e,impac ting on t h e moon.

The Saturn V begins i t s f l ig h t program i n 1967 and w i l l e v e n t u a l l y d e l i v e r t h eApollo CSM and LM in to lu na r o r b i t . On such f l i g h ts , spent S-IVB sta ge s w i l ld r i f t i n t h e v i c i n i t y o f t h e moon and cou ld be d i r ec t e d and p rope l l ed so a s t oimpact th e moon t o c re a te a s i z ab le se i smic shock ( se e f ig ur e 1 7 ) . Normally,t h e s t a g e would ha ve be en a llo we d t o d r i f t i n t o s o l a r o r b i t o r r e t u r ne d t oea r t h by con t ro l l ed r e -en try .

If t h e s t age were t o i m pact t h e moon i n a s e l ec t e d a re a f o r shock r e g i s t r a t i o ni n a nearby Surveyor re co rd er , a moonquake of magnitude 3 on th e Rich te r Sca lewould be created. The impact cou ld be 160 km (100 m i l e s ) d i s t an t f rom t h ereco rde r and s t i l l p rovi de m eani ng fu l r e f r ac t i o n se i smi c da t a .

These da t a could prov ide in formation on th e cha ra c t e r i s t i cs o f th e lunar sub-st ru ct ur e t o depths of approximately 30 ki lome ters . Such inform at ion would beof g r ea t va lue t o th e development o f th e lun ar su bsurface s t ru c tu re models andthu s man's knowledge of i t s nature and hi s t or y. A s an a l t e r n a t e , if t h e e x p e r i -ment must be de layed un t i l a f t e r t h e Apollo l and ings on th e moon, th e se i smicrecorder cou ld be pos i t ioned on th e lunar sur fa ce i n an emplaced Lunar Sc ie n t i f i cS t a t i on , de l i ve re d and pos i t i oned by a LM a s t r o n a u t . A ls o, i n t h e e ve nt t h a ta L una r O rb i t e r i s i n ope ra t i on a t t h e t im e o f t h e S-IVB i m pac t, t h e s u r faced i s t u rbance cou ld a l so be pho t og raph i cal l y r eco rded and t r ansm i t t ed t o ea r t h .

The se ism ic shock provided by th e impacting S-IVB st ag e i s e q u iv a le n t t o t h eexplosion of t h i r te e n ton s of TNT. ' The energy i s produced by the impact of15,900 ki lograms of empty s tage weight t ra ve l in g a t a ve lo ci ty of 2 .56 ki lom etersper second. The explos ive po te n t i a l o f 368 ki lograms of poss ib le res id ua l pro-p e l l a n t s i s i n cl ud ed i n t h e i n di c at e d r e a c ti o n .

I n th e normal Apollo f l i g h t , t h e S-IVB pro pel s t h e Command, Se rv ice , and LunarExcurs ion Modules in to a t ran s lun ar t ra j e c t or y . Af ter t h e Apollo modulesse pa ra te from t h e S-IVB sta ge , t he y w i l l perform up t o th r ee mid-course ve loc i tyc o r r e c ti o n s t o i n s u r e a n o pt im al l u n a r o r b i t en t ry cor r idor approach . The Apollo


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SPE NT S-IVB STAGE AS A LUNAR SEIS MIC WAVE GENERATOR

FIGURE 17


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modules, th e r e f o r e , move ahead and away from t h e S-IVB st ag e, lea vi ng i t t o bed i sposed by some deb r i s c on t r o l ope ra t i o n .

I n o r d e r t o g u id e t h e s p e n t S-IVB s t a g e i n t o a lu n a r - i m p a ct , a n i n i t i a l r e t r oth ru s t o f about 10 1 / 2 me ter s pe r second must be i n corp ora t e d , fo ll owed bys e v e r a l m id -c ou rs e c o r r e c t i on s w i t h t h e no rm al s t a ge a u x i l i a r y p r opu l s i on s y s te munde r t h e c on t r o l o f t h e I n s t r um e n ta t i on U n i t . I n t h i s mode o f ope r a t i on , t h eS-IVB stage w i l l impac t on t he l u na r sur fac e a lmos t s im ul t aneous ly wi th t h elu na r o r b i t c i rc u l a r i z a t i o n impulse ope ra t i o n of t h e Command, S e rv i ce , and Luna rExcursion Modules on th e -backside of th e moon. I t may, t h e r e f o r e , be pos s i b l et o v iew o r photograph th e su r face d i s tu rba nce f rom t h e CSM/LM, s i n c e t h e y p a s sove r t h e i m pa ct a r e a w i t h i n a n hour a f t e r i mpac t.

Thus t h e S a t u r n l a unc h ve h i c l e de s igne d f o r a pa r t i c u l a r m i s s i on , w i l l haveu t i l i t y f a r b ey on d t h a t i n i t i a l l y a n t i c i p a t e d . The trem en do us power a ndv e r s a t i l i t y of t h e s e s ys te ms w i l l pe r m it t h e pu r s u i t o f a dva nc ed goa l s i n t h eexpl ora t i o n of space us ing av a i l ab l e re sou rces t o a maximum ext en t . The scopeo f t h e s e f u t u r e us es w i l l e x te n d fro m u t i l i z a t i o n of s p e nt s t ages t h rough Marsf ly by mi ss ions and w i l l encompass t h e so la r sys tem. Douglas Mi ss i le and SpaceS ys te ms D i v i s i on i s p l e a s e d t o p l a y a p a r t i n t h e a dvancem en t o f w orl d s c i e nc e ,t h r ough s pa c e e xp l o r a t i on .

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Extensions of Saturn