flight results and experiences with the s-iv stage of the saturn i

8/4/2019 Flight Results and Experiences With the S-IV Stage of the Saturn I

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ENGINEERING PAPER

SPTtJRN HiSTORY DOCUMENTUniversity of Alabama Resea~chnstit*History of Science L. Technology GroupDate---- ----- DOC. O. - - - - - c ~

F L I G H T R E S U L T S A N D E X P L R l E N C E SU71TWT H E S - I V S T A G E O F T H E S A T Q R N I

P R E P A R E 5 B Y :LIJDLLl'iGROTI-tM I S S ! L E A N 5 S P A C E S '. 'S TE US D i V l S l O N

S ' J A C E S V S T E M S CSN T E 9D O U G L A S A ! R C R 4 F ? C O M P A N Y . INC.


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FL IGT SES9ZfS 2 i D EXPERIE:;CESr/1TTH Ti-? -F J STAGE OF ' i i SATLEZl I

Tir ee y ear s ago a t your annuctl meet ing a t Xoblenz my colleague, Ifx. T . J .Gorfion, to ld you about our p lans wi th the S-IV s tage of t h e S a t u r n Isystem. A t that t ime he gave you an ou t l i ne of our ideas , our ca lcu la -t ion s , our des igns and th e expec ta t ions w e h ad f o r t h e f u t u r e . ? 'h is Ist5 e per io d of development which eve ry engineer l ove s most; because it i sa t t h i s t h e he can l e t h i s c r e a t i v e rnind g o u n r e s t r i c t e d . S in ce t h e nwe ha-re gone through thre e years of "blood, sweat and te ar s" aod hea zt-x~ rm in g uccesses . Our f i r s t t r ue space baby, the S-IV s tage , has reachednarihood and has l iv ed up t o a l l of our promises and expe ctat ion s. Todayit i s my p l e a s u r e t o r e p o r t t o you ab ou t o u r x or k, o u r e x ~ e r i e n c e s , and,about th e s uccesse s we have had with th e Sat urn veh ic le .

We ar e very proud of t h e pr oj ec t rihich has been so success17ul. It i s asi gn if ic an t s t ep clos er t o the :core ambit ious grograms i n ?:hi& we ar enoT< eng age d. I am very hsppy t o be a ble t o show you a t t he end of nyspeech a most unique f i L r of tk e se par at io n of th e S-IV from th e S-I ;th e separ,-.tion of t he skroud woun8. th e Pegasus and t h e u n f o l ~ i n g f t h ePegzsus senso-- sa re ls i n f i i g h t . Tnanks t o the gen eros i ty of NASA, youi ~ r i l : p r t i c i p t e i n t h i s i n t er e s ti n g sFace o pe ra ti on . The p i c t u r e s ofth e 2eplojmonz of th e Pegssus were taken by te l ev is i on cm er as nountedon t!-e S-IV and t e l e n e t e r e d t o t h e g ro un d s t a t i o n a t A nt ig u a.


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2 . DESCIIIPTIO:; OF STAGE

F or t h e b e n e f i t o f t h e p o p l e wr?o d i d n o t h e a r r l r . . Cc:.dcnts paser, permitfie t o repea t a few gener a l renarks about the S a tur :~ Froqra~i . The presen tS a t ur n f z x i l y o f b i g s c a ce b c o s t e r s c on si st :: o f t h r e e d i s t i n c t c o n f i g ur a -t i o n s ( F i g . 1 ) : t h e S a t n r n I, t h e S a t u r n I 3 and the Saturn V . The Saturn Ic o n s i s t s o f t h e f i r s t s t a e e S - I an d +,he s ec on d s t% ze S-I71 (3'ig. 2 ) . Orig-in a l ly pia naed ris a c;z50r space boos ter, i t i s now being used for providingf l i g h t d aza t o s tu dy a d ve r i f y des ign concepts and subsys tem fo r theSa turn I!? and Saturn V; o f p r t i c u l z r b - p r t a n c e was t h e r es ea rc !l a nd d ev el op -Eent o f t he l iq u i d hydrogen (m2) and l iquid oxygen (LOX) s y s t e m . Theprogress of t3 e prograT was so succ ?srr 'u i th at it -.,as p s s i b l e t o u se t h e l a s tt h r e e t e s t v e 3 i c le s f o r c a r r y i n g s r z c e e x y e r i ie n t s , i n t h i s g z e t i c u l a r c as e,t h e P e ga su s e x p e r b e n t .

The Satrrn I 3 c o n s i s t s o f t k e f i r s t s t a g e S-IB a n d t h e s ec on d s t z g e S-IVB.3 ) . The Saturn IB mission i s b a s i c a l l y t o i n j e c t a s i x t e en t o n p ay lo ad

i n t o e a r t h o r b i t . The s p e c i d and p ri ma ry m is s io n i s t o l au n ch t h e t h r e e -~rirneciA po ll o s p a c e c r a f t i n t o o r b i t . V i t a l i n fo r m a ti o n w i l l be ga thered wi tht h e s e P . p l l o l a u nc k i ng s b e f o r e t h e f i n a l a t t a c k o n t h e n oon i s s t a r t e d . S a v -ing of t i m e and cos t s were ach ieved wi th th e i n s e r t i o n o f t h e S e t u rn I B i t l t othe Frogran . In add i t ion , a very capable and ve rs a t i l e boos te r system fo rgene ra l use was es ta b l i she d .

The Saturn V b o o s t e r ( ~ i ~ .), t h e f i n a l o p e r a t i o n a l A co l lo -2 oo st er , c o n s i s t s ,or" t h e S-IC, the S-I1 znd the S-ITB. It i s d ev el op ed p r k 2 - r i l y t o c a r r y t h eA ~ i l o ~ a c e c r s f t n i t s l u n w m ission. It w i l l be r;ke nost p7t;eyful boosteri n th e Wesizer~lk-orld for z long t h e t o cone.


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SATURN FAMILY

PAYLOAD(CO NF B)

1

SATURN 1 SATURN IB SATURN IB(BLOCK II) (2 STAGE) (3 STAGE) SATURN V


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SATURN I


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t n t

SABU W N I B SAT UR N OB


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These in tro duc tor y rexarks shocl i? give you a good fee l i ng of th e plac e theSa turn fa~lf r s i n t h e A p l l o 5 rogra.n.

5 e f o r e I ?resen t t'ne e x pe r i e~ ce s e have ga thered -A+,!! he S-TJ, l e t nei T t ro c F ~ ce ou t o s o ne o f t h e d e t a i l s o f t h e S - I 7 d e s i g n . This s l i d e ( F i g . 5)shows you a p i c t l ~ r e f t h e s t a g e a i% er c o a p l e t i o n an d r e ad y t o b e n a t e d t ot h e f i r s t s t ag e. rile ne xt p ic tu re ( ~ i g . ) shows you the in te rn a l a r range-ments s t a r t i ng wi th th e c on ta i ners which a t th e same t ime se-rve as t he ou te rwzl l s . The engine systems a r e enc losed by a shroud, a ~ d , he fo rward sk i r tse rves as connec ting f ra ne fo r th e ins t rument un i t and pay load . The v i t a ls t a t i s t i c s o f t h e S -IV a r e sho>;n i n F i g . 7 .

The bas i c e lement o f th e S-IV s t ru c tu re i s th e con ta iner assembly ( F ig . 8) .To save weight and vo lm e, th e U1 an d LO:: a n k s a r e a s i n g l e u n i t , s e p a r a t ed2by a coxm,on bulkhead which a l s o se rv es a s an i n s u l a t i o n b a r r i e r b e tw ee n t h etwo gro pe l lan ts . Th is i s n e c es s sr y t o av oi d t h e s o l i d i f i c a t i o n o f LOX vrhichw o ~ l d c c u ~ f t h e b ul kh ea d r e zc k es t h e t e m p er at u re o f t h e LY To s t a b i l i z e2'the con ta iner w al l a ga ins t compressive loads caused by long i tud ina l loads andb cn di ng nc me nts, i n t e r n a l s t i f f e n e r s i n a w e f f l e p a t t e r n a r e u s e d. Thee n gi ne s a r e m ounted t o a t h r u s t f r ~ z e hich c o n ne ct s t o t h e a f t b ul kh ea d o f-t h e LOX c o n t a i n er . The a f t s k i r t aa d t h e a f t l n t e r s t a g e n o t o n ly p r o t e c tt h e e n gi n e assem %ly-, b u t a l s o c a r r y t h e l o a d s 'so t h e i n t e r f a c e w i t h t h e f i r s ts t a g e . The a f t i n t e r s t a g e c on t a i n s blo1:-out p m e l s f o r r e l i e f o f t h e c h i l l -c?om g a s e s . The c c n i c a l f c r w a r3 i n t e r s t z g e c o nn e ct s t h e i n s t r a ~ e n t n i t w it hth e sta ge 23d c a rr ie s t h e ~ a y i o s d . Bonde3 al.u-7linum honeycomb i s beirig used fors k i r t s and i n t e r s ta g e s . I a l s o :.;ant t o me ntio n t h e h e a t s h i e l d w hich r o t e c t sth e for wird are a from hea t of t ke er:gine exhaust .


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S-IV STAGE PRODUCTION


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S-IV STAGE CUTAWAY


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V STAGE a V TAB. STATGN VALUES

OVERALL LEN GTH 41.0 FT.

OVER ALL DIAMETER 18.3 FT.30Ca7rn FORW ARD SKI RT

LENGTH 130 IN.DIAMETER 154 IN.

TANK SECTIONS LH2LENGTH 260 IN.D!AME TER 220 IN.

LOX126 IN.200 IN.

LH2 TAN K-VO LUM E 4300 CU. FT.

LOX TAN K-VO LUME 1300 CU. FT.

DRY WE IGHT 14,000 LBS.

TAKE-OFF WEIGHT 140,000 LBS.

THRUST 90,000 LBS.II BURN TIME 490 SEC.


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SATURN S- V STAGE INBOARD PROF

f- FT BULKHEADL!Q QXY.7(4) ULLAGE ROCKETS7

(2) RETRO-ROCKETS

COMMONJ /- ENGINESBULKHEAD SEPARATIONPLANE

HEAT

'""'"7

wAFT END VIEW


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Tp-e p r o p l s i o n sjrsten; of th e S -TJ u s es s i x W a t t Zc h ii tn e y kLlCA-3 rock etengices ( ~ i ~ .) . Each engine develops 15,000 ~ o u n d s f thxist a t a l t i t u de .The prope l lan ts a re U{ ar?d LOX. The g b . b a l m n t e c i e ng i ne s a r e n o t t o be2r e s t a r t e d . T hi s f e a t u r e xi11 h e u s e 3 o n ly i n t h e second genere t ion of theS-TV s t a g e s , t h e S - I V ~ / Y . The t:nLzst cha?l'cer i s o f tu bu la r c on st ru ct io n 'vrithr e g e n e r a t i v e c o o l i n g . X e li un i s u se d a s ~ r e s s u r a n t o r t ? e o pj ge n c o n t ai n erand th e con tr ol devices. The hydrcgen pump 2nd t'ile oxygen ~ u ~ pr e e n e r g i z e 4by a hydrogen-driven tu rb in e. It i s i s t e r e s t i n g t o n ot e t h a t t h e e n gi ne s a r ed e si gn e d f o r o p e r a ti o n a t hi g h a l t i t u d e s and ha d t o be t e s t e d a t s i m l a t e da l t i t u d e s o f b0,000 t o 6 0,0 00 f e e t . 'i"nis r e q u i r e d i n s t a l l a t i o n of d i f f u s e r

m d e x h au s t d u c ts f o r a l l h ot s t a t i c f i r i n g s . The e lec t r ica l sys tem or ' theS-TV provides AC and DC FoTi:er to the s tage th rough fo ur se>ara te ba t t e r ie s .Two 28 v o l t 1 5 A! b a t t e r i e s a n d t w o 28 v o l t 5 AY b z t t e r i e s & r e b e i ng u s e d .Zinc-s i lver ox ide a d t a s s i u m ydroxide ::ere s e l e c t e d a s t i l e e l e c t r o 7 y t e s .T h e b a t t e r i e s a r e s e a l e d a n d t h e r r ? o s t e t i c a l l y c o n t r o l l e d .

Guidance inp ut s f o r tk e st ag e ar e recei ved f ro n t'fie Instr3mer.t Unit corn-~ u t e rhrough a hard-di re t ru nkl ine t o th e s tzge s e l ec to r swi tch (l?ig. 10) .Each en gi ne i s g i ~ b a l l e d j t 0 hydrau l ic ac tua tors i r . a degree pa t te rn .P eak e ~ g i n e o os it io n r e t e i s i 5 degrees/second.

To obtain , ~ L ? X ~ ~ L Tl ig ' r t px-fornance, i t :.res e ss e n ti a l xo zrov ide e systemf o r p r o ~ e l l a n t o ad in g m3.d e p l e t i o n . !Illis system us es ca pa ci ta nc e Tiassse ns in g >rob es f c r bo th th e 0-xyger. end 'i+rdrogen ta nk s. A y r o p l l : m t u t i l i -z a ti o n e l e c t r on i c s a s s e ~ b l y e c e iv e s t h e xe ss p rc be o u t y ~ t s nd t a i l o r s t h eo x id i z er c o n s u ~ y t i o : ~r' the engines t 'nrougll the rilicure r a t i o c on tr ol v , ~ l - ~ ~ e .In t h i s r m n e r , t he c r o ~ l l a n t s re d e ~~ l. et .e do l e ss than 3 .5 percent of t i i ei n i t i a l l oa di ng .


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OMTROLFORWARD


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The S-FI tel ez et ry syste n nees 'ures, gathers, arid t rsan s~ii ts l i g h t Fnstru-nen tat ion data. Accelerat icn, force, not ion, pressure, s t ra in, temperature,v i b r a t i on an d t h e w e n t f un cti on s, e tc ., a r e p a r a ~ e t e r s e n t t o t h e grounds t a t i o n s . ?,:o bas ic types of t e l e ~ e t r y re used - R.:/F!~ and ?~I.!/FI~:/FI.I.Tflree different systexi t rkrsxi t awroxina. te1.y ~ G G zta chancels . The f l ightd a t a s ys te m i s a u p e n t e d f o r g r o md t e s t i n g b y a d d i ti o n al h a r & ~ ~ i r eeasure-merits. Tota l s ta t i c f i r i ng in s t m ~ en ta t i o n pprcaches 1 ,000 charnels .

The hy&aulic syste n provides engine gimball ing fo r s tage at t i t ud e contro l .Rajor compnents of t he hydrzulfc sy s t e i ~ re an engine-driven hydraulicpx-np, ~otor-drivenau xi lia ry hydraulic pu-p, and two act ua tor assembliesfo r each engine. Tlie e figine-driven pmp opera tes a t 3,450 ~ s ind i sdriven off the turbopmp accessory drive . Tne aux i l ia ry rprp oge rat e s a t2,950 ps i , a d s use.? t o g i ~ b a l ngi nes du r ing checkout and t o cha rgezhe h y rh a ul ic a c c w l a t o r p r i o r t o l i f t o f f . The e ng ic e a c t ua t o rs a r el inear , double-act ing, equal-piston-displacenent uni t s .

iiiow l e t ne resent some of t he sr;er-ial developnent ta sk s we had t o p r -f o r= s i n c e t he y r e pr es e nt t h e t b ~ i c a l t e p ~ i n g t o ne s f o r f u t u r ? d ev elo p-ments. In the s t ru c t ur a l f i e ld , one of the b igges t chal lenges jras th edesign of an in teg ra ted cont il iner f or LOX & ~ dCp ( E g . 1 1) . 'rle not ori1y

-0had t o de al wizh a tempereture of -253 C ( t5 e t o i l i r g saint for hyjrcgen)

end i t s n f f ec t on r r at e ri a ls , bu t a l so ;,rith t he t ex ~e ra t u r e i l f e r en t i a l0 0bet-,t7een-253 C and -183 C ( t he bo i l i ng p i n t o f oxygen) md tke dif i 'erence

between t t e s e t e n ~ ~ e r a t u ~ e snd t h e a b i e n t t e n p r z s u r e m d i.;: Ln.fl.>ence


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S-IVB STAGE PROPELLANT TANK TEMPERATURESAT FIRST STAGE BURNOUT


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on t h e b o i l o f f r a t e s . 2014 T-6 ~ ~ U Y L E ~ J-Qq2s se l ec t e3 as th e mi t e r i a lbeczuse of i t s good perfornance a t lo.,i ten ~e ra tu re s , and, because o f ourf a ~ L l i x i t yritli t h i s ~ ~ t e r i a ln e a r l i e r ~ r o ; e c t s i k e t h e Thor. We a l s ohad ex tensive exper ience x i th LCX from th e d ev e lo p -ent o f b a l l i s t i cm i s s i l e s . There we Lad lez rne d t o hvld le t he cryogenic Liquid ivithoutsp e c ia l i n s u la t io n y e t k eep th e b o i lo f f l o s ses w i th ir , 2 ccep t sble l imi ts .With I.B2 en te r ing the p lc tu re a cmple te ly new env irom-en t has es t zb l ishe d .Boilof f r a t e s ti it ho ut i n s d at io n becane unacceptably high. A v eryin t e r es t in g s tu dy of th e a i iv an tq es and d isad van tag es o f i n t e rn a l o rex te rn al i ns ul at io n had t o be conducted. The 7_eroblen was so complex th a tt h e i n d i v i d u a l n i s s i o n o f a p a t i c u l a r s t a g e became t h e c r i t e r i o n f o r t h ese?,ection. Tnis was dezonstr ated very viv idl y by choosing exte rna l insu-L e t i ol f o r t h e S - I 1 and i n t e r n a l i n s u l a t i o n f o r t h e S-TV ( ~ i ~ .2 ) . Ofi n t e r e s t i s t ha t, t h e i n s ~ d a t i o n o n s i s t s o f 1 /2 t o 3 / L o f an in ch o f p l y -u rethane foam wiiich i s i n form of t i l e s g lued t o th e i riner wal l o f the hydrogenco n ta in e r . A l zy e r o f l i k e rg la ss c lo t h p rev ent s th e fu e l fr crn seegin g in to th ef o ~ ? . ome of t h e b e n e f i t s of' t h e i n t e r i o r i n s u l a t i o n a r e : more c o n t i n ~ o u sin su l s. t io n ( l e s s h ea t l eak s ) , b on ding mate r i a l t e~ y e ra tu re lo se r t o n o rn al ;lower hy5rogen lo ss duri ng ckiildo-,,?I of tile con tai ner i.:bich is , f or th e S-TV,only l/&f t h e slnount a s zeed ed fo r th e ex te r io r in su lz t io n (~ ~ ~ ro x i . . : a t e lyone t a ~ ki l l i n g ) ; l e s s c!:ange f o r dz x ge during handling, et c. There areobviously some disadvantages connected with interior insulation such ascontzv5nation of t he f i e 1 b y c h i ~ z e d n s u la t i o n, no? u s in g t h e i n cr e as e daz k e r i a l g e r fo rz ~ r i ce t lo;.;er t e x ~ ~ e ra tu re ,t c . One of t h e 3a jo r prablemsin th e develogx?n t o f such larg e l ig h t weigh t con ta ine rs i s i n t h e s i z ei t s e l f , &:ore Lngenuity was req7-1ired i n des ign ing t 5 e f' ixtu res an3 to o l sf o r ~ a u f e c t u r i n g h a n Tor t h e de s ig n o f t h e t ~ n kt se lL ' . As an exan2ieJ


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m t i q g o f t 'ne c y l i n d r i c a l s h e l l t o t h e d o ~ e s o ul d b e done o nl y i n t h ev e r t i c a l p o s i ti o n. The accuracy of the se high st re ss ed structiuxes had t ob e ve r y ex a c t t o 2 vo id l o c a l s t r e s s r i s e r .

Eecause o f the low dens i ty o f the tydrogen/oxygen p r o ~ e l l a n t o~b ina t io n ,a r_ininm-volurne ta nk arran gez ent i s necessary t o reduce t ine ta nk weight.A cy l in dr i ca l tank wi th hemispher ical dones was se lec ted as the noste f f i c i e n t a rr a ng ex e nt . This required development of a coTrmon bulkheail(I?ig. 13) :.ihich, f o r eas e of manufacturing and to oli ng, was th e sane shapeas t h e f ~ r ~ i a r dd a f t d o ~ e s . Tnis hemispherical segment, of alurninumhoceyconib sa n& ~i ch onstruct'on, se par at es th e oxygen and hydrogen. Thef ib erg las s hexagonal honeycod i s bonded t o th e 2014 T-6 aluminum face. Thed es ig n i s co n se rv z t ive and p rov ides su f f i c i e n t b end in g s t i f fn e ss t o accon -;.lodate f u l l reverse p re ssure f o r th e cond i t ion o f f i l l 1 hydrogen t m k pressureand a vented oxygen tank. Large thermal s t r es se s m s t a ls o be accormodateddur ing p ropei la n t load ing . Close-to lerance fa br i ca t io n techn iques wered ev elop ?d which p r d u c ed a so g h i s t i c a t ed s t ru c tu r a l co n f ig u ra t io n u i thh igk r e l i e 3 i l i t y . The o nl y l a rg e s t r u c t u r e d i r e c t l y e x p s e d t o l i q u i dhycLrogen i s t h e comnon bulkhe ad. Over 400 fe et of welding i s req uire d onth e buikhead. E:;tremely high qua li ty co nt ro l measures were require d, and,t o a la rge Cegrce, had t o be developed. The bulKcead hes ~erl"orn.eds a t i s -f a c t o r i l y in a l l of i t s f l i g h t e xy er in en ts .

The c koice t o use bonded al:~micw~oneyconb d id no5 t u r n ou t t o be t he3e st one. The combination o f no ise f requencies f r o3 the ecg ines a dtherc la l s t r es se s ca wed f requen t debonding . B J ~o i n t e r fe ren ce w i ththe f l igh t yererfo r~ancewa.s exrer ienced .


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BONDING OF COMMON BULKHEAD


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I have shoi;n i r , zj7 i r s t ~ ; i ct ~ u z ~eh s t t h e S - N a nd S-T?3 are a lxays thelas ; powered s t q e s and , as such, have the s m e t rede-of f f ac tor s as the~ a y l o a d . P r o ~ e l i a n t o ad in g a d r o p l l a n t insu la t ion becomes, there fore ,a d e c is i v e f e c t o r f o r r l i s s i ~ n c co n -r ,l is hr ,e ~t . D c u g l ~ s as d e v e l o ~ e dP r o r e l l a n t U t i l i z a t i o n (PU) systerr. ( ~ i g . 4) f o r c ryoge ni c l i qu i d s whichhas Sroven accuracies of bet ter than 0.5$. The syst en uses nass-sensing i nth e Ycrm of cap ei ta nc e sensors , and, an onboard c o z p t e r fo r con trol . Aca li br at io n sys ten was develosed, :+rhich in sur es t'ne requi red a ccur acie s fo rloa , iing as wel l as cons c~ pt i on ont ro l . Proble,m i n the feeding systemof th e hydxxogen which were ex ~ e ri en ce d uring tk e Centaur develo prent ;.rereovercoze by us ing vacuun jacke ted l in es but s t i l l the problem of s t ra t i f i -c a t i on had t o be so l ve d . S t r a t i f i c a t i on = ems t ha t t he t e xpe r a t u r e o f t heIhi2 i s not uniform but r iarmer and colder l aye rs e xi s t . To avoid pumpc z v i t a t i on arid o t he r d i f f i c u l t i e s , a s t e p p re s s u r i z a t i on s yst em i s us ed a tul i nt er ne 3i at e ~ o i n t n f l i g h t .

Jxot5er >ro-DlerI, t he Pogo e ff ec t, which p l ~ ~ e dhe Thor and Ti tan projectwas ?l ot e xper ie nce d i n t he S a t ~ r n f l i g h t s .

Orle na jor p r~ t~ le rnrose, :.&en it became obvious during the engine de-relop-ment t h at a t3n-ust of 20,000 pc7~1ds per w i n e (80,000 f o r ?L engines)ccd ld not 5e achieved. Sorle chm ges in t'ke cayload nade it al so aclvisa3let o increase th e t o t a l th -mst t o 90,000 pounds u d he r e f o r e 6 e ~ g i n e s adt o be u se d.

P s Far back as in t he Viking v ld t he C or pr a l devcloprren t i n th - . l a t e LO'Swe had euser ienced d if f i cu l t ie s 35t h base he.:t ing. Fi e cla ste red enginesof t l -e S-IV s t ~ 4 e ere e xg ec~ ej . o c rea te t ine sar e rzoblens d7ue t o t i le


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SATURN S- \I PROPELLANT UT ON SYSTEMLOADING 2% T E L EM E T R Y


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in t era ct i on of the eng ine exhaust p lumes a t high a l t i tu des . Ex tensiveth eo re t i ca l ca l cu la t ions and model te s ts were conducted and f i na l l y a heatsh ie ld develo-pea which so lved t'ce problem ( ~ i ~ .5 ).

In g en era l it, can be stated that, our very thorough Deve1ope.n.t an6 @al/T es t F ro g ra? h as n inimized ac t u a l f l i g h t p ro b lem.

4. DEVEMF?~~TTSD Q.VAL/TEST STATISTICS

I b e l i ev e it w i l l be of i n t e r e s t t o you t o u n d e r s t ~ ~ dhe scope accl thee f fo r t n ecessa ry t o d ev elop a l a rg e r e l i ab le b o o ste r, md , I sb-al l putemphasis on th e work "rel iab le ." Xost equ ip en t used in a rocket canbe increased i n re l i a b i l i ty by us ing redundancy . Obviously th i s i s ou to f th e q u es t ion fo r th e l a rg e su bsys tems , b u t s t i l l i n th e S-IV we havesome measure o f in creased re l i ab i l i t y in th e c lu s t e r o f s ix en g i ~ es .B as ica l ly th e app ro ach to h ig h r e l i a3 i l i t y i s t o use a v ery s t ro n gd e t a i l e d aid i iel l-exe rcised devel-opzent and &ur zl/~ est rogrm ( r i g . 16).As the nave implies, a developen ' ; t e s t i s used t o prove the basi c design ofcorrFonents/sub-assenblies or t o determine improved ~erfo rm ance o r r e l i -

ab i l i ty , whichever i s the more des i red . After t h i s ~ h a s e s conclLuded,t h e co",paents/sub-assemblies go t:hrough a qu ali f ic ati on t e s t beforeproduction brawings and s,-ecificat5ons a re fi na li ze d ar,d rele ase d t or m u f a z t u r i n g . !?%is develo-men'; and & u a l / ~ e s z r o g r m consL,itutes actuzlly.a largo - p r t i o n o f t h e e f f o r t s o f t h e o v e r a l l d e v e l o~ . e r ; tgrografi.Let rie give you an ex a ~ p i e y skoxing you the st zx is t i cs of th e S - N(3'ig. 17). Zooking a t these fig ure s i t becones obvlous rihy our s p c ep :-~gr i .~s r e so conplex and co st ly i n both money a d he. For exasley


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S-IV COMPONENT TESTING CATEGORIES

RESEARCH - TO IDENTIF Y NEW MATERIALS OR PROCESSES0 DESIGN DEVELOPMENT - ADVA NCED COMPONENTS, CO NFIGUR ATIONS , OR,

CONCEPTS

4 QUALIFICATION TESTING - VERl FY OPERATION O F PRODUCTION COMPO NENTSIN SIMULATED FLIGHT ENVIRONME NTS

0 RELIABILITY VERIFICATION - STATISTICAL SAMP LING TO VERl FY PERFORMANCEADEQUACY

0 PRODUCTION ACCEPTANCE - VERIFYING ACCEPTABILITY FOR END ITEM USE

FORMAL QUAL IFICATION - EXTENSIVE PRODUCTiON COMPONENTS TESTING TODETERMINE MANUFACTURING REPRODUCIBILITY


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S-IV DEVELOPMENT AND QUALlFlCATTEST PROGRAM

TOTAL NUMBER OF DEVELOPMENT TESTS

TOTAL NUMBER OF QUALIFICATION TESTS

TOTAL TEST PROGRAM

NUMBER

180

HOURS


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look a t th e number of t e s t s involved. We have t o a s sme tka t a ce r t a i rl~e rc en ta ge , maybe 50$ or rtore, w i l l not succeed dur ing t he f i r s t t e s t and?my we ll have t o go through a s er ie s of t e s t s befo re we can be assured th a tth e pro duction i t e m 1ci.11 ope rate a s designed. One can a g u e tha t s in cesuch ca re f i l invest igat io ns zrld :roof had not been pr fo m~ ec iw i t h e a r l i e rrA ss il e s and ve hi cl es , why do we do i t now? One irnnprtant reas on i s t h a tour large space boosters and the i r p yl oa ds represent a much large r ef ro r tthan ever before. That means a failure i s not only f i n an c i a lu , bu t a l s ot im*wise, a much heav ier los s. You h o w th a t we have fo r many of our mis-s i l e s a ve ry l imi t ed t ime i n which t o l aunch i n o rde r t o conp le t e t hemiss ion successful ly . One misfire might s e t us back one or more yea rs.It i s f or the se reasons th at we er e conp2l led to increase th e requirementsfo r re l i ab i l i t y more and more. Tr'my p o p l e have ar,gued d 3u ia g t h e l a s tdecade th a t we ar e hold ing of f pro gres s with our s t r i c t delr.pmds, bu t looka t t h e r e s u l ts . The ~hor/Deltamiss i le , which i s being b ui l t by c y coz~pany,th e Douglas ALrcraft Conparv, has re ce nt ly p rfc rm ed th e 321d consecutivelaimc:? without a f a il u re . The Saturn I in a qui te spectacular perfornance,has launched 9 vehicles wi th 9 successes ( 5 of the se veh icl es were launched~ 5 t hh e Do-a las S-FJ s ta ge ), and we hope we can f i n i s h t3e prog rvn nex tlrontn with another successf'ul la s t lauqciling. Tnese ar e tine res u l t s of a gooddesign and a sup erior t e s t program. It rnxight be of ir -te re st t o look a t somed e ta i l e d f i g a r e s ( ~ i ~ .8) . Conparing, f o r exi!,m,ple, t h e nun'aer of t e s t s con-nected k%th th e di ffe re nt subsystems. It i s t o some degree a mirror of thedevslop ent prob lens we had; but it a l s c in d ic a te s t h e c o l ~ ~ l e x i t yf t he:prt icular subsystens. Outstan3ing exm~=,les i-e the el e at r i ca l cornpnentsand subsysteras ~L:nosec i e ~ e l o ~ e n tequi red 4~: of a l l t e s t s . Experi ence has


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V DEVELOPMENT ANDON TEST PROGRAM

@ ELECTRICAL 40 %

@ PROPULSION 30 %

MECHANICAL I8 %

@ STRUCTURAL 12 %

TOTAL PROGRAM 100 %


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shown th a t nost of th e problems occurr ing auring ac tu al operat ion =e con-n ec te d wi th e l e c t r i c a l f a i l u r e s . A very important aspect of the Frogruni s the involvenent of a v e q lar ge nuqber of vendors, a l l of whom had t ounderstand tl le phi losopi iy of z erfec t ion and re l i a b i l i t y %fnichhad 20 beapplied t o our pro jec t . To give you a fee l in g of the extent of ,w-rt icipa-t l on , l e t me ent ti on t h a t we engaged a force of 2200 vendors who supplieda~ pr ox im at el y 6% of th e 72,OC.O com pne nts th e S-IV cons i s t s o f . Includedi n th i s f igure , na tura l ly , i s the engine suppl ier , even though they de l iveredth e engines through t he Government t o us. The vendors part icipated also int h e ~ a l / ~ e s trogram bu t t o a le ss er degree. Of the 715 t e s t s performed,528 were conducted by Gagias zzd 187 or 26% by t h e v endo r. m o s t 60$ ofa l l ~ u a l / l e s t i n ~a i l e d d u ri ng t'ne f i r s t t e s t and a s t i l l si z e ab l e n a ~ b e rhad t o be perforned repeatedly.

5 . FLI,3I;T TEST RESULTS

As you h.or.r, the in s ta l la t io ns for i aunching such giant space boos ters havet o be, by necess i ty , l h i t e d i n nunbe rs ; and r equ ir e , t he re fo re , c a r e msche&uli ng. Th is s ch ee ~ l e s f t r r l y f i xed ea r l y i n t'ne deve lopen t, s t agesof such a vehicle. Since these vehic les requi re e de t a i l e d checkout a t t hefa ct or y and, again st t he t e s t s i t e where t hey a r e zccep tance f i r ed f o r t hef u l l durat ior?, Development and Qua lif ica t ion Test ing has t o s t a r t my nonthsb e fo r e t h e f l i g h t . Tne f l i g h t t e s t i t s e l f i s t h e f i n a l p ro of t h a t e ve ry th in ghad been done wi thi n th e lii-xits given by th e desiser and th a t +,he b a si cdes ign i t s e l f was cor re c t . We have f l ig ht t es ted tyke S-IV st-e f k e t i n e snow zz?d have had fi v e Fa11 suc ce sse s. Here ar e some of th e r z s u l t s .


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Trernendo~s mLounts of r:easurexents a r e conducted x ~ dele:?etered t o theground as shown in F i g x e 19. iiow l e t ne give you r, condensed rundo'mof t he r e su l t s c f t he d i f f e r en t f l i g h t s (F 'ig. 20). On 29 J m u q 1564,the f i r s t Sa turn vehic le (SA-5) s tage , uFan corple tior , of a nof in a l f i r s ts tage f l i gh t , indectecl r ,pproxinatel j 38,000 ~o mc ?s n to or bi t . Thismass con sist ed of the S-IV stage, Instrument Unit, and a ba ll as te d Supcternose cone ~ay1oa. l. The prescribed e l l ip t i c a l orb i t of a 1L2 na ut i ca lmtle perigee ar ~d 416 na ut ica l mile ap g ee was achieved. S-N t e s r ob j ec -t i v es i nc iuded de~ on s t r r t i on f t he s t a r t and fu l l -du ra t ion S~w ni ng f thes tage proljul sion sy s t e i t o pro-ce llant deple t ion , s t r; ic tu ra l in teg r i t y of bothf l i g h t s tz ge s, a d pro,ro-,e.rop ra t i on of t he e l ec t r i ca l , da t a acqu i si t i on,hydraul ic, and f l ig h t con trol systems. SA-5 was the Ti rs t f l ig ht te s t of the

I mid anc e systern. Hoirever, th e path adaptive g ~ i d u l c e?as flovtn open-ioop. Engine cerfornr,r,ce was sli gi- tly lower than ~ r e d i c t e d . The prop ellantu t i l i z a t i o n s y s t e n se rfo r~ ,ed t s f 'unc%ions exceedingly well, res ul t in g in aprc_oellant u t i l i z a t i o n o f 99.$ ~ e r c e n t f z r e d ic t ed d e p l e ti o n . Cxe f l i g h tanor aly was tke debor2ing of an e f t i n t e r s t age p n e l obse rved t o occur sub-sequent to s t% e separ r t ion .

On 28 Xay 1$L, the second Se t ~ r i l ehicle (SA-6) rd th a l i ve S-IV stage wassuccessful ly f ohm. Tie S -IV-6 stage , tog eth er w%th th e Inst-ruTent Unita d a ba l la ste d A p l lo bo i le rp lat e pzyload, 'r;as in ject ed i nt o Tile prescribedorbir, 1m:th a 99 n a u t i c z l n i l e p e ri ge e a nd 129 n a u t i c z l ~ d l ecogee. S-IVt e s t obfec t ives inclur ied denons t ra t ion of tine s t ~ r t n& ul l -&rat ion burn-5ng of tke s k g e pr o~ ul s i on ystem t o a g ~ i d m c e ys ten co~~:a:?


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GHT MEASUREMENTS

PARTIAL SUCCESS

FA1LED

% SUCCESSFUL


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GHT TEST SUMMARYSTAGE

STAGE THRUST %

STAGE I S P %3 STAGE TOTALC IMPULSE %x3mh )o ENGIN E BURNTIME %

PROPELLANTUTI LI ZATI O N %T/M DATARETRIEVAL %INJECTIONVELOCI TY %ORBITAL PERIOD%ORBITAL LIFE %(DAYS)


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f l i g h t c o n t r o l s y s t e m were a l s o p s i o f t h e t e s t 0 b:e ctiv es ; i n a d d i ti o n t ot h e t e s t i n g o f t h e A:p110 jet t lson escape system.

i he f i r s t s t q e e qe ri en ce d zn unexpected ea rl y cuto ff of one engine, w&ichre su lte d in lower and slo xer burnout con diticn s. 3.e S-IV stage enginesocerated noLTally with th e except ion of one e n gi ~ e, xhicn experienced ath ru s t con t rol le r mal fi lnc tion r esu l t in g i n higher -t 'nan-predicted th ix s t f romth et engine. The st% e p ro p ls io n systen ,perfomm.ce was sl i gh t l y lowerthan pred icted . Sig nif ica ntl y, th e guid*nce system com~anded he S-IV sta get o make up fo r the subnormal S- I st ag e cutof f con ditio ns. I 'his was eccom-pl i shed sa t i s fa c tor ik v. The p ro pl ia n t u t i l i z e t io n sys tem again cer formedi t s h c t i o n ex ce ed in gl y w ell, pro du cin g an e x t r a ~ o l a t e d r o ~ e l l a n t t i l i z a -t i o n of 99.95 percent t o propel lant deplet ion from the ac tu al coozimded cut-o ff . The S-TJ sta ge a f t inte rs ta ge panel debonding observed on the SA-5f l i gh t d i d no t r eoccur.

On 18 Sectex5er 1964, -the t 't ird Saturn vehi cle (SA-7) with a l i v e S-IV s tag er:as su cc es sf ul ly fiown. The S-IV-7 stag e, tog etn er rri_th th e Ins tr un en t Unitand a ba l l a s t e d bo i l e rp l a t e A p l l o pay loea , uas i n j ec t ed i n t o t he p r e sc ri bede l l i p t i c a l o r b i t o f 10G nau t i ca l n i l e pe r i gee and a 129 n e u t i c a l n i l e a p g e e .,-. n ee s t objec ti sres were ide nt i ca l t o the SA-6 f l i gh t , except tha t th e boi ler ->l a t e Acol lo escape notor i fas t es ted lns tead of the i e t t i s o n n o to r . Thestage propulsion system perforxiice wls zgairl sligktly lobier than ;i-edicted.P1c.e propel lant ut i i l iza t io n system rerforxed exce edL~g lywell, wit:? an extr a-p l - a t e d p r o _ r e l l a ~ t t i l i z e t i o n of 99.95 pe rcent t o _ r ro~e l l anC es l e t i on fromthe ac t -ua i corx'3ndecl cutolf. The S-IV e f t i nte rst age g a e l deboncling observedon the SA-5 f lf g h t reoccur:-eci, pad i s no t yet co:?,?let,el;y ~ ? d er st o o d .


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On 16 FeFjru~ry1565, the four th Saturn veh icle (SA-9) with a l i v e S-TJsta ge tras su cc es sf ull y flown. Tq:?is was th e f i r s t Saturn ve hic le enployedt o p la ce a f i~1 l .y perat ional payloa3 in to o r b i t . 'The py lo a d, des igna tedPegasus A, along x it h th e Lnstrument Unit, th e S-T? stage, ard a b o i l e r p l a t e.4pll o , was injec te d in to the prescriSed ell . ip ti ca1 near-Eart 'n or bi t with aper igee o f 6 8 nau t ic al mi les and an a p g e e o f 402 n a 7 ~ t i c a l i le s . Thes r imary t e s t o b jec t iv e ? ,a s t o e s t a b l i sh th e Fegasus ex p r i r i en t in o r b i t t odetermine the magnitude a d d ire ct ion o f in te- rzed ia te s ize meteroids. Inad di t io n , t h e A p U o c o m d no du le was t o b e sep ara ted from th e se rv icenodule. In order t o assure succe ssfu l Aygollo separa tion and Pegasus nete-o ro id d ek ct io n - m e 1 dep loyment, i t was necessary that the vehic1.e roll-rate be minimized. A non-propulsive ve ntin g system vas enployed t o iinitvehi cle motion a ft e r engine cu tof f. O~ererationof t h i s sys ten was success-fil a l t h o q h an unexpected roll-moment was i q a r t e d t o the Pegasus becauseof iaptngenent of vented oxygen on the d ete cto r p n e l s . (lJtktough thefo rc e iii2 arted i s very srr?-11, th e la rg e panel eisea and ,~omentz m of she$6 ' x l L r P eg asus "w ings" i s s u f f i c i en t t o produce a s ig n i f i ca n t r o l l r a t e . )The res ultir rg moL,ion, rrhile g re at er than ex ~e ct ed , di d not con>rorrjse th esucce ss of the mission. One co ntr ibu tin g fa ct or to the roil-moment was as1ig':tl.y 'r,Pg7vler 'nan exp ected qu m t i t y of re s i& ua l pr op e ll m ts a t th e t h eof in je ct io n in to or b it . !i%e perforr:ance of th e propi-sSon syscem d u~ il igtlze fi r s t thr ee S-IV f l i gh ts had been con sis ten tly 0 .7% lo:?er than noainal .This had been a tt r i bu te d TO a base drzg effec-i caused by engine clusteringand he& been tak en i n t o ECCO-!L'~+n determining th e pred ic ted S- IV p er fo r -rlmce of SA-9. In t k i s f l i g m h owever, s y s t e ~ e r f o r ~ a n c e ?zs -1ery n e ar l ynol.?inal, %e ref ore t 're bia s 2.n p e d i c t i n g p r f o r n ~ z t c e e s u l t e d i n s o;-e :c h~tIriigher grozellant resicllizls.


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On 25 !:2qJr l$65, the f i f t 5 conzscut ive success fu l E-Ti f l e x a s ~ ; w tf t h eS z k m vehicle , SA-8. c b i e c t i v e o f t h i s f l i g h t , a s o f SPA-9, was t o p tari oge rat io nal Pegasus payload in$o a neer-Zarth o rb i t . The ~ e r f o r m n c e f$!?is s tage was abzost exac t ly es yrer iic ted. The or ki t p r a ? e t e r s cons is te dof a raxige e of 276 neutical rr .i les aad zn zpogee of 406 nawtical ~ d e s .aorder t o reduce the ro l l -zo t io r ! h pa r t ed by vented gasses , the LOX znd LH2n o n - y o y l s i v e v e nt s % er e inxerckanged so that vented oxygen iiould not bedirected toward the p y l 0a d p a e l s . The ef'fect of vented hydroger, vouldprodxce a roll-~?.o:nent, bt d of a l e s s e r rnaFprr?itu2e. Per fornulce of th i ss tag e was very near ly exact l y as ant i cip ate d. The pzyloed rol l - ra te wassi gn if ic an t l y reciuced and no dif f ic ul t j r was ex ~e ri en ce d n A p o l l o s e p a a t i o no r Fecesus deployment. P r o p e l l a t u t i l i z a t i o n on t h e f l i g h t was e x c el l e n t; ? i t h E ncnzn~t lm i d u e r a t i o r ~ a i n ta i n ed h ro ug ho ut t'ne ~ o ~ i e r e dort ti on oft h e f l i g h t .

6 . S FT EEXFZELTJCE N73 ITS IJTACT 0:: S-FTl?

As we gathered the ac tua l exx r ie nc e with the S - N systen?, we a ~ p l i e d t5r xe c ti e te l y t o t he S-IVB wfnich :,:as the n i n th e des ign st ag e. I d e a l l y alonger t ine s p a would have en&- led the engineers t o rake a ven be t t e ruse of t h i s exper ience. There vere very few negativ e re su lt s rv~hich orce dus t o change desi,q concepts. The nain b e ~ l e f i t arre fro n tifie proof t h a tce rt ai n zethods we had used worked v e i l and cculd be in co rp xa te d i.rithcutf l x th e r t h e c on s~ xL ngd e v e l o ~ z e n t ff o r t s , The ~ o s ta v z l u a b l e e x ~ e r i e n c ewas the fa x i l i a i z a t io n ;.rith the handl ing of IS.:,. % i s iiss zn ~:~~ex-c.?-ored

d

f i e l d fo r roclce t opera t ions 2nd had been avoided f c r s, long t h e a s u nr ea i-i s t i c a l l y d i f f i cu l t . It can be s t a t e d t 'r,at Douglas 'cy r-o:.r i s h a id l in g :JI=,-


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i n a rou t ine xmvle r . A t th e no3ent we are probably the l w g e s t Lt! c o n s q a e r2i n t h e w or ld . S-I7,r ex ~e r i en ce s n s t age se r a r a t i on zqd i gn i t i on i n spacexe re used i n he design of the S-IVB. The te s t 2nd checkout procedureseskaklished during the developnent of the S-IV were used as the Coun3ationTor th e t e s t prograq of th e muck? Fore c o ~ q l e x -FE,. Oi c c u r s e , e x * ~ r l e n c e sof e arl , ier rIZssi les l i k e the S ~ y b o l t , he Thor and the Mike, whtch weredeve lopd by the s m e team, con t r ibu t ed a s we l l .

7. ST,WS OF S-IV S- IF ? PROGiiAMWhere do we s ta nd now i n ou r S-IV/S-IVS progran? m e n on ?.ky 2LJ 1 9 0 t h ef i r s t d eve lop en t c ont r ac t was s igned the progra ii inc luded the development,panufacture , and te s t of t en S-IV s tages of 5 iliich s ix jrere t o be f l i g h tt e s t e d . This program was t o be ended with th e l a s t launch i n August 1965.We ar e aow clos e t o t'ne end and hopefu lly i t r i l l conclude successfu1l.y with thel a s t E i g h t o f SA-10 ne xt ~ o n t h . foll owi ng prcgram, t h e development o fth e S-DJB, star t?e d i n Ap ri l 1$2 has s o fa r 3rcceeded very nic ely. Of t h e~ r o g r a m e c t o u r u n i t s f o r g rou nd t e s t i n g , t h e t w el ve u n i t s f o r t h e Saturn Eand t h e s i x u n i t s f o r S a tu r n V, we have b u i l t a nd d e li v e r ed a l l o f t h e f i r s tca t egory . The f i r s t veh i c l e o f t he Sa tu rn 33 c l a s s i s i n t h e t e s t s t an d a.tSacrarrento, Za li fo rn ia . The next i s i n f i n a l checkout a t Huqt ington Beach,C a l i f o r n i a . All o the r s -e i n d i f f e r e n t s zzges o f a s se r+ ~ ly nd nanufactu re .Tne de ve lo pen t p rog rax ~ r 'n i ch nc ludes apprcx i r s t e y 1000 t e s t s i s con ingalong. tkny probless s t i l l cha l lenge the i r?ger.ui 'iy 05 o il r engineers , butno major obstacle i s foreseen. As menxione3 before , zhe experience g ath -ered du rin s th e develoy;r-enz of th e S -Fi has heiged t o s as e th e proble-ns oft h e s-5n3.


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h as e n v i ro m e n ta l ly c o n t ro l l e d c o ld p la te s a v a i l a b le fo r c o n d i tio n inga u x i l i a r y p y l o a d s . P .e a cc om.o da tio ti o f e x ~ e r h e n t s n d/or p y lo a -3 ~fo r these loca t ions de ~e nd n the miss ion req l i i reaen ts ; i. ., environ-xent, mounting, e l ec tr ic a l Faker, t e l e ~ z e t r j , a t t i t u d e c o nt r ol , ando r b i t a l op e ra t in g t k e .

b . Pods co ntai nin g experiments and/or payloads can be nountec? onth e i 'orward s k i r t of the S-IVB, (7 8 fe et 3 and 1100 lb s . each).The ~ o d s i l l allori experiments t o be : (a ) sub Jec ted t o spaceenvironment by je tt iso ni ng th e pod fairing; ( 5 ) j e t t i s o n e d a sa package or as in d i~ r idu a l xp erh en ts ; (c ) launched in to avar ie t y of o rb i t s by us ing a so l id motor such as the X-258De l ta th i rd s t a g e .

c . m e volume with in the LH tank w i l l provide a very co ld environ-2meat -vrhich may be usel'ul t o ex pr im en te rs in te re st ed in low noiser ec ep ti on o r e q e r i n e n t s w i t h s u p e r - c o n * ~ c t ~ g a t e r i a l s . Several3.5 f e e t 3 s p h e r i c a l b o t t l e s a r e a v a i l a b le .

E l e c t r i c a l p ower a nd t e l eme t ry i s a c c e s s ib le t o th e s e a re a s . If presen te l ec t r ic a l poT*rerand te lemztry i a no t adequate, ad3 i t ion a l ba2 te r i es o fthe Sa turn V type m d an adctit ional te lemetr y system ( k i t ) can be added.

0Attitude con7;rol of the S-IX? n c lu din g pa yloa d i s a v a i l a b le t o +1 i n a l lth r ee axes dur ing the 4-1/2 hour o r b i ta l coas t . If' a d d i t io n a l a t t i tu d e c o n -t r o l l e d c o a st i s r eq ui re d, t h e l a r g e r S a tu rn ST KCS and/or r el ax at io n of th econ tro l tolera nce can be provided. This w i l l p -o vi de a t t i t u d e c o n t r o l t o a smuch as 72 holx-s in o rb it .


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I st at ed i n the beginning th at %he Saturn IB xi11 i n i t i a l - f l i g h t t e s t un-mnned and nanned P.pollo h adw are . Ilowever, i t s cap ab il it ie s ar e ;.;Lcplicablet o raztly ot he r p?.yload ob je ct iv es .

The Saturn E, o r in stance , catl place up t o 35,000 _pounds in to a 100 n.mi.due eas t ea r th o rb i t ( s ee f i gu re 21), or 27,900 pounds in to a p o l a r o r b i t .The t h e e s tage Saturn IB, /~entaur vers ion be ing p lanned as the boos ter fo rVoyager w;,ll place 9,800 pounds t o synchronous o rb it al t i tu de , over 12,300pounds t o escap e and about 8..5cC, .punds on a Mars-Venus tr an sf er t ra je ct or y,These f igures rec resent the t o t a l prime payload ca pabi l i ty . Ce r t a in fu tu reniss ions 3s present ly p lanned w i l l not have prime ~a yl oa dswhich f'ullyu - t i l i z e t h i s t o t a l b o os te r c a p a b il i ty . On shese launches , ther e i s a -goodpo ss ib i l i ty t ha t a uxi l ia ry payloads or exper infents could be ca r r ie d a longa t a ar ;linL~al os t t o th e ex~er i r nenter .

On the S-TVTJ s tage these ex is t s a v ide va r ie ty of s ize s a d shapes cf volumesfo r mounting p rime ~ a ~ r lo a d snd a ux il i a ry e x~ er ir -e nt s ~ i ~ .2). The niount-ing of such zu xl li ar y experiments or prime payloads i s >".at Pouglas c a l lsthe Space Pac coricept. fin ex an ple o f a p r i ~ e ayload v o l u ~ e s t he 'Jgyagertype shrcud which would allow 300@cu . f t . of sgttce. In adAition, th er e ar evolumes w ai la b le : ihlre au xi l ia ry pqvloads czn be xountet i n such area s asthe forward ski r t , a f t sk i r t , ex te rna l yods, and, wi th in the hydrogen tanki t s e l f . A nore de t ,a iled descr ip t ion of t h is space ,?sc i s a s fo l lows:

3. E x ~ e r i n e r . 5 ~yd,/or _cayloads czn be c a r ri e d ir. the for ~ra -d k i?-", (upt o 110 $eet3 2x6 10C lbs.) 2ft s k i r t (8 f ee t3 ) cr ~ ~ i i t h i nh e I n s t r u -zent Unit , (425 fee t3 and 2533 l b s . ) . ?he for:v7arc! s k i r t ar ea ai so


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SATURN B PERFORMANCE


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S-IVB PAYLOAD VOLUMES

PAYLOAD FAIRING FORWARD SKIRT

ENVE LOPE 3 1(VOL. 810 M )PAYLOAD ADAPTER


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With t h e exce l len t r e s u l t s o f t he S - N s t q e backing our expec ta t ions in thec a p a b i l i t i e s of th e S-J?B/B;Te ar e very encouraged i n our fu tur e programsof space ex pl or at io n. We -know ve have t h e t e c b ~ i c r , i o o l s . We m n t t oassure owse lves of the coopera t ion of all ~ e o p l e n th e 'western world, and,hopefully the whole tiorld, 5n QLW space endeavors.

W e h o w t h at the magnitude of tl-.is t as k i s a trernendoas one. W hzve tack-;ledt h e f i r s t p a r t; t h e d e v e lo p e n t of s u f f i c i e n t l y lage boosters . It has t&er:us many years a d t w i l l re qu ir e some ac re befo re we have per fe cte d the n.

Bat we have onl y scr atc he d t h e su rf w e of th e vzs t complex of space explora-t io n . Ikis i s the f i e l d .&ere we w i l l have t o concentrate our fut ure spaceefforts and wh?re t h e r e s u l t s w i l l be most benefi cial t o a l l of mankind.

flight results and experiences with the s-iv stage of the saturn i

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