space shuttle 1974

8/7/2019 Space Shuttle 1974

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SPACE SHUTTLE FACT SHEETIn t roduc t ion

The Space Shuttle w i l l be a reusab le space veh ic l eoperated as a t r a n s p o r t a t i o n s y s t e m f o r a wide var ie ty ofspace miss ions i n low Ear th or bi t .s a t e l l i t e s of a l l types . Since it can carry payloads weigh-ing up t o 29,500 kilograms (65,000 pounds) it w i l l r e p l a c emost of t h e expendable la7mch ve hi c l es cur ren t ly used.

The Shuttle w i l l d ep lo y s c i e n t i f i c and a p p l i c a t i o n s

The Shuttle w i l l be a b le t o r e t r i e v e s a t e l l i t e s fromE a r t h o-b4.t; t o r e p a i r and rede ploy them; o r bring them backt o E ar th l o r refbrbishment and reuse. It c a n a l s o be usedt o c a r r y o ut m i s sio ns i n which s c i e n t i s t s and t e c h n i c i a n scondilct experii i ients i n Eart h or bi t or s e n i c e automateds a t e l l i t e s a lr e a dy o r Di ti ng .The Nati onal A eron auti cs and Space wdruinistr ation p la nst o develop t h e S h u t t l e o ve r t h e n e xt s i x years . Horizonta lt e s t f l i g h t s a re t o begjn i n 1977, o r b i t a l t e s t f l i g h t s i n1979, and the complete vehicle i s t o be o pe r at io n al i n 1980.The Shuttle w i l l provide Ln ef fe ct iv e and economical

means f o r t h e United S t i t e z t o u t i l i z e and a dvance i t s capa-b i l i t i e s i n s pace. It d i l l r e du c e s u b s t a n t i a l l y t h e c o s t ofspace operat ions f o r c i v i l i a n and d e f e n s s n ee ds i n t h e d ec ad eof t h e 1980's and beyond.The Shuttle wil l r o n s i s t o f a reusab le o rb i te r , mountedpiggy back a t lau nch 011 a l a rge expendab le l iqu id p rope l lan ttank and two reccverable and reusa ble so l i d propel l ant rocke tboosters . The or bi te r w i l l l o o k l i k e E del ta-winged a i rplane,abo l l t the s ize o f a DC-9 j e t l i ne r . It will h a v e t h r e e l i q u idfuel ed rocket engines , a carg o bay 18 meters (60 f e e t ) l ongand 4.5 meters ( 1 5 f e e t ) i n d ia me te r, and w i l l be operatedby a crew of t h r e e . L n g s p a n w i l l be about 24 meters (78f e e t ) a n d i t will be about 37 meters ( 1 2 2 f e e t ) long.W i t h t h e e x t e r n a l t a n k a t t a c h e d , t h e t o t a l S hu t tl eveh ic le will stand about 57 meters (184 f e e t ) t a l l on thelaunch pad.

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- 2 -A t l au nc h, t h e two s o l i d r o c k e t s and t h e o r b i t e r s t h r e el i qu id rocke t eng ines will i g n i t e and burn s imul taneously .

A t a n a l t i t u d e o f a bo ut 4 9 kilometers (approximately 25 s t a t u t em i l e s ) t ie s pe nt s o l i d r o c k e t s w i l ; be detached and parachutedi n t o t h e ocean f o r recovery and reuse. Following s o l i d r o c k e ts taging, t h e o r b i t e r a n d i t s propel lant ta ,nk w i l l cont inueascen t . A t main engine cut o f f , the expendab le p rope l lan tt a n k will b e j e t t i s o n e d i n t o a remote ocean area.o r b i t e r t h e n f i r e s i t s or b i ta l maneuvering system (OMS) f o ra s h o r t p e ri o d t o a ch ie ve o r b i t a l i n s e r t i o n . The o r b i t e r w i t hi t s crew and payload will remain i n a r b i t t o c a r ry o u t i t smission, normally f o r about seven days, but when re qu ir edf o r a s l o n g a s 3 0 days. When t h e mis sio n i s completed t h eo r b i t e r will r e t u r n t o E ar t h and l a n d l i k e a n a i r p l an e .

The

Eackgr oundExtensive engineer ing, de s ign , and cost s t ud ie s of aSpace Thut t le were i n i t i a t e d by NASAs O ff ic e of MannedSpace F l i g h t i n e a r l y 1980. These studies covered a wideva r i e t y of concepts ranging from a f u l l y reus ab le mannedboos te r and o r b i te r t o t h e concept employing an ex t e rn a l p ro-p e l l a n t r o c k e t s w hich was s e l e c t e d . I n de p th s t u d i e s f o r e ac hof sev era l cand ida te concepts eva lua ted t h e deve lopment r i s kand c o st i n r e l a t i o n t o t h e o p e r at i o na l s u i t a b i l i t y and t h eove ra l l economics o f th e e n t i r e system.

Rockwell Gorp., (now Rockwell In tt 2r na ti on al ), was s e le c t ed t odevelop th e high pres sure l iq ui d oxygen, l i qu id hydrogenengines which p rov ide t h e main p ropu ls ion f o r t h e o rb i t e r .

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I n J u l y 1971, the 9ocketdyne Divis ion o f North American

On January 5 , 1972 , Pr es id en t Nixon announced t h a t NASAshould proceed w ith development of a reusa ble low cost SpaceS hu tt le system. He sa id :This system w i l l cen te r on a space veh ic l e th a t cans h u t t l e r e p e a t e d ly f rom E a r th t o o r b i t and b ack. I tsiri11 r evolut ioniz e t r a n s p o r t a tion in t o near space,by rou t in iz ing i t . It w i l l t a k e t h e a s t r o n o m ic a l c o s t so ut of a s t r o n a u t i c s . I n s h o r t , it w i l l go a long waytoward d e l i v e r i n g t h e r i c h b e n e f i t s o f p r a c t i c a l s pa ceu t i i i z a t i o n and t h e v a l ua b l e s p i n o f f s f rom sp ac e e f f o r t si n t o t h e d a i l y l i v e s of Americans and a l l people.However, a l l t h e s e p o s s i b i l i t i e s , and c o m t l e s s o t h e r swith direct and dramatic bearing on human betterment,can never be more than f r ac t i on a l ly re a l iz ed so longa s e ve ry s i n g l e t r i p from E a rt h t o o r b i t r em ai ns a

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- 3 -matter of sp ec ia l e f fo r t and s tagg er ing expense . Th isi s why commitment t o t h e Space S h u t t l e program i s t h er i g h t n ex t s t e p f o r America t o t a k e , i n moving out fromour prese nt beach-head i n t h e sky t o ach ieve a r e a lworking presence i n s pa ce - ecause the Space Shut t l ewill g i v e u s r o u t i n e a c c es s t o s p ac e by s h a r p l y r e d ac i n gc o s t s i n d o l l a r s a nd p r e pa r at i o n time."I n t e n s iv e e n g in e e rin g s t u d i e s were continued throughJan uar y and Feb rua ry of 1972 by NASA arid i t s aerospace indus t rycon t rac to rs . These s t ud ie s concen t rated on t he t e ch n i ca l andeconomic as pe ct s of us ing e i t he r a s o l i d o r l i q u i d p r o p e ll a n trocke t boos te r , and a l so t h e f e a s i b i l i t y o f a recoverab le

and reusable o r an expendable system fo r e i t he r typ e ofboos te r .On March 1 5 , 1972, Dr. James C. Fl et ch er , NASA Administra-tor , announced that t h e S h u t t l e would u s e tw in s o l i d p r o p e l l a n trocket motors which w i l l be reco verab le and reus able . Thed e c i s i o n was based on informat ion developed by t h e s tu di eswhich showed t h a t t h e s o l id rocke t sys tem of fe red lower deve lop-ment cost and lower te ch ni ca l r i s k .The c on cep t of t h e e x t e r n a l p r o p e l l a n t t a n k f o r t h e o r b i t e :had a major impact. By making t h e or b i te r much more e f f i c ie n t ,

it became po ss ib le t o l e t t h e o r b i t e r t a k e more o f t h e b ur de nof p rope l l ing t h e Shu t t l e i n t o o r b i t . Boos te r shutdown ands t a g in g s e p a r a t i o n c ou ld t h e r e f o r e o cc ur a t a much lowera l t i t u d e and v e l o c i t y . T h i s importafi t advantage presentedt h e o pp or tu ni ty t o us e b a l l i s t i c l i q u i d r o ck e t b o os t er s o rso l i d rocke t motor boos t e r s t h a t a r e e f f i c i e n t a t the lowerstaging v e l o c i t i e s .i n development cos ts . O f t h e two, t h e development co st s oft h e . so l i d rocket boost er were es t imated t o be about $700m i l l i o n l ow er t h a n t h o s e of t h e l i q u i d r o c ke t b o os te r .

The f i n a l d e t e r m in a t i o n was t h a t t h e s o l i d r o ck etb o o s t e r r e c o v e r a bl e s ys te m w i th t h e o r b i t e r l i q u id r o c k e t si n pa ra l l e l would have t h e lowes t t o t a l deve lopmentp er f l i g h t , and lowest te ch ni ca l r i s k of development.Addi tion ally, economic stu d ie s had shown t h a t t h i s systemwould provide t h e highest r a t e of re t u rn on investment.

A pa ra l l e l burn, where boos ter and o r b i te r eng ines a r eig ni te d a t l i f t -o ff , ta ke s maximum advantage of th e highperformance o r b i t er engines and i s p a r t ic u l a r ly a t t r a c t i v ef o r t h e s o l i d s w here it i s d e s i r a b l e t o minimize t h e i r s i z ef o r o p e r a t i o n a l c o s t r e a so n s .

T h e ir u s e p ro mise d t h e g r e a t e s t r e d u c t i o n

$5.25 b i l l io n i n 1971 d o l l a r s ) , l e a s t c a p i ta l r i s k

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- 4 -On March 17, 1972, N.,SA is su ed re qu es ts f o r pr op os al st o industry for developmen; o f t h e o r b i t e r v e h i c l e and s ys te msi n t e g r a t i o n f o r t h e o r b i t e r e x t e r n a l p r o pe l la n t t a n k , s o l i drocke t boos te r , and o r b i te r m ain engine.

of t h e Kennedy Space Cen ter i n Fl or id a and Vandenberg A i rForce Base i n C al i f or n ia as t h e s i t e s from which t h e SpaceS h u t t l e w i l l be operated.On July 26 , 1972, North American Rockwell Corporation's(now Rockwell In te rn at io na l) Space Divis ion, Downey, Ca li fo rn ia ,

w a s s e l e c t e d as prime con+ ,ractor f o r desi gn , development aridpjoduct ion of t h e o r b i t e r a nd i t s i n t e g r a t i o n w i t h a l l o th e re lements o f t h e Sh u t t l e sys tem.On August 1 6 , 1 9 7 3 , t h e Mart in-Marie t ta Corporat ion,Denver Division, was s e l e c t e d t o d e s ig n , d ev el op , t e s t andevaluate t h e S h u t t l e e x t e r n a l t a n k. T h i s c o n t r a c t i n c lu d e st h e f a b r i c a t i o n of t h r e e ground t e s t tanks and s i x developmentf l i g h t t a n k s.The f i n a l major S hut f le c ont rac tor , Thiokol ChemicalCorp orat ion of Brigham Ci ty , Utah, was s e l e c t e d on November 20,1973, t o d e s ig n , d ev el op , t e s t and e v a lu a t e t h e s o l i d r o c k e tmotors. The proposed contract w i l l i n c l u d e f a b r i c a t i o n of

ground t e s t and development f l i g h t motors wi th a sep ara tefol low-on con tra ct f o r t h e major engine product ion.

On Apr i l 1 4 , 1972, D r . Fle tc her announced t h e se le c t io n

Space Shut t le Configurat ionOn t he l aunch pad t h e S hu t t l e system w i l l stand aboutha l f as t a l l a s t h e Apollo-Saturn ve hi c l e , and consi s t of fo urla r ge e lements c lu s te red toge th er ; t h e expendable rop e l l an tt a n k , tw in r e c o v e ra b l e s o l i d ro c k e t b o o s t e r (SRB'S P and th eo r b i t e r v e h i c l e . The s o l i d r o c k e t s w i l l be mounted t o t h et a n k a t two points approximately 180 d e g r e e s a p a r t .about 47 meters (154 f e e t ) l on g and 8 .4 meters (27 .5 f e e t ) i ndiameter , w i l l be mounted beneath t h e o rb i t er .

21, hours and launched wi th in two h o u r s from th e s t an db y s t a tu sOn s t a n d b y s t a tu s it w i l l be ready for launch except f o r cryo-gen ic p rope l lan t fill ( l i q u i d hydrogen and oxygen), crewin g r e s s a nd f i n a l s y st em s v e r i f i c a t i o n .

The tank,

The Shuttle can be held on a s tandby launch s ta tus f o r

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- 5 -A t l a un c h t h e t w i n rocket booster , about 3 . "meters(12.2 f e e t ) i n d iamete r and 45.5 meters (149 e e t ) long w i l l beig n i t e d s im ul t an e ou s ly w ith t h e l i q u id f u e l e d o r b i t e r e n g ine sand b ur n i n p a r a l l e l w i th t h e o r b i t e r e n i n e z t o a n a l t i t u d eof about 40 ki lomete rs (25 s t a t u t e m il es7 The so l i d roc ke t swill th en be detached, descend by parachutes , t o be recovered,refur bishe d and reused. The so l i d ro ck et s are e xp ec te d t o bec ap ab le of a t l e a s t 20 reuses .

(6,141,000 pounds) made up of 1,668,000 newtons (375,000 pounds)from each of t h e th re e main engines a t se a le ve l and 11,156,000newtons (2,508,000 pounds) f r o m each of t h e two so l i d boos te r s .T o t a l l i f t 9 f f t h r u s t i s t o be 27,316,000 newtons

Orbi ter -- The orbi ter will be about the s i z e of a DC-9a i r c r a f t , a p p r o x i m a t e l y 37 meters ( 1 2 2 f e e t ) long and have awing spr ead of 24 me te rs ( 7 8 f e e t ) . The cargo compartment,o r payload bay, w i l l be approximately 4.5 meters ( 1 5 f e e t )i n d iameter and 18 meters (60 f e e t ) long. Maximum payl oadc a p a b i l i t y w i l l be 29,500 kilograms (65,000 pounds) launcheddue East i n a 278 ki lometer (150 n a u t i c a l m i l e ) o r b i t .Cargo bay doors extending t h e f u l l ength of t h e cargo baypermit exposure o r deployment o f payloads.The orbi ter : v i11 be capable of landing on a conventionalrunway with a payload weighing up t o 14,000 ki lograms (32,000pounds ).Unl ike p revious manned space cra f t t h e Shu t t l e o rb i t e rw i l l have reusab le ex t e rn a l ins u la t io n . Each veh ic l e w i l l bedesigned t o c a r ry out a t l e a s t 100 space missions without major-7erhaul.After extended s tudy and te s t i n g of pass ive thermalp r o t e c t i o n s ys te ms , r e u s a b l e s u r f a c e i n s u l a t i o n m a te r i a l swere s e le cte d t o reduce refurbishment requirgments . gorareas sub jec ted t o t e mp er a tu r es i n t h e 1 , 9 2 2 K (3 ,000 F)r a w e , a n o x ida t i on - inh ib it e d c ar bo n m a te r i a l w i l l be used.It co ns i s t s of pyro l ized carbon f ib e rs i n a pyro l ized ca rbonmatrix w i t h s i l i c o n c a rb id e c o a t i ng , and i s comiionly referredt o a s "carbon-carbon" .

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- 6 -In te rmedia te hea t ing areas (u p t o 1,533'K o r 2,300'F)w i l l be pro te c ted by high tempera tu re reusab le su r fa ce insu la -t i o n t i l e s (HRSI), cons i s t ing o f 99% pure f e l t e d s i l i c af iber s . These t i l e s range i n th icknes s f rom 2.5 crn t o 7.5 cm(1 t o 3 i n c h e s ) ,bo ro s i l i ca te coa t ing con ta in ing pigment t o p rov ide t h e d e s i r e dabsorptance/emit tance ra t ios .s i d g s of t 8 e fus ela ge, where temperatures do not exceed616 K (650 F ) low-tempera tu re reusa b le su r fac e in su la t i onwill be used.

The t i l e s w i l l be p ro tec ted by a f r i t t e dFor a r e a s a lo ng t h e t o p a nd

I n normal opera tio ns, t h e person nel complement can varyfrom t h r e e t o a maximum of seven. The ba si c crew co n si st sof a p i l o t , co-pi lo t and miss ion speci a l . i s t . For complexpayload missions, up t o f o u r a d d i t on91 p ay lo ad s p e c i a l i s t scan be carried. Accommodations a r e prov ided f o r bo th sexes.A l l w i l l normally t r a v e l i n sh i r t - s lee ve comfort wi thou tspace su i t s and undergo a maximum of 3 G f o r c e s d u r i nglaunch and reentry .

If r e q u i r e d t h e o r b i t e r will c a r r y a docking modulei n th e payload bay and w i l l be capable of manual docking w i t hoth er ve hi c l es wi th compat ible docking devices . The miss ions p e c i a l i s t will h av e a c c e s s t o t h e p ay lo ad t h r ou g h a n a i r l o c klead ing i n t o t h e pay load compartaent wi thout d epr ess ur i za t ionof t h e o r b i t e r c ab in . He w i l l t h e n be ab l e t o check ou t anddeploy ce r t a i n pay loads or c on du ct i n v e s t i g a t i o n s r e q u i r i n gd i r e c t a c ce s s t o s pac e.On s o m e f l i g h t s a press ur ize d Spacelab, being developedby nine European countries a t t h e i r e xpe ns e, w i l l be ca r r iedi;l t h e payload bay and will s e r v e a s a space laboratory .For t h 3 f i r s t t ime , s c ie n t i s t s and eng ineers who a re no ta s t r o n a u t s will have an opportunity t o accompany and conductt h e i r experiments i n space.

experiments a r e c a r r i e d o ut i n t h e Orbiter payload bay,Experiments can be assembl ed, checked o ut , and mated i nadvance and t h e S pa ce la b i n s t a l l e d i n t h e p a yloa d b ay just p r i o rt o f l i gh t . The Spacelab w i l l inc lude a pressur ized enc losurehousing s uppo rt equipment ( t o make i t h a b i t a b l e ) a s w e l l . ast h e experiment al equipment. When sen sor s re qu ir e d i r e c t expo-sure t o t h e space environmmt, a p a l l e t w i l l be used i n asso-c i a t i c n w i t h t h e p r e s s u ri z e d e n cl o su r e. On o th e r t y p e s ofmiss ions , a p a l l e t may be used alo ne, w i t h t h e c o n t r o l o f t h eins t ruments taking place f rom t h e 9 r b i t e r c a b i n o r even fromt h e ground. The Spa cel abs a r e b e h g designed a round a b a s i cseven-day mi ss io n which i s extendable up t o 30 days by t r a d i n goff payload weight and volume f o r t h e addi t ional consumablesnecessa ry t o accommodate th e a dd i t io na l t ime i n o r b i t .

The Spacelab w i l l be t h e means by which man-a ssociated

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- 7 -The Spacelab i s be ing des igned t o meet t h e requi rementsof a broad spectrum of sc ienc e and app l i ca t i on s , domest icand foreign. It w i l l provide a f u l l complement of gene ralsupport equipment and have pr ov is io ns t o accommodate a wideva r i e t y of spe cia l iz ed needs . The Spacelab i s being developedi n Europe with European funding under t h e ausp ices o f t h eEuropean Space Agency (ESA). It w i l l be buil t by Europeanin du st ry under t h e management of VFW-FOKKER-ERN0 o f WestGermany. The dev elopmen t w i l l i n c l u d e t h e d e l i v e r y o f onef l i g h t uni t and c er ta in engineer ing and hardware support t oNASA. NASA w i l l purchase one o r more addi t ional Spacelabsfrom the Europeans.

Space Shu t t le Miss ions and Operat ional C ap ab i l i t ie sAs t he Shu t t l e becomes op era t i ona l , it w i l l c a rr y i n t os p a c e v i r t u a l l y a l l of t h e n a t i o n ' s c i v i l i a n and m i l i t a r ypayloads a s wel l as many in te rn at io na l c i v i l i a n and gover'n-ment payloads. These inc lud e sci enc e and ap pl ic at io nsp ay lo ad s f o r p r i v a t e i n d u s t r y , u n iv e r s i t i e s and r e s e a r c horganizat ions .

w i l l be required t o handle the volume of space payloads ant i -c ip at ed i n t h e 1980's.Approximately 60 t o 70 Shu t t l e miss ions each year

S t u di e s of p o t e n t i a l S h u t t l e m i ss i on s i n t h i s p e ri odi n d i c a t e t h a t a bo ut 38 p e rc e nt a r e l i k e l y t o be S pa ce la bmiss ions w i t h t h e r em aind er b e in g t h e p la ce me nt , r e v i s i t , o rr e t r i e v a l o f a u to ma te d s pa c e c r a f t .The 1973 Payload Model - NASA's most r e c e n t a n a l y s i s --e s ti m at es t h a t t h e d i s t r i b u t i o n of a c t i v i t y i n t h e 1 9 8 0 ' sw i l l be approximately a s fol lows:Science -- Astronomy, physics , l i f e sc ien ces ,lunar and p lane ta ry 3k%Applicat ions -- Ea rt h re so ur ce s, communica-t i o n s and nav iga t ion , spaceprocess ing , e tc . 3 5%Department of Defense 31%

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- 8 -A t y p i c a l s c e n a r i o of t h e u s e of t h e Space Shu t t l e t op l a ce a n automated s a t e l l i t e i n low Earth orbi t would be asf ol lo ws : The S h u t t l e c a r r i e s t h e s p a c ec r a f t t o t h e r e q ui r e da l t i t u d e and i n c l i n a t i o n . The s a t e l l i t e i s checked outthoroughly by a payload specia l is t t o v a l i d a t e i t s opera t ioni n t h e env ironment o f space. Adjustments and ca li br at io il o fins t ruments and senso rs ar e performed before t h e sp acecr af ti s committed t o i t s unat tended operat ion. In t h e e v en t t h espacecra f t f a i l s t o p er fo rm as planned and on-orbi t re pa ir sa r e in a de q ua t e, t h e s p a c e c r a f t i s re tu rned t o Earth f o r mweext ens ive re pa ir s. The same procedure i s a p pl ie d t o n;. ll-func t ioning spa cecra f t p rev ious ly p laced i n o rb i t .s p a ce c r af t c a r r i e d t o o r b i t by t h e S h u t t l e t h e re b y s t a r t s i t s

on-orbi t opera t ion i n func t ion ing condi t ion .Each

I n a study of 1 3 1 s a t e l l i t e f a i l u r e s which have o cc ur re di n t h e p as t , 78 were re la te d t o l aunch p roblems. The remain-i n g 53 f a i l u r e s were a t t r i b u t a b l e t o s p a c e c ra f t an om ol ie s.Most of th es e fa i l u r e s could have been avoided i f t h e S h u t t l ehad been available.The s i z e and weight-carrying capac i ty of th e or bi te rw i l l f r ee spacecra f t des igners f rom cons t r a i n t s which havemade payload development very ti me consuming and co st ly .It will be p o s s ib l e t o u s e r e l e t i v e ly i n ex p en s iv e c o ns t ru c -t i o n mat e r ia l s and s tandard labor a to ry equipment i n p laceof sp ec ia l l y constructed, h ighly minia t ur ize d components whichare e x pe n siv e t o d e v elo p and t e s t .The Sh ut t l e can be used t o va l i da te prototy pe ins trumen-t a t i o n and sub-systems i n t h e t r u e space environment and re t ur nthem t o Ear th f o r ana lys i s and i n c o r po r a t i o n i n t o s p ac e c ra f tdes ig ns with o per at i ona l assurance having been demonstra ted .The Shuttle w i l l be capable of t r a n s p o r t i n g p a y lo a d s upt o 500 m il e s i n E ar th o r b i t .miss ions which requ i re h igher o rb i t s . To achieve these higherorb i t s , a Space Tug i s re qu ir ed . The Space Tug will be ar e u s a b le s t a g e t h a t w i l l f i t i n t h e S h u t t l e c ar go bay w i t h i t spayload and w i l l p r o v id e t h e c a p a b i l i t y t o p lace and re t r i evepay loads i n o rb i t s beyond th e ca pab i l i ty of t h e S hu t t l e anda c hi e ve E a r th e s ca pe v e lo c i t i e s f o r t r a n s p l a n e t a r y s p a c e c ra f t .A tentative agreement has been reached between NASA and theDepartment of Defense f o r t h e DOD t o develop a n i n i t i a lupper s ta ge cal l ed an Orbit - to-Orbi t Stage us ing exi s t in gtech nolo gy and/or components. This st ag e w i l l not have apay load re t r i e va l cap ab i l i t y but may be reusab le . I t will beava i la ble when t h e S hu t t le becomes ope rat ion al i n '380,

However, t h e r e a r e many sp ace

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- 9 -ForandTugon-

While t h i s in i ' ; i a l upper s ta ge i s developed by the Airce, NASA w i l l cont inue planning f o r t h e l a t e r d e v e lo p m e n tt i m e l y i n t r o d u c t i o n o f a r eu s ab l e, f u l l c a p a b i li t y Space. This Space Tug will provide f o r p a y l o a d r e t r i e v a l o ro r b i t s e r v i c in g t o u l t i m a t e l y meet t h e n e ed s of a l l u s e r s .Appropr ia t ions (mi l l ions ) -- Space S h u t t l e Program

Research & Construct ionDevelcpment of F a c i l i t i e s -o t a lFY 1970 $ 12.5 $ $ 12.5FY 1971 78.5 1.5 80.0FY 1972 l G 0. 18.5 118.5FY 1973 198.6 27.9 226.5FY 1975 . 800 0 77 .0 877 U

$1,664.6 $181.2 $1,845.8

FY 1974 4'75.0 56.3 531.3


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- 10 -Space Shuttle Program Management

Overall d i r e c t i o n of the program i s i n t h e Space S h u t t l eProgram Off ice , Of fi ce of Manned Space F l i g h t , which i sr e s po n s ib l e f o r d e t a i l e d as si gn me nt o f r e s p o n s i b i l i t i e s ,basic performance requirements, c o n t r o l o f m ajo r m i l e s o n e sand f un di ng a l l o c a t i o n s t o t h e v a r i o u s NASA f i e l d c e n t e r s .The Johnson Space Center (JSC), Houston, has programmanagement responsibil i ty f o r program con t ro l , overa l lsystems engineer ing and systems in te gr at io n, and ove ra l lr e s p o n s i b i l i t y a nd a u t h o r i t y f o r d e f i n i t i o n of t h o s e e le me nt so f t h e t o t a l s ys te m which i n t e r a c t w i t h o t h e r e le me nt s,

such as t o t a l con fig ura tio n and combined aerodynamic loa ds.JSC a l s o i s res pon sib le f o r development , product ion, andd e l i v e r y o f t h e S h u t t l e o r b i t e r and manages t h e c o n t r a c twith Rockwel l In ternat ional .Kennedy Space Center, F l a . , i s r e s p o n s ib l e f o r d e si g nof launch and recovery f&: i l i t i e s , and w i l l . s e r v e as t h elaunch and land ing s i t e f o r t h e Space Shu t t l e deve lopmentf l i g h t a n d f o r opera t ion a l miss ions requ i r ing launches i na n e a s t e r l y d i r e c t i o n ,Mar shal l Space Fl ig ht Center (MSFC), Hun ts vi ll e, Ala.,i s respons ib le f o r t h e development , p roduc t ion and de l i ve r yo f t h e o r b i t e r main en g in e , t h e s o l i d b o o s te r , and t h e

hydrogen-oxygen pr op e ll an t ta nk . MSFC a l s o w i l l accomplishand /or manage ce r t a i n o ther Shu t t l e t a sk s where t h e Cente ra l s o h as u ni qu e c a p a b i l i t i e s .Launch and Landing S i t e

p o s s ib l e l a u n ch s i t e s t h ro u gh o ut t h e U ni te d S t a t e s f o rmore th an one ye ar . More th an 150 s i t e s we re c o ns ide r ed ,and 80 have been s t u d i ed i n d e t a i l f o r all p o s s ib l er e qu i re m en t s a nd c o n ti n g en c i es a p p l i c a b l e t o t h e S h u t t l e .

A Space S h u t t l e l a u n ch s i t e e v a lu a t i o n b o ar d s t u d i e d

The decis ion was made i n Apr il , 1972, t h a t :1. The i n i t i a l l aunch and recovery s i t e will be a tKennedy Space Cent er, Fl a. , and be used f o r re se ar ch anddevelopment launches and f o r a l l e a s t e r l y o p e ra t i on a l l a un he sf e a s ib l e f r o m KSC. G en er al p ur po se S h u t t l e f a c i l i t i e s f o ra l l u s e r s w i l l be provided by NASA a t KSC on a t ime schedulecompatible with the Shuttle development program.

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- 11 -

2. A second operat ional s i t e for m is sio n s r e q u i r i n gh ig h i n c l i n a t i o n l a un c he s n o t f e a s ib l e fro m KSC i s planneda t Vandenberg A i r Force Base toward the end of t h e 1970s.G en er al p ur po se S h u t t l e f a c i l i t i e s f o r a l l u s e r s w i l l beprovided by t h e Department of defense a.l; Vandenberg AirForce Base on a t ime schedule compat ible wi th progress i nt h e Shu t t le development program and t im ely u t i l i z a t i o n oft h e S h u t t l e f o r o p e r a t i o n a l m is s io n s r e q u i r i n g h i r h i n c l i n a -t i o n l au n ch e s.


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space shuttle 1974

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