a primer the u.s. manned space flight program

8/6/2019 A Primer the U.S. Manned Space Flight Program

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WHY EXPLORE THE MOON?. (Excerpt from st atem ent t o Congress March 11, 1969 byD r . George E. Mueller, NASA Asso ciat e Admi nist rator f o rManned Space light)

Let us look f i r s t a t why lu na r ex pl ora ti on i s ofgr ea t importance t o our na t ion . To the s c i en t i f i c world,t h e r e i s g r e a t i n t e r e s t i n t h e o r i g i n and h i s t o r y of t h eMoon and i t s r e l a t i o n t o t h e E ar th , and t o t h e so l a r system.Was i t formed wi th the Ear th , o r cap tured l a t e r ? Are the rec l u e s t o t h e o r i g i n of l i f e ? To qu ot e t h e , P r es i d en t 'sScience Advisory Committee, "Answers t o th e se que st io ns mayprofoundly a f fe c t our v iews of th e evolu t ion of the s o l arsystem and i t s place, as well a s man's, i n th e la r ge r schemeof things."Many p l a n e t s have moons, b u t ou rs i s t h e l a r g e s t i nr e l a t i o n t o i t s planet , This impl ies th a t the two bodies

may have been formed i n t h e same manner a t the same time.If tr ue , th e moon may be a book containing the s ec re t oft h e e a r t h ' s f i r s t b i l l i o n y e ar s o f l i f e . T hi s r ec or d i sl o s t on t h e e a r t h which i s subjec ted t o the wear and t e a rof erosion by atmosphere and water,%ti1now na tu ra l Ghenomena t h a t can a f f e c t man couldbe studied only on Earth. Now we be li e ve many t hi ng s t h a thappen on Ea rt h a l s o happen on t h e Moon. By comparing s i m i -l a r i t i e s and con t ra s t i ng d i f ference s , man may be ab le t oa r r i v e a t a g r ea t e r understanding of th e f 'undamental proces sest h a t a f f e c t t h e Ear th ; f o r example, th e mechanisms th a t causeearthquakes and volca nic er upt ion s, and th e processe s respon-s i b l e f o r concen tr a t ing o re depos i t s. The o r b i t s of Apo llo8 and t h e Lunar Orb it er s were dis tur bed by mass concentra t ionsbeneath t h e c i r c u l a r lun ar seas. These may be hugh meteorst h a t s tr uck t h e Moon with such fo rc e th a t they melted and sanki n t o t h e i n t e r i o r , o r t he y may be i r o n d e po s i ts .Another obje ct i ve of l un ar explorat ion i s t o l ea rnabout man as a space explorer- -h is ca pa bi l i t i es and l i m i t a -t i o n s . Some day man w i l l move on t o ot he r plan ets ; t h e Mooni s a t ra ining ground.I t i s d i f f i c u l t t o look f a r ahead. We do n' t have th ebas ic in format ion which e ar ly l una r land ings w i l l f u r n i s h

and we can on ly specula te today about th e fe a s i b i l i t y of t h eMoon as a base fo r an obse rva to ry o r a permanent sc ience sta-t ion--about exploi t ing i t s environment of low g r a v i t y andhigh vacuum--about i t s p o t e n t i a l f o r n a t u r a l r e so ur ce s .


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The eventual goal of a lu na r base would brin g i n t ofocus the s te ps t h a t must precede i t , Jus t as Apollo wasimportant i n es ta bl is hi ng th e o bje cti ve s of Mercury, Gemini,Surveyor, and Orbi te r . Cr i t i c a l t o fu tu re cons idera t ions ofa lunar base goal i s information on the lunar environment,loca t ion of na t ura l resources and s t ra teg ic s i t e s . th a t couldserve multiple purposes. A long-range goa l l i k e the l unarbase would di r e c t techno logical advances, st im ulat e publicin te re s t , and a t t a i n subs idia ry obJec t ives wi th Ear th appl ica-t i on such as food syn thes is, environmental con trol , and re- -covery of useful elements from rock.To summarize the points I have made, through exploringthe Moon we hope t o make fundamental advances in :1. Understanding dynamic processes on Earth throughd i r e c t comparison of t h e Ea rt h and Moon.2. Evaluati ng th e na tu r al r eso urc es of th e Moon andi t s po t e n t i a l as a base.3. Extending th e p ot en t i a l of man t o funct ion a s anexplorer on another planet ;4. Understanding the solar system and i t s or ig in ,i ncl udi ng c lue s t o t he o r i g i n of l i f e .


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APOLW HISTORICAL SUMMARY

I n i t i a l p lanning fo r a l aunch veh ic le having a payload cap ab i l i t y of theSaturn I began i n Ap ri l 1957. I n August 1958, st ud ie s concluded t h a t aclu s te red boos ter of 1.5 mil l ion pounds t hr us t was fe as ib le and the researchand development e f f o r t was begun. I n i t i a l r e s u l t s proved t h a t t h e en gi nec lus te r ing techn ique , using e xi s ing hardware, could fur nis h l arg e amountso f t h r u s t .

Rocketdyne, a di vi so n of North Amerfcan Rockwell Corp., updated th eThor-Jupi ter engine, increased i t s t h r u s t , thuo developing th e 200,000 poundt h r u s t H - 1 engine. Concurrently, from advanced st ud ie s, th e 1.5 mil l io npound th ru st F-1 engine was conceived and subse quently used a s t he powerp lan t fo r the even l a rger boos te rs .

I n October 1958, t he Army team moved t o de vel op a high-pe rformen ceboos ter fo r advanced space missions. Ten ta t ive ly ca l l ed 3uno V an d f i n a l l ydesignate d Sat urn , th e booeter was turned over t o NASA i n l a t e r 1959.I n Ju ly 1960, NASA f i r e t proposed pu bl ic ly a post-Mercury program f o rmanned f l i g h t and designated i t Pro jec t Apollo. The Apollo goal s envisione da t t h a t time were ea r t h- or bi ta l and circumlunar f l i gh ts of a three-mens p acec r a f t .During 1960, Douglas A i r c r a f t Company, In c . (now McDonnell Douglas) wass e l ec t ed t o b u i l d t h e S a tu r n I second stage (S-IV) and Rocketdyne was chosento deve lop th e hydrogen f uele d 5 -2 engine for f u t ur e upper s tage s of theSaturn vehic lea .On May 25 , 1961, Pr es id en t John F. Kennedy proposed t o Congress t h a t t heU ni ted S t a t e s a cce l e r a t e i t s space program, es ta bl is hi ng a s a n a t i o n a l g o a l

a manned luna r landi ng and re tu rn by the end of t h i s decade. In h i s re po rtt o Congress Pre sid ent Kennedy sa id :"Now i s the t ime. . . f o r t h i s n a ti o n t o t ak e a c l e a r l y l ea di ng r o l e i nspac e achievement , which i n many ways may hold th e key t o our f u t u r e one a r t h .I I.. t h i e i s not merely a rac e. Space i s open t o us now; and ou r eag er -ness ' to share i t s meaning i s not governed by the ef fo r t s of o th ers . We gointo space because whatever mankind must unde rtak e, fr e e men must fu l l yshare ."No s i ng le space pro jec t i n th i s per iod w i l l be more irnpr'essive t o man-kind or more important fo r the long-range expl orat ion of space. .


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The Saturn I B launch vehicle was successfully f lown three times i nth ree attem pts i n 1966 and is consi dered ready f o r manned ( li g h t s. Tuo ofthe se f l i gh ts c ar r ie d spacec raf t t o space where they sa t i s f ac to r i ly cornp1.etedrequirements f o r Apollo command and se rv ic e modules i n ea rt h or b i t a l opeL-ations.The f i r s t Apollo lunar module f l i gh t and f i r s t Apollo/Saturn V f l i g h t .a r ep lann ed t h i s f a l l .Ori January 27, 1967, t ragedy s t ru ck the nat ion al space e f f o r t when a f i r e

erupted in s id e an Apol lo s pac ecr af t dur ing ground te s t in g a t Cape Kennedy,re su lt in g i n th e deat hs of Astronauts V ir gi l Grissom, Edward White I1 andRoger Chaffee. A f te r two' and a half months of investigation, involving 1,500people , the Board o f l n ~ u i r y e te rmined t ha t th e most l ik e ly cause of thef i r e waa e le c t r i c a l a rc ing from ce r ta in spacecra f t w i ring . Af te r the Boardof Inq uir y 's re po rt t o Congressional committees, th e National Aeronautica andSpace Administ ra t ion followed with det ai l ed de scr ip t i ons of corr ect ive act io ns ,schedule modif ic at io na , and c o s t ea tim ate s neceseary t o move t he program towardi t s obiec t ive .

On November 9, 1967, th e f i r s t f l i g h t t e s t of the Apollo/Saturn V spacevehic le was successfu l l y accomplished. Designated Apollo 4 , th e unmannedf l i g h t demonstrated performance of t he previously unflown f i r s t and secondSatu rn V s t a g e s, t h e r e s t a r t - i n - o r b i t c a p a b i l i t y o f i t s th i rd s tage ', t heApol lo spacec ra f t a b i l i t y to r ee n te r Ear th ' s a tmosphere a t lunar miss ion re tu rnspeeds , performance of the in teg rated space veh icl e , and the operat iona l readinessof Kennedy Space Center Launch Complex 39. A l l mission obj ec ti ve s were metfol low ing an on-time laun ching and an 8-hour 37-minute mis sion. The Saturn Vplaced a t o t a l weigh t i n t o o r b i t o f over 278,699 pounds a f t e r a near per fe c tcountdown. The spa cec raf t he at shie ld performed sa t i s f ac to r i ly dur ing the24,800 m i l e per hour plunge i nt o Ear th ' s atmosphere.

During t he J anua ry 22-23, 1968 Apollo 5 mission, lunar module systems ands t ru c t u r a l per fo rmance met a l l o b j ec t i v e s , i n clu d in g two f i r i n g s of b oth t h eae cen t and de sc en t pr op ul si on systems. The unmanned Lunar Module I was boostedi n t o E ar th o r b i t by a S a tu r n I B . Post - f l i ght ana lys is determined the lunarmodule ready f o r manned Eart h o r b i t a l missions.

The Apr i l 4 , 1968 f l ig ht of Apollo 6 was the second unmanned Saturn Vmission t o demonstrate, launch ve hi cl e and spac ecr aft systems performance.Two problems were exp er ie nc ed wit h the rocket systems -- v e r t i c a l o s c i l l a i o n so r "POGO" e f f e c t i n t h e f i r e t s t ag e and r up t u r e of s ma ll p r op e l la n t l i n e s i nthe upper s tages - - i n an otherwise, very success ful miss ion.The precise reentry end splashdown on October 2 2 , 1968 of th e 11-dayApollo 7 f l i g h t ended what was ca ll ed a 101 perce nt su cce ssfu l mission.Manned by Astronauts Walter Schirra, Donn Eisele, and Walt Cunningham, theApollo 7 performed fl aw le ss ly f o r more than 780 hours i n space , inc lud ing 8f i r i ng s o f th e spacecra f t ' s p rimary propuls ion system and the f i r s t l iv e TV

from a manned vehicle .


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-6-Apollo 8 l i f t e d o f f p re c is e' ly on time, December 2 1 , 1968 from the

Kennedy Space C ent e r fo r h i s t o ry ' s f i r s t f l i g h t f ro m Kart h t o an ot l le rbody i n t h e s o l a r s y st em . Ap o l lo 8 perfo rmed f law less ly f o r 147 hoursa nd o v e r a h a l f m i l l i o n miles o f s p ace f l i g h t whi ch i n c l u ded t e nre vo lu t i on s around th e Moon, luna r and Ear th photography, and l iv at e l e v i s i o n b r oa d ca s ts .

Apollo 9 splashed,down i n t h e A t l a n t i c Ocean, n o r t h ea s t o f Pu e r t o Ri co,a t 12 :00:53 EST, March. 13, 1 9 6 9 , a f t e r a 10-day , 6-mil l ion mile Ear tho r b i r a l m is si on . . ALL rnaj o r m i s s i o n o b j ec t i v e s were-met i n t h e Eirsc 5d a y s o f t h e f l i g h t . A p ol lo 9 b as t h e f i r s t al l -u p rranned f l i g h t o f t h eAp o l l o Sa t u rn V s p a c e v e h i c l e , f i r s t manned f l i g h t o f the lunar module, .f i r s t Apo110 EVA, and incl ud ed rendezvous and dockin g, l i v e te Levi.sior.,pho tograph ic su rveys o f E ar th , artd obse rva t ion o f Pegasus I1 s a t e l l i t ea n d J u p i t e r . T h i s was t h e fo u r t h Sa t u rn V on-time launch (1l:OOam EST).


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APOLLO LUNAR LANDINGS

Primary ob jec t i ve of the f i r s t Apollo lunar landingmission i s t o prove th e Apollo system by ach ie vin g a suc-ce s s fu l Moon landing and s a fe r et ur n t o Earth.During the f i r s t landing , p lans c a l l fo r the twoas t ro nau ts t o leave the s pacecraf t and spend up t o th r eehours on the Moon1s surface. During t h i s t ime. they w i l lmake observa t ions and photograph the a re a i n th e v ic in i t yo f the l anded spacec ra f t in add i t ion to co l l ec t in g thesamples and deploying s c i e n t i f i c instruments.The astronauts w i l l per form t he i r task s i n an order ofincreasing complexity. A t each l e v e l o f a c t i v i t y , s c i e n t i f i cand medical da ta on th e expenditur e of energy by th e as tr o-nau t s w i l l be obtained . This w i l l ensure adequate monitoringof t h e i r a b i l i t y t o perform i n th e vacuum, extreme temperature

and one -s ix th g r a v i t y of t h e Moon and w i l l provide importantdata which w i l l permit the planning of longer and more com-p lex miss ions f o r the fu tu re .The s c i e n t i f i c exper iments, Ear ly Apollo S c i e n t i f i cExperiments Payload (E ASEP ),a r e a passive seismometer, alaser ranging re t ro- ref ] -ec tor and a s o l a r wind compositionexperiment.The passive seismometer i s a self -contained seismics t a t i o n w ith i t s own Earth-Moon communications link. I t i spowered by s o l a r c e l l s and may be provided with ra di oi so to peh e a t e r s t o e na bl e it to survive the extremely cold lunar

n i g h t s f o r up t o a year . It w i l l provide da ta on the in te rn a la c t iv i t y of the Moon.I f t h e Moon i s se ismica l ly ac t iv e , in format ion on i t sst ru c tu re can be obtained. These da ta w i l l as s i s t i n d e t er -mining the va l i di ty of cu rre nt concepts about t h e Moon and i t so r i g i n and perhaps le ad t o new concepts. D r . Gary Latham ofColumbia Un iv er si ty 's Lamont Geolog ical Observatory, Pa lis ade s,N.Y., i s experimenter.The laser r ang ing r e t ro - r e f l ec to r i s a wholly passiveexper iment co nsis t ing of an ar ra y o f p r e ci s i on o p t i c a l r e -f l ec to rs which serve as a ta rg e t f o r Ear th-based la s e r sys tems.Data obtained w i l l improve th e measurement of Earth-Moon d i s -t ances and the f luc t ua t io n o f the Ear th ' s ro t a t i on r a te .


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Measurements of the. v ar ia ti on s i n t he g r a v i t a t i ona lcons tant "G" a l s o w i l l be improved. The theo ry of in t e r -con t ine ntal d r i f t can be te st ed by d i r e c t measurements fromdi f fe ren t con t inen t s . D r . Car ro l l 0. Al ley of the Universi tyof Maryland, College Park, and Dr . Donald Eckhardt of theA i r Force Cambridge Research Labora tory, Cambridge, Mass,,have.experiments of t h i s type under development.The s o l a r wind composition experiment i s designed toen t rap the noble gases ( ~ e l i w n ,Neon, Argon, Krypton, xenon)i n t h e so l a r wind. It cons i s t s o f a sh eet o f aluminum f o i lwhich i s placed ac ros s t he so la r wind. It i s re t r ieved beforethe a st ro nau ts leave th e Moon and r etur n to Earth f o r analys is .The one-pound experiment i s developed and funded by t he Swissgovernment. D r . Johannes Geiss of th e Unive rsi ty of Berne i sexperimenter.

On th e second, th i r d and fo ur th lu na r landin g missions,NASA pla ns t o have t h e as tr on au ts deploy a fill geophysicals t a t i o n o r Apollo Lunar Su rfa ce Experiments Package (ALSEP)and conduct a de ta il ed f i e l d geology inve stig atio n. ALSEPinstrumentat ion w i l l provide fo r passive and act iv e lun arsei sm ic experiments, lu na r t r i - a x i s magnetometers, medium andlow energy solar w i n d experiments, suprathermal ion detectorsand cold cathode io ni za ti on guages.

Lunar surface samples returned to Earth w i l l be thoroughlyanalyzed by 142 s c ie n t is t s and the d ata made avai lab le t o theworld s c i e n t i f i c community.


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ESTINITL- COST OF IU\SA bIA134KD LUtUUt U I I D I N G 1?OCRAM(~anww y 969)

A p u ~p8cecraft--------.I--------..-----w--------.--~--..Saturn 1 hunch Vehicles------------------------------- $7,945,000,000767,100,000a t u r n IB 1,131,200,000Saturn V bunch Vehicles------------------------------- 6,871,100,000hunch Vehicle Engine Development---------------------- ~~G , xx ) , o o oMission Supp3rt------------------------,432,300,000I 'rackdn~ nd k t a AcqUisiti~n------------------------ 664,l00,000eound F~~il~tie~----~------------------ 1,830,3009000Operation of Installations----------------------------- 2,h20,600,000

TOTAL $23,915,900,000

MERCURYS p c e c r ~i . .. . .o--U ~.I--)---------------------------35,300,000bunch vehicles-------------.------------------------- 82,900,000Operation~~~~~~---~----~------------..---------~------ 49,300,000Tracking Operations and Equipment--------------------FaC i ~ t ~ e s ~ ~ ~ ~ - - - ~ - ~ - o . - - - - ~ - - - - ~ - - - - ~ - - - - - - - - - - - - . - ~

71,900,000--POLIO MISSION COSTS(included i n To tal Estimated Cos t s , above)Awllo 7-ll-----------I----I--------------------------III.I- $145 a ill ionApQyJo8.I.- UC ----..-I--..-..---..---~~----------------~~-- 310 nlillionAp33J-0+-----....---..--------------..-------..------..--~---~-110 nlinionApollo 10 and subsequent; lunar missions-------------------- 350 riU.lon


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MissionDesignationApollo Saturn I B(As-m)

Apollo Saturn I B(AS-203 1

ApoUo Saturn I B(AS-202)

Mission13atesFebruery 26, 1966

July 5,1966

August 25, 1966

November 9, 1967

Mission D e ~ f l r f tion--Unmanned, suborbital, space vehicle developent f l i gh t,demonstrated space vehicle compatibility and structuralintegr i ty; spececraft heat shield qual i f icat ion forEarth orbital reentry speeds,--Unnamed, orb ita l, launch vehi.cle develo ment f l i g h t;

demonstrated second stage restart and cryogenicpropellants storage a t zero g conditions, Liquidhydrogen pressure test.--Ummnned, subor bit al, space ve hi cl e developuent f li g h t;demonstrated structural integrity and compatibility,spacecraft heat shield performance.--First ApoLLo Saturn V fli gh t, unmanned, Earth or bi ta l tU,234 miles apogee, space vehi cl e development fl ig h t.Demonstrated Saturn V rocket performance and Apollospacecraf't heat s hie ld fo r lun ar mission re en try speeds

January 22-23, 1968 --Firs t ApoUo lun ar module fl i g h t on Saturn IB , unmamedEarth o rb it a l, Demonstrated spece cra ft systems performascent and descent stage propulsion fir ings and restarta n d s t a g f r ~ ,

--Second fU g h t of Saturn V, unmanned, Eart h or b it a l,launch vehicle d e v e lo p n t f l ig ht , DemonstratedSaturn V r oc ke t p e rf o rm m e =d A ~ l l op c e c r a f tsubsystems and heat shield performance.


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MissionDesignation MissionDates Mission Description~ c t o b e r.1.022, 1968 --F irst manned Apollo fl ig n t, Earth orbital, demonstratespacecraft, crew and support element performnce, Higsuccessful f l ight Lasting 10 days 20 hours, including8 najor propulsion system fir in gs and fi r s t l i v e Wfrom manned spcecraft.December 21-27, 1968 --History's first manned fl ig ht from Earth t o another bodi n so lar system; included 1 0 revolutions aixmnd the Mo(20-hour period) and safe retu rn t o Earth, TV andphotography of Moon and E~rth y astronauts,March 3-13, 1969 . --Apollo 9 was ' t he f i r s t all-up manned fl ig ht of the ApoSaturn V space vehicle, f i r s t manned flight of the lunmodule, f i r s t Apollo EVA, and included rendezvous anddocking, l iv e tele vis ion , photographic surveys of Eart

and observation of Pegasus I1 sa t e l l i t e and Jupi t e r ,All mission obJectives successfully completed,


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AI'OLU) APPLICATIONS PROGRAM

The A pol lo App l i ca t on s Program, th e Na ti on a 1 Aeronautics and Space.dm ini s t ra t io n ' s manned f l i g h t program t o fo l low the lu nar lan< li .ng ,w i l lco ns is t of long dura t i.on i..;lrth o r b i t a l miss ions duri r rg which as t ro nau tsw i 11 c a r ry o u t s c i e n t i f i c , echnologica 1 and engi neer ing exper iments .

The Satu rn launch ' rehic les and spa ce cr af t developed f o r t he Moonexplor- t ion program w i l l he mo.1j.Eied t o provide th e c ap ab i l i t y fo r c rewst o r em ai n i n E a rt h o r b i t f o r up t o 56 days .

The f i r s t phase of th e Apol lo Appl i ca t ion s l 'rogrem w i l l be theSa tu rn Workshop mis sio ns planned fo r 1971 and 1972. The workshop,c o n s i s t i n g O F a m od if ie d S a tu r n upper s t a ge , a i r l oc k and doc king a da p te r ,w i l l pr ov ide L iv ing qu a r t e r s and l a bo r a to r y a r e a f o r t h r e e men t o o r b i tt h e E ar tl r. T hr ee v i s i t s t o t h e workshop a r e p l an ne d , t h e f i r s t o f 28 daysdu ra ti on and two o'f up t o 56 days . O r b i ta l a l t i t u d e w i l l be a bou t 200. n a u t i c a l m i l e s .

S c i e n t i f i c , en g i n e er i n g , t e ch n o lo g i ca 1 and biomedical experi .ments ar ep la nn ed t o b e c a r r i e d o u t i n t h e S a t u r n I Workshop. Includ-ed a r e exper imentsfo r t he Department of Defense i n supp or t of i t s Manned Orbiting LaboratoryP rogr am . S c ie n t i f i c e xpe r im e nt s o f spe c ia 1 i n t e r e s t a r c m ul ti -b an d E ar tht e r r a i n p h ot og ra ph y an d t e l e s c o p e s t o o bs e rv e t h e a c t i v i t i e s o f t h e sununobs t ruc ted by the Ear th ' s a tmosphere . Much attenti.on w i l l be g iven tobiome dical experiments t o i nv es ti ga te how t he hunlan b


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The workshop w i l l be launched unmnnned. Af te r achiev ing or b i t , th esecond s tage w i l l be purged of r es id ua l p 'kopellants and t he hydrogen tankpr e pa re d f o r p r e s su r i z a t i on . One da y l a t e r a se cond S a tu r n I B w i l l o r b i ta c re w o f t h r e e a s t r o n a u t s i n an Apo llo connnand and s e r v i c e module.

A f t e r R r endez vous m aneuver ' s i m i l a r t o those c a r r i e d ou t in the Geminip rogr am , a s t r o na u t s w i l l doc k t he s pa c e c r a f t w i th t he workshop a ndp r e s s ur i z e t h e a i r l o c k a nd h y d r o ~ e n a nk . Af te r p r e s s u r i z a t i o n i s accomp-l i s h e d , t h e crew w i l l e n te r th c hydroge n t a nk th rough tunne l s in the dock ingad ap te r and ai r l o c k and i ns ta l .1 food arid waste management s ystem s, a rra ng et h e i r p e r sona l e quipm en t and p r e pa r e t he e xpe r ime n t s .

P l an s c a l l f o r t h e f i r s t c re w t o rem ain i n o r b i t f o u r weeks. B ef or eundocking t h e commnd module f o r t h e E a r t h r e t u r n t r i p , t h e workshop w il l .b e pr e pa r ed f o r t h e n e x t crew v i s i t .

About two months l a t e r th e second crew w i l l f e r r y t o t he workshopi n an Apol lo spa cecra f t ' launched by a Sa tur n I B . An ex te n si ve numbero f m e di c al e x p e ri m en t s a r e p la nn ed f o r t h i s m i s s io n o f a b o u t 56 daysd u r a t i o n . Addi t iona 1 e n g i n e e r i n g a nd s c i e n t i f i c e xp er im e nt s a l s o w i l l b einc uded .

The th i r d v i 8 j . t t o t he workshop w i l l r e qu i r e l a unc h ing o f two S a tu r nTB v e h i c l e s . F i r s t , t h e t hre e-m an c re w w i l l b e l a un ch ed t o r e a c t i v a t eth e workshop and checkout i t s sys tems. A few da ys l a t e r , a no the r S a tu r n IRw i l l o r b i t t h e unmanned Apo l lo Te lesc ope Mount, mated t o th e a sc e n t s t a geof an Apol lo lunar module.

The telescope mount wi 11 be co~nmanded t o rendezvous wi th th e workshop.When i t approaches wi th in a few hundred fe e t of t he workshop, th e as t ro nau tsw i l l dock t he ve h ic l e by r a d io commands in to one of th e ha tc he s i n thed o ck i ng a d a p t e r l o ca t ed a t a 90 deg ree a ng le t o t h e docked command module-workshop spacecra f t .

Through a c on so le i n th e luna r moduLe c a b i n the a s t r o na u t s w i l l v i s ua l l ys c an t h e s u n , s e l e c t a r e a s o f i n t e r e s t o n which t o a c q u i r e d a t a and p o i n tthe in s t r um e n t s a c c o r d ing l y , wh i l e c on t inu ing t o m oni tor much o f t he so l a rd i s c . P h o to g r ap h i c f i l m wi 11 be r e p la c e d a nd r e t r i e ve d th rough e x t r a ve h ic u l a r .a c t i v i t y .

The Saturn I workshop missions w i l l y i e ld a we a l th o f in f o r m at ion ont h e c a p a b i l i t y o f nmn t o l i ve a nd work i n spa c e ; type s o f e quipm en t be s tsu i t e d f o r work ing i n spa ce , t ype s o f to o l s ne eded t o m a in ta in a nd r e pa i rspa c e equipm en t a nd , ve r y poss .lb ly, unEore se en s c i e n t i f i c da ta o f g r e a ts i g n i f i c a n c e .


15/83

-14-LUNAR DESCRIPTION

T e r r a i n - Mountainous and cra te r- pi t t ed , t h e formerr i s i n g t h o u s a n d s of f e e t and t h e l a t t e r r an gi ng from a fewi n c h e s t o 180 m i les i n d i amete r. The c r a t e r s a r e t hough tt o be formed by th e Impact of mete ori t es. The su rf ac e i scovered wi th a l a ye r of f ine-gra ined ma ter ia l resembl ing3i1t o r s and, as w e l l as small rocks.

Environment - No a i r , no wind, and no mo is tu re . Thetemper ature ranges from 250 degree s i n th e two-week lu na rday t o 280 deg ree s below ze ro i n th e two-week lu na r nig ht .Grav i ty i s one-s ix th t h a t of Earth. Micrometeoroids p e l t th eMoon ( t h e r e i s no atmosphere t o burn them up). Radiation mightp r e s e n t a problem du r ing pe r iods of unusual s o l a r ac t i v i t y .Dark Side - The dark o r hidden s i d e of t h e Moon no long er

i s a complete mystery. It was f i r s t photographed by a Russianc r a f t and si nc e the n ha s been photographed many t imes, pa rt ic u-l a r l y by NASA's Lunar O r b it e r spa ce cr af t.O r i g i n - There i s s t i l l no agreement .among scient is tson t h e or ig in of t h e Moon. The th re e the ori es : (1 ) the Moononce was p a r t of E a r t h and s p l i t o ff i n t o i t s own o r b i t , (2 )i t eyolved as a sep ara te body a t the same time a s Earth , and( 3 ) I t formed elsewhere i n space and wandered u n t i l it wasc a pt u re d by E a r t h ' s g r a v i t a t i o n a l f i e l d .

Phys i ca l Fac t s

Diameter 2 ,160 mile s (about t h a t of Ea rth )Circumference 6,790 mi les (abou t $ t h a t of Ea r th )Dist anc e from Ea rt h 238,857 miles (mean; 221,463 minimumt o 252,710 maximum)Surface temperatureS u rf a ce g r a v i t yMassVolumeLunar day and nightMean ve l oc i t y i n o r b i tEscape ve loc i t yMonth (period of r o t a t i o naround Earth)

250 (sun a t zen i th ) -280 (n igh t )1/6 t h a t o f E a rt h1/100th that of Ear th1/5Oth t h a t of Ea rt h14 Ear th days each2,287 miles per hour1.48 miles per second27 days, 7 hours, 43 minutes


16/83

LUNAR SITE SELECTION

The f i r s t Americans on t h e Moon w i l l l and i n one off i v e three-by-f ive-mile landing ar ea s sel ect ed by t h e NationalAeronaut ics and Space Administra t ion 's Apollo Si t e Sele ct i onBoard.

Each of t h e f i v e l an di ng a r e a s s a t i s f i e s c r i t e r i a i nwhich astronaut safety i s the paramount consideration.

The places selected are e l l i ps es around the fo l lowingce n tr al poi nts on th e fa ce of th e Moon:

S i t e 1. 34 degrees E a s t ; 2 degrees , 40 minutes North.S i t e 2. 23 degrees, 37 minutes' E a s t ; 0 degrees, 45 min-

utes North.S i t e 3. 1 degree, 20 minutes West; 0 degree s, 25 minut esNorth.S i t e 4. 36 degree s, 25 minutes West; '3 d egrees , 30 min-utes South .S i t e 5. 41 degrees, 40 minutes West; 1 degree, 40 minutesNorth.


17/83

T h e . f i r s t two s i t e s a r e i n t h e Sea of T r a n q u il l i t y,t h e t h i r d i s i n t h e S Ce n t r alBay and t h e f o u r t h and f i f t h a r ei n t h e Ocean of Storms.

The f i v e were se lec ted from eig ht under s tudy from achoice of 30 o r i g i n a l s i t e s . S e le c ti o n of th e f i v e w i l l per-m i t s c i e n t i s t s and e n gi n ee r s t o c o n c en t ra t e on t h e f e we r a r e a si n p re pa ri n g d a t a on t h e s p e c i f i c s i t e s .

The Board. st ud ied ma'terial obtained by unmanned LunarOr bi te rs and soft - landin g Surveyor spacecr aft . Lunar Or bi ter

' re turned h igh reso lu t ion photographs of a l l t h e s i tes andSurveyor provided c lose-up photos and surf ace da ta of t h egene ra l a re a s i n which they a r e l oca t ed .

Fo l lowing .a re t he c r i t e r i a cons ide red by t he Board:--Smoothness of are a. The s i t e s should have r e l a t i v e l yfew c r a te r s and boulders ;

--Approach path. There should be no l a r g e h i l l s , hi ghc l i f f s o r de ep c r a t e r s which would c a us e i n c o r r e c t a l t i t u d es i g n a l s t o t h e l an di ng radar;

--Propellant. The s i t e s were s e l e ct e d t o a ll ow f o r t h eexpendi ture of t h e le a s t amount of prope l lan t by t h e l u n a rmodule propulsion Bystems.


18/83

--Recycling dur in g countdown. The s i t e s were selectedt o a l low fo r the recycl ing time of the Apol lo /~atur nVnecessary if t he countdown f o r launch a t Kennedy Space CenterIs delayed;

--Free re tu rn . The s i t e s must be within reach of theApollo spacecraf t i n the "free-return" t ra jec tor y . On t h ef r e e - r e t u r n t r a j e c t o r y a spacecraft would coast around theMoon and re tu rn sa fe ly t o Earth without req uiri ng t he operat ionof propulsion systems;

--Lighting. For optimum v i s i b i l i t y by th e as tr on au tst h e s i t es w i l l have a Sun-angle of 7-20 deg rees behind t helu na r module as i t approaches the landing;

--Slope. The general s lope of the landing area and theapproach t o th e landing s i t e must be l ess than two degrees.

A l l s i t e s are wit hin th e Apollo Zone of I nt er es t- -t ha tar ea of th e vi s i b l e s id e of th e Moon within 45 degrees eas tand west of t h e ce nt er of t he Moon, and fi v e degrees no rthand south of i t s equator.

The desired Sun-angle range of 7 t o 21 degrees re su l t si n a one-day launch opp or tu nit y pe r month f o r a g i v e n s i t e .

Before f l i g h t t o the Moon, th re e of t he f i v e s i t e s w i l l bechosen f o r . th e sp ec i f i c mission . This w i l l make a three-dayperiod each month av ai la bl e f o r launching th e prime Apollof l i g h t .


19/83


20/83

-18-APOLLO SPACECRAFT DESCRIPTION

COMMAND AND SERVICE MODULE STRUCTURE, SYSTEMSThe Apollo spacecraft i s comprised of a Command module,s er v ic e module, lu n ar module, a spacecraft- lunar modulead ap te r (SLA) and a laun ch escape system. The SLA serv es

as a mating s t r uc tu re between th e ins t rument u n i t a top t heS-IVB s t ag e o f the Sa tu rn V launch vehicle and as a housingf o r th e lu na r module.

Launch Escape System (LES) --Prop els command module t o s a f e t yi n an abor ted launch. It i s made UD of an o~e n-fr ame towers t r u c t u r e mounted t o t h e command mobule by f b u r fr an g ib le b o lt s ,and thr ee s ol id -pro pel l ant rocket motors : a 147,000 pound-thrustlaunch escape system motor, a 2,400-pound-thrust p i t c h con tro lmotor and a 31,500-pound-thrust tower j e t t i s o n motor. Two canardvanes n ea r t h e to p deploy t o t u rn t h e command module aerodynam-i c a l l y t o an a t t i t ud e with the heat - sh ie ld fo rward. A ttached t oth e base of t h e launch escape tower i s a boost protec t ive covercomposed of g la s s, c l o t h and honeycomb, t h a t p r o t e c t s th e commandmodule from rock et ex haus t ga se s from th e main and t h e j e t t i s o n .motor. The sy st em 'i s 33 f e e t t a l l , f o u r f e e t i n dia me ter a t t h ebase and weighs 8,000 pounds.Command Module (CM)Struc ture--The bas ic s t ru c t ur e of thecommand module i s a pressure vessel encased i n hea t - shie lds .cone-shaped 12 f e e t high, base diameter of 12 f e e t 10 inche s, and

., lau nc h weight 13,000 pounds with crew.The command module c o n s i s t s of th e forward compartment whichco nt ain s two negative p it c h rea cti on co nt ro l engines and compo-nen ts of th e Earth lan ding system; th e crew compartment, o r in n erpr es su re ve ss el, con tain ing crew accommodations, co nt ro ls anddisplays , a n d sp ace cra ft systems; and t h e a f t compartment housingten reac t ion cont rol engines and prope l lant tankage .Heat-s hield s around th e t hr ee compartments a r e made of brazeds ta in le ss s t e e l honeycomb wi th a n ou te r la y er of ph enolic epoxyr e s i n as an ab la t i ve mater ia l . Hea t - shie ld th ickness , varyingaccording t o hea t loads , ranges .f rom 0.7 i n ch e s ( a t t h e a pex ) t o2.7 in ch es on th e a f t s ide .The spacec ra f t i nn e r s t ru c tu re i s of aluminum alloy sheet-a luminum honeycomb bonded sandwich ran gin g i n th ic kn es s from 0.25i n c h es t h i c k a t forward acc ess tunnel t o 1.5 i n c h e s t h i c k a t base.

Docking hardware consists of a probe assembly, a fo ld ingcoup ling and impact at te nu at in g devic e, mounted on th e CMtunne l t h a t mates wi th a conical drogue mounted on the LMdocking tunnel. Af ter th e docking l at ch es a r e dogged downfol lowing a docking maneuver, both th e probe and drogueassemblies are removed from the vehicle tunnels and ntowed t oallow f re e crew tr an sf e r between the CSM and LM.


21/83

@BALL (TiOSE CONE)-, PITCH CONTROL MOTORJETTISON MOTOR

STRUCTURAL SKIRTtAUNCH ESCAPE TOWER

7W"ER ATTACHMEtST (4)COMMAND MODULEBOMT PRDTECTIVE

EPS RADIATORREACT1071 COXROLSYSTEM: EtlGIXES

SERVICE MODULEECS RADIATOR

SPS ENGIriE EXPANSION NOZZ

SLA PANEL JUNCTION.(BETWEEN FAD AND AFTPANELS)

INSTRUMENT UNIT(SHOWN AS ,REFERENCE)1 1

SPACECRAFT CONFIG34ATION


22/83

C C l l A P l N f T ! TI IPIPJI L 44tC*J

LAtJtlCU f 5CAPt TO'UI RA T T A C ~ ~ ~ P I ~~ Y P I ~ L :

' SIDE WINDOW(1WICAL 7 PUCEI

ror,uAm v ~ rc ~ ~ c ,~RfNOtZVOtJSlWINDOW

a primer the u.s. manned space flight program

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