apollo saturn lunar landing program

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Frogme n secure flotation collar around Spacecraft 009 in recovery af ter high-heat re-entry test.

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APOLLO PROGRAM

Apollo i s the Unit ed States program to land menon the moon for s cie nti fic exploration and returnthem safely to earth. I t has been described as thegreatest scientific , engineering, and exploratory

challenge i n the history of mankind.

The challenge essentially was to create an ar ti fi -ci al world: a world large enough and complexenough t o s upply a l l the needs of three men for twoweeks. A par all el problem was to deve lop a boosterlarge enough to put this world into space and to sendi t on its way t o the moon 250,000 miles away.

NASA announced the program and its o bjectives i nJuly of 1960. More than a year later (N ov . 28,1961), aft er a series of studies on the fea sib ili ty ofthe proiect, NASA awarded the basic Apoll o con-tract to North American Aviation's Space Division.

Development of the booster-the Saturn program-wasbegun in lat e 1958 under the Advanced ResearchProjects Agency.

Briefly, the program i s to send a three-man space-cra ft to the moon and into orb it around it, land twoof the three men on the moon while the third remainsi n orbit, provide up to 35 hours of explorat ion on themoon, retu rn the two moon explorers to the orb iti ngspacecraft, and retu rn a ll three safely to earth. Theentiretrip, from launch to earth landing, i s expectedto last about 8 days; th e Ap ol lo spacecraft has beendesigned for 14 d ay operation to giv e a wide marginof safety.

The program i s the most extensive ever undertakenby any government. More than 20,000 companiesand 300,000 persons throughout the country haveparticipated in it. North American i s principal con -trac tor for the spacecraft's command module, servicemodule, laun ch escape system, and spacecraft -LMadapter. The LM (lunar module) contract or i s Grum-man Ai rc ra ft Engineering Corp. Associate contractorsare Massachusetts Inst itut e of Technology, for theguidance and nav iga tio n system, and Da vid ClarkCo. and Inte rna tio nal Latex Co., for space suits.

1 M A N

MERCURY

PAYLOAD (LB)3,500

LAUNCHVEHICLE ATLAS

THRUST (LB) 360,000

GEM INI APOLLO

7,000 250,000

TITAN ll SATURN

430,000 8,700,000

Manned spacecraft

The Saturn program invo lves two separate launch

vehicles: the Saturn IB , a two-stage vehicle w it hato ta l thrust o f 1,800,000 pounds, wh ic h i s used foreart h-orb ital missions of the Apol lo program; andthe Saturn V, a three-stage vehicle with a totalthrust of 8,700,000 pounds, whic h w i l l be used forsome ear th- orb ita l missions and for the lunar mis-sion. Saturn I B contrac tors are: Chrysler Corp., forthe firs t stage; Mc Do nn el l Douglas Space SystemsCenter, for the second stage; and IBM, for the instru-ment unit. Saturn V contractors are: Boeing Air -craft, for the first stage N ort h American Rockwell'sSpace Div isi on for the second stage; Mc Do nn el lDouglas, for the th ir d stage; and IBM, for the instru-ment unit.

The Apollo program s under the technical d irecfi onof the Off ic e of Manned Space Flight, HeadquartersNAS A. The Apol o spacecraft program i s directed byNASA's Manned Spacecraft Center in Houston, Tex.The Saturn program i s under the technical directionof NASA1sMarshall Space Flig ht Center i n Huntsville,Ala.



LAUNCHESCAPE SYSTEM

BOOST

PROTECTIVE COVER

C O M M A N D M O DU LE

SERVICE MODULE

ADAPTER

LUNAR MODULE

Apollo spacecraft and Saturn V space vehicle.



COMMAND MODULE

This is the control center for the moon flight; i t

provides living and working quarters for the three-man crew for the entire flight, except for the periodwhen two men wi l l be in the LM for the descent tothe moon and return.

The C M consists o f two shells: an inner crew corn-partment and an outer heat shield. The outer shelli s composed ~ r i m a r i l ~ f stainless steel honeycombbetwe en stainless steel sheets, covered on the out -side wit h abla tiv e material (heat-dissipating materialwh ich can be burned away dur ing re-entry). Theinner shell i s constructed primarily of oluminumhoneycomb betwe en oluminum al lo y sheets. Thetwo shells are fastened rig id ly together, wi th a two-layer insulation (micro-quartz fiber) i n between.This construction i s designed to make the CM as li gh tas possible yet st il l rugged enough to stand the strain

of acceleration during launch and return to earth,the shock and hea t of re-entry, the force of landing,and the ~os sib le mpact of meteorites during flight.

Inside, i t i s a compact but eff icie ntly armngedcombination cockpit, office, laboratory, mdi o sta-tion, kitc hen , bedroom, bathroom, and den. Itswal ls are lin ed wi th instrument panels and consoles,and its cupboards (bays) contain a wide varietyofequipment. The cabin w i l l be a ir conditioned to acomfortable 75 degrees. The atmosphere w i l l be100-percent oxygen, and the pressure w i l l be 5 poundsper square inc h (a l it tl e better than one-third ofsea-le vel pressure o f 14.7 pounds per square inch).

DOCKING PROBE

FORWARD HEAT SHIELDARENDEZVOUS

WINDOWS

- / /cRwCCESS

SIDE WINDO W(TYP 2 PLACES)' -1

Command module

'ACE RADIATOR

H I G H - G A I NA N T E N N A

SERVICEPROPULSIOENGINENOZZLE

Service module

The C M i s equipped with controls to enable thecrdw to guide i t during flig ht. Test equipment w i l lgive the crew means of checki ng out malfunctions i nspacecraft systems. Television, tele me try and trac k-ing equipment, and two-way radio w i l l pro videcom -munication with earth and among the astronauts dur-ing moon explo ration and the moon or bit 'rendezvous.

These and othe r systems, such asthe re ac ti on control ,earth landing, and parts of the environ menta l con-trol, and el ec tr ic al power systems, occupy almostevery inch o f avail abl e space in the module.

Althou gh crewmen can move about from one sta-tion to another, much o f their time w i l l be spent onthei r couches. One o f the couches can be foldeddown so the crewman can stand o r move around.Space by the center couch permits two men to standat one time. The couches are made o f steel framingand tubing and covered wi th heavy fireproo f fiber-glass clo th. They rest on eigh t crushable honeycombshock struts whi ch absorb the impact o f landing.Control devices are attached to the armrests.



S E RV I CE MODULE

The service module's function , as its name implies,i s to support the command module and its crew. I thouses the el ec tri ca l power system, reac tion controlengines, and part of the environm ental con tro l sys-

tem, as wel l as the main propuls ion engine for retur nfrom the moon and for midcourse correction.

The SM i s constructed prim arily o f aluminum a lloy.

Its outer skin i s constructed of aluminum honeycombbetween aluminum sheets. Propella nts (hydrogen andoxygen) and vario us systems are housed i n six wedg e-sheped segments surrounding the main engine.

The service module i s attached to the commandmodule unti l just before earth entry, when i t wi ll bejettisoned.

L U N A R M O D U L E

The L M w i ll carry two men from the orbitin g CSMdown to the surface o f the moon, p rovid e a base otoperatio ns on the moon, and return the two men to arendezvous wit h the CSM i n orb it. Its odd appear-ance results in part from the fa ct that there i s nonecessity for aerodyna mic symmetry; the L M i s en-closed du ring launch by the spacecraft-LM adapter(a smooth aerodyn amic shape), and ope rates on ly inthe space vacuum or the hard vacuum of the moon.

The LM structure i s div ide d int o tw o components:the ascent stage (on top) and the descent stage (atthe bottom). The descent stage consists pr im ar il y ofthe descent engine and its propellant tanks, theland ing gear assembly, a section to house scien tifi cequ ipm ent for use on the moon, and ext ra oxygen,water, and heli um tanks.

The ascent stage houses the cre w compartm ent(which i s pressurized for a shirtsleeve environmentl ik e the command module), the ascent engine andits propella nt tanks, and a l l the crew controls. I thas esse ntia lly the same kin d of systems found in thecommand and service modules, inc lud ing propulsion,environm ental control, communications, and guid-ance and control.

Portable scien tific equipment carried in the L Mw i l l inclu de such things as an atmosphere analyzer,instruments to measure the moon's grav ity, magn eticfield, and radiation, rock and soil analysis equip-ment, a seismograph, a soil temp erature sensor, andcameras (including television).

After separating from the command module in lunarorbit, the L M lands on the moon using its descentengine . I t provides she1 er and a base o f operationsfor its two crewmen for the lunar stay of up to 35

hours. Aft er the lunar exploration, on ly the LM'sascent stage returns to o rbi t and rendezvous w it h theCSM; the descen t stage serves as a laun ch pla tfo rmand i s le ft on the moon's surface. Aft er the two L Mcrewmen have returned to the CM, the L M ascentstage i s jettisoned. It remains i n orb it around themoonwhen the CSM begins the journey back to earth.

STAGE

Lunar module



I I I t UAHES

Spacecraft 009 is lowered onto dolly in Dow ney clean room after final tests beforeit was turned over to NAS A;craft was later launched atop Saturn ZB in test of the command module's heat shield.

LM

Bug-like cab on legs

22 ft. 11 in.(legs extended )

29 ft., 9 in.(Iegs extended)

160 cu. f t .

32,000 Ib.

Aluminum alloy

SM

Cylinder

22 ft. 7 in .

12 ft., 10 in .

-

55,000 Ib. (approx.)

Aluminum alloyStainless steelTitanium

Shape

Height

Diameter

Habitable volume

Launch weigh t

Primary material

C M

Cone

l o f t . 7 i n .

12 ft., 10 in.

210 cu.ft.

13,000 Ib. (approx.)

Aluminum alloyStainless steelTitanium



INSTRUMENT UNlT

TH lRD

INSTRUMENT UNlT

Saturn V (left) and Saturn IB launch vehicles.



L A U N C H VEHICLES

The launch vehicles used i n the Ap ollo programare the Saturn I B for earth-orbit missions, and theSaturn V for lunar missions.

The Saturn I B was conceived by NASA's MarshallSpace Flight Center, whic h has technical dire ctio no f launch vehicles, as the quickest, most reli able ,and most econom ical way to develop a vehicle wi ththe ab ili ty to check out the Apollo spacecraft and

train astronauts i n earth orbit .

The Saturn IB has two stages and an instrumentunit (IU). The IU, a cylindrical-shaped segmentmounted atop th e second stage, contains equipmentfor sequencing, gu idance and control, tracking,communication, and monitoring. It was designed anddeveloped by MSFC and i s produced by IBM's FederalSystems Division.

Basic Saturn IB facts:

OVER-ALL VEHICLE

Height 138 ft. (launch vehic le only)224 ft. (with spacecraft)

We ight 1,3000,000 Ib. (wi th prop ellant)153,000 Ib. (wi th spacecraft dry)

Payload 40,000 Ib. i n low earth or bi t

FIRST STAGE (CHRYSLER)

Height 80.3 ft.

Diam eter 21.4 ft.Gross weigh t 1,000,000 1b.Propellant weight 910,000 lb.

Propellant RP-1 and liq ui d oxygenEngines 8 Rocketdyne H- 1 S

Thrust 1,600,000 Ib . (sea le vel )

SECOND STAGE (McDO NNELL DOUGLAS)

Height 58.4 ft.Diameter 21.7 ft .

Gross weigh tPropellantweightPropellantEngineThrust

l U (IBM)

HeightDiameterWeight

253,000 Ib.230,000 Ib.

Liquid hydrogen and liquid oxygenRocketdy ne J-2 (one)225,000 Ib. (vacuum)

3 ft.21.7 ft.4,500 Ib. (approximate)

SATURN V

The SaturnV i s the nation's largest and most power-ful launch vehicle. It w i l l be used to launch theAp oll o spacecraft on the lunar landing mission.

It i s composed of three stages and an instrumentunit.

Basic Saturn V facts:

OVER-ALL VEHICLE

Height 282 ft. (launch veh icle only)363 ft. (with spacecraft)

Weight 6,200,000 Ib. (with ~ r o ~ e l l a n t )430,000 (witho ut paylo ad)

Payload 270,000 i n low earth orbit100,000 Ib. trans lunar in je ct io n

FIRST STAGE (BOEING)

HeightDiameter

Gross weightPropellant useableweight

PropellantEnginesThrust

Burning time

138 ft.

33 ft .

4,792,000 Ib. a t li ft of f4,492,000 Ib.5 Rocketdyne F-1 'sRP-1 and liquid oxygen5 Rocketdyne F- 1 s7,500,000 Ib.

(1,500,000 Ib. each eng ine)150 sec.



SECON D STAGE (SPACE DIVI SIO N)

~-

- ppComparison o f Saturn V with other vehicles

Hei ght 81.5 ft.Diameter 33 ft.Gross weigh t 1,037,000 lb. at li ft of fProp ella nt 942,000 Ib.

useable weightPropellant Liquid hydrogen and liqu id oxygenEngines 5 Rocketdyne J-2's

Thrust 1,125,000 Ib . (225,000 Ib. eachengine)

Burning time 359 sec.

THIRD STAGE (McDONNELL DOUGLAS)

Height 58.5 ft.D ameter 21.7 ft . lower interstage expands

to 33 ft.)Gross weight 262,000 lb. at li ft of fPropellant 228,000 Ib. (excludin g reserves)

useable weighPropellant Liqu id hydrogen and liq ui d oxygenEngine 1 Rocketdyne J-2Thrust 225,000 Ib. maximumBurning time 491 sec.

lU (IBM)

Height 3 ft.D ameter 21.7 ft .Weight 4,500 Ib . (approximate)



Saturn V l if ts Apollo com mand and service modules of fpad at Kennedy Space Cente r.



APOLLO CHRONOLOGY

July 29 - Project Apo llo , an advanced spacecraftprogram to land men on the moon, was announcedby NASA.

Oc t. 25-NASA selected General Dynamics, GeneralElectric, andMartin to conduct individual feasibil-i t y studies of an ad vanced manned spacecraft as p artof the Apollo project.

Jan. - NAS A studies of a manned lunar-landi ng pro-gram were completed. Both a direct-ascent trajec -

tory using large Nova-t ype launch vehicles and anearth -orb it rendezvous technique using Saturn-typelaunch vehicl es were considered.

May 15 - Final reports on Project Apollo study con-tracts were submitted by Gene ral Dynamics, GE,and Martin .

May 25 - President Kennedy presented a plan toCongress for ac cel era tin g the space program basedon a national goal of landing a man on the moonbefore the end of the decade.

July 28 - NASA issued a request for proposal to 12

companies or development of the Apol o spacecraft.

Aug . 9 - NAS A selected MIT' s Instrumentation Labo-rator y to develop theguidance and navigation systemfor the Apol lo spacecraft.

Sept. 19 - NASA announced that the recen tly estab-lished Manned Spacecraft Center would be locatedat Houston, Tex.

Nov. 28 - NASA announced that a contract had beenawarded to North American's Space Divi sion or theApol lo spacecraft program.

Dec. 21 - The first four major Apollo subcontractorswere announced: Coll ins Radio, telecomm unicationssystems; Ga rr et t Corporation' s AiResearch Div isi on,environme ntal control equipment; Honeywel l Inc. ,the stab ili zat ion and control system; and Nor thropCorporation's Ventura Division, parachute earthlanding system.

Jan. 22 - The first A po ll o engineering order wasissued, for fabrication of the first mockups of theApol lo command and servic e modules.

Feb. 13 - Lockheed Propulsion Company was selectedto design and bui ld the soli d-propellant launch-escape motor for Apollo.

Mar. 2 - Marquardt Corp. was selected to designand bu ild the reaction-control rocke t engines forthe Ap ol l o spacecraft.

Mar. 3 - Aer oje t-G ene ral Corp. was named as sub-contractor for the Apollo service propulsion system.

Mar. 9 - Pratt and Whitne y was selected to b uil d theApollo fuel cell.

Mar. 23 - Avc o Corp. was selected to design andinsta ll the abl ati ve mater ial on the spacecraft outersurface.

April 6 - Thiokol Chemical Corp. was selected tobui d the sol id-propel lan t rocke t motor to be usedto jettison the Apollo launch escape tower.

July 11 - NASAannounced that the lunar rendezvousmode wo uld be used for the moon mission. This newplan called for development of a two-man lunarmodule to be used to reach the surface of the moonand return the astronauts to the lunar -orbi ting com-mand module.

July 16 - Beech Aircraft Corp. was selected to buildthe storage tanks for supercritical gases.

Aug. 2 2- The length of the Apo ll o service modulewas increased from 11 feet 8 inches to 12 fee t1 1 inches to provide space for additional fuel.

Sept. 7 - Apo llo command module Boilerplate I wasaccepted by NASA and d elive red to SD's Engineer-in g Development Laboratory for land and waterimpact tests.

Nov. 7 - Grumman Aircraft was named by NASA to

design and build the LM.



Mar. 12 - ApolloBoilerplate 13, the first flight-ratedboil erpla te to be completed, was accepted b y NASAand shipped to MSFC.

July 23 - Dr. George E. Mu el le r was named direc tor,NASA's Of fi ce o f Manned Space Flight.

N o v. 7 - The first launch test - a pad-abort test ofBoilerplate 6 - was conducted at White Sands.

February - A boost prote ctive cover was added to thelaunch escape system i n order to protect the win -dows of the C M and the heat shield surfaces fromsoot from the LES motor.

M a y 13 - The second test fl ig ht of the Ap oll o programoccurred a t Wh ite Sands when Boilerplate 12 waslaunched by a Li t t le Joe II vehicle during a high-stress, hig h-spee d abo rt test . The launch escapesystem wor ked as planne d, except that one of thethree parachutes cu t loose. The C M was landed

without damage.

M a y 28 - Ap ol lo command module B oilerplate 13 wasplaced in o rbi t from Cape Kennedy following launch

by a Saturn I booster. This was the first Ap ol lovehic le to be placed in orbit, and the third Apo llotest f l ight.

Sept. 18 - Ap ol lo Boil erpl ate 15 was successfullyorbi ted at Cape Kennedy b y a Saturn I two-stagelaunch veh icl e. This was the fourth Apo llo testf l i g h t .

Dec. 8 - The fif t h Apol lo test f l ighto ccurred a t WhiteSands when B oile rplat e 23 was li fte d of f the pad bya Litt le Joe II in a high Q abort test.

Feb. 16 - Apollo Boilerplate 16 was launched fromCape Kenned y in a micromete oroid test. A Pegasussate llite was carried al oft in a modified Apol lo SM.A l l equipment functioned as planned. This was thesixth Apol lo test f l igh t.

May 19 - Apol loBo ilerp late 22was launched at White

Sands in a planned high -al titu de test of the launchescape system. The Lit tl e Joe II disintegrated at

low alt itu de , resulting in an unscheduled bu t suc-cessful low -al tit ud e abo rt test. This was the seventhtest flight.

May 25 - The second Pegasus sa te lli te was p ut int oorb it a t Cape Kennedy during the Saturn I launch ofApo llo Boilerplate 26. This was the e ighth Ap oll otest flight.

June 29 - Apol lo Boilerplate 23A was successfully

launche d at W hite Sands during a pad abort test.A l l systems func tion ed as plan ned . This was thenint h Apol lo test fligh t, and the fifth abort test.This boil erpl ate module, previously designatedBoilerplate 23, had been launched a t Wh ite Sandsduring a high Q test.

Ju ly30 - Ap oll o Boilerplate 9A was launched a t CapeKenne dy and was used to pl ace the t hir d Pegasussatell i te into orbit .

O c t . 2 0 - The first actu al Ap ol lo spacecraft, SC-009,was accepted b y NA SA and subsequently shipped toCape Kennedy.

Dec. 26 - Ap oll o SC 009 was mated w it h UpratedSaturn at the Kennedy Space Center.

Dec. 31 - Command modules accepted by NA SA bythe end of 1965 inclu ded 18mockups, 18 bo il er -plates, and 2 spacecraft.

Jan. 20 - Apower-o n tumbl inga bort test of the launchescape system was cond ucted at Whi te Sands w it h helaunch of SC 002. Thiswasth e sixthan d fin al launch

escape test; the LES was then de cla red qua1 fi ed .

Feb. 26 - SC 009 was launched aboard U prated Saturni n successful test of command module's ab il it y t owithstand re-entry temperatures. Test was fir st f l g hto f unmanned spacecraft and firs t fl ig ht of UpratedSaturn.

Aug. 25 - SC 01 1 was launched successfu lly in theSecond fl ig ht of an unmanned Apol lo space craft to testcommand module's a bi li ty to withstand re entry tempera-tures under high heat load. The fli gh t was thre equarte rearth orbi t wi th recov ery of the command module suc-cessfully completed in the Pacific Ocean near Guam.



Jan. 27 - Threeastronautsdied n a spacecraft acci-dent a t Kennedy Space Center on the launch padduring a prelaunch test.

Nov. 9, 1967 - Apol lo 4 (SC 017) the firs t launch ofa Saturn V space vehicle was successfully carriedout . The spacecraft for the mission entered theatmosphere at almost 25,000 miles an hour. Heatshield temperatures exceeded 5,000 degrees. I twas the first test of a spacecraft retu rning at lunarveloc ities and the first launch of a hydrogen-powered Saturn V second stage (S-11).

APOLLO

-he possibility of a sporadic micrometeoroid as biga cigarette ash striking the commandmodule during

8-day lunar mission has been computed as 1 i n1230. If a meteoroid did strike the module, i t wouldbe at a ve loc ity of 98,500 feet per second. Thepro bab ilit y of the command module getting hi t i s

0.000815. The prob ab ili ty of the command modulenot gett ing h it i s 0.999185.

The heat leak from the Apollo cryogenic tanks,whi ch contain hydrogen and oxygen, i s so small that.if on e hydrogen tank containing ice were placed in aroom heated to 70 degrees F, a tota l o f 8- 1/2 yearswould be required to melt the ice to water at justabove freezing temperature. I t would take approxi-mately4 years more for the water to reach room tem-

perature. Thegases i n he cryogenic tanksare uti li ze din the production o f e lect ric al power by the Apo llofuel ce II system and pro vid e oxy gen for the use of thecrew.

April 4 - Apollo 6(SC 020)second fl ig ht of a SaturnVspace veh icle , was pa rt ia ll y successful. Thespacecraft funct ioned satisf actori ly. However,launch vehicle engine problems caused the space-craft to go in to alt ernate mission mode. Theservice propulsion engine burned for a recordlength. A l l subsystems performed we l .

BRIEFS

Wi th g ra vi ty on the moon on ly one-sixth as strongas on earth, i t i s necessary tha t this d iffe ren ce berelated to the Ap ol lo veh icle . A structure 250 feethighand 400 feet long i n which cables l i ft five-sixthof the spacecraft vehicle i s being used in tests tosimulate lunar conditions and th eir e ffe ct on thevehicle.

The command module panel display includes 24 in -struments, 566 switches, 40 event indica tors (mechan-ical), and 71 lights.

The command module offers 73 cubic feet per manas against the 68 cubic feet per man i n a compactcar. By comparison, the Me rcu ry spacecraft offere d55 cubic feet for its one trav eler and Ge mi ni pro-vided 40 cubic feet per man.

When the Ap ol lo spa cecraft passes through the VanAl le n Belts on its way to the moon, the astronautsw i l l be exposed to radiatio n rough1 y equivalent tothat of a dental X-ray.

The angular accuracy requirement of midcoursecorrection of the spacecraft for a l l thrusting maneu-vers i s one degree.



If your car gets 15 miles to a gallon , you cou lddrive 18 mi lli on miles or around the world about 700times on the fue l req uired for the Apollo/Saturn lunarlanding mission.

When the Ap ol lo re-enters the atmosphere i t w i ll

generate energy equiv alent to approximate1 y2300 kilowatt hours of electricity - enough to lightthe c i t y of Washing on for a bout 6-1/2 seconds; or theenergy generated would l if t al l h e people i n he USAthree inches off the ground.

There are 27 different means of communication inthe telecommunications system: ground to spacecraftlinks, 3; spacecraft to ground links, 7 . Ni ne diffe r-ent frequencies are used (1 HF, 3 V H F, 1 UFH,2 S band, 2 C band), and 5 antenna systems.

The fu ll y loaded Saturn V launch veh icle wit h theApollo spacecraft stands 60 feet higher than theStatue of Lib erty on i ts pedestal and weighs 13 timesas much as the statue.

During its 3.5 second fir ing , the Ap ol l o spacecraft'ssol id-f uel launc h escape rocket generates the horse-power equivalent o f 4,300 automobiles.

The engines o f the Saturn V launchvehicle that wi l lpropel the Apo ll o spacecraft to the moon have com-bined horsepower equiv alent to 543 jet fighters.

The Ap ol o envir onme ntal con trol system has 180 partsi n contrast to the 8 for the average home window a ircondi tioner. The Apol o environmental control sys-tem performs 23 functio ns compared to 5 for the aver-age home con diti one r. There are 23 functions of theenvironmental co ntrol system, wh ich includ e: ai rcooling, air heating, h umidity control, ventilatio n

to suits, ventilatio n to cabin, air filtration, C 0 2

remo val, odor removal, waste management functions,etc.

The Saturn V that wil l boost the Apo llo spacecraft

to the moon generates the horsepower equivalent todriv e an automobile 18 mi lli on miles-a 34-year tri pat 60 miles an hour.

The maximum dif fer en tia l pressure that the innerstructure of the command module can withstand i s8.60 psi. The environmental c ont rol system restrictsthe differential pressure to be less than 6.0 psi.

The 12-foot-high Apol l o spacecraft command module

contains almost 20 miles of wire, enough to wir e50 two-bedroom homes.

The astronaut contro ls and monitors the sta bi liz ati onand control system by means of two handgrip control-lers, 34 switches, and 6 knobs.

The command system o f the acceptan ce c hec kou tequipment can generate up t o 2048 separate stim ulior 128 analog signals, or combinations of both, and

route them to spacecraft and other checkout systemsat a m il li on bits per second. In contrast, hand-operated commercial tele type generates 45 bits persecond and autom atically, over voic e channel, i tgenerates 2400 bits per second.

The Apollo command module can sustain a hole aslarge as one-half inch i n diameter and st ill m aintainthe pressure inside for fi ve minutes, whi ch i s con-sidered long enough fo r an astronaut to pu t on aspacesuit.

Total amount of fue l i n the booster plus service mod-ule and lunar excursion module i s 5,625,000 pounds.



Giant booster undergoes last-tninute checks before launch Astrotiuuts enter C M f r o m scrvice tower crftcr final cltccks

Saturn V l i f ts Apollo spacecraf t of f ad at C ape Kennedy Saturn V second stage ignites as the first stage falls away

Second stage is jettisoned and third stage is ignited Third stage prrshes spac ecraft out o f earth's orbit



Adapter panels are opened and CSM separates C S M trirns around to get into positior? fo r docking

Command module docks with LM After docking, spacecraft leaves third stage behind

SM engine fires to put spacecraf t in orbit around moon L M separates from CSM to begin descent to moon



LM engine fires while CSM emains in orbit

Astronaut gathers soi l samples from the lunar surface

Tw o astronauts guide LM to landing on lunar surface

As t ronau t exp lo res su r face o f moon

Engine fires to lift LM ascent stage off m oo n and into orbit A.rtrona~ctsn LM l ine up their craf t for docking with SC C SM



S M engine fires to start homew ard journey; LM stays behind SM is jettisoned as C M prepares for entry into atmosphere

Pilot orients CM so base heat shield rakes friction heat Drogue parachutes are deployed for initial slowing of CM

Main parachutes are deployed to lower CM safely ro surface Recovery forces m ove in as the C M floats in water

apollo saturn lunar landing program

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