Apollo Saturn User Manual

TECHNICALIHFORMATIOHSUMMARYAPOLLO-11(AS-506)APOLLOSATURHV: SPAC,EVEHICLE*

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LAUNCII COMPt,EX 39• Launch Complex 39 (LC-39), Kennedy Space Center, Florida, provides all thefacilities necessary for the assembly, checkout, and la

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MOBILE LAUNCHERThe Mobile Launcher, figure 8, is a transportable steel structure which providesthe capability of moving the erected vehicle to the lau

GROUND SUPPORT EOUIPMENTA computer controlled automatic checkout system is used to accomplishcheckout or testJn] of the launch vehicle when in the Ver

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CUIDANOE AND CONTROL SYSTEM (G&C)• F_,nction and DescriptionJ e G&C system provides the following basic functions during flight:I. Stable posi

ABBRF,VIATTOI_S AND ACRO,_fMSac (AC) Alternating Current H2 HydrogenAccel Accelorometer lle HelII_AM Amplitude Modulation liP High Pressureamp Ampere

SPACECRAFT BACKUP GUIDANCE AND CO;;TROL/F_M,_IAI,ATTITUDE COi_"I';<OLCAPABILITYThe Launch Vehicle Flight Control Computer will accept att

!EMERGENCY DETECTION SYSTEM |The Emergency Detection System (EDS) is designed to sense and react toemergency situations resulting from launch vehicle

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LAVNCII VEIIICLE SECURE P_%NGE SAFETY .,¢\'_'i'c"¢',,.• ,..,The Secure Range Safety Systems, ]ocatcd on th,, S-IC, S-II and S

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MEASURI_E._' S_$T_The ve_icle measurement systems senses performance parameters and feedssignals to the stage a._dspacecraft telemetry systems. I

.AS-506Launch VeldcleMeasuremc_nt Summary ** Included illLaunchVehic]_.Totals-- j " I i,Designation ,, S-IC S-if S-IVB IU [| Totals_ccel. Flow Ra

, COMMAND _.ND CO_MUNICATION INTERFACES }:OR MISSION CONTROLMission Control Center (.UCC) Manned Spacecraft Cehter, Houston, Texas.Contains communicat

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SPACE VEIIICLE WEIGHT VS FI.IGIIr TI:.I}"l.l,iir, stage pr'pella1_ c_,' u;_4_ti,,.: du_i1_ F, S--]C pc':ercd fl_[.hr (approxi-mate

o\ABBREVIATIONS _ANDuACRO[;)_IS(Cont'.._d)NAR North American Rockvell USB Unified S-BandNASA National Ae_onautlca and SpaceAdministration Vel Vel

iiS-IC STAGE STRUCTUREThe S-IC stage is approximately 138 feet lo-g and 33 feet in diameter andis powered by fiv_ liquid-iuei_d Rocketdyn_ F-I engines

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F-I En_2_.IneOperationThe F-I engine is started by ground support equipment. Ground fluid pres-,:_. r s ports in the main LOX valves. Opening of the m

S-!rC ST.\GE PROPELLAI(T SYS'J t,7,ITile S-IC stage propell:,nt svstem is co:,lpnsed of one LOX tank, one RP--1 tank,prope11;mt ]ines, control va

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,¢_,!S-IC SI'AGE TIIRLI'ZTVkCT9R CONTROL S_. _EI-iThe fo_,r outboard F-I engines are gimbal mounted on the stage thrust_tructure to provide

GENERALINFOIiI4ATIONAbbreviations 2List o£ _isuree 4Mission 5mmary 6 .Dintribution List 92/LIST OF FIGURESIsGENERAL1 Countdown Sequence. ... , . . .

S-If STAGI" STRUCTUREThe S-II stage ib a large cy]Indrlcal booster approximately 8] feet in lengthand 33 feet in diameLer. The _tag¢: is powered

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J-2 EN(; NE OPE,.AI_ON S-If STAGET_ ,perating cycle of the J-2 Engine consists of prestart, _ttatt, steady-..tat, :. _ation and cutoff sequences. Duri

S-II STAGE PROPELLANT SYSTEMThe S-If Stage propellant system is composed of integral LOX/LH 2 tanks,propellant lines, control valves, vmts, and prepre

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S-II STAGE THRUST VECTOR CONTKOL SYSTE_I: The four outboard J-2 engines are gi_bal mounted to provide thrust vector ._eontro] during powered flight. ,

i LIST OF FIGURES (Continued)i Tit__1 PaS__.is! S-IX STAGE (Continued), 33 S-II ElectrlcalPower and Distribution System.. , ... 6034 S llTelsmetry Sy

IJ-2 ENGINEOPET_ATIONB-lV_ STAGET'n_operating, cycle oi the J-2 Engine consists of preetartj startt steady-stat_ operatlo_ snt! c_toff sequence_,

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! $-TV_ STAGE PROPELLANT SVST__ite S-JV_ stage propellant syst+,m is composed of integr;ll LOX/Lil 2 tankg,p._opo._._nnt iin_ control vaJvP.s 9 vents

\!i4• _ S-IVB TBRL'-ST VECTOk COntROL SYSTEMi.The single J-2 F_gine is global mounted on the lengltddtnaI axis of theiS-IVB Stage to provide pitc

This document Is prepared jointly by the Marshal) Space Flight CenterLaboratories S&E-ASTR-S, S&E-AERO-P, and S&E-ASTN-F_D The document pr

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\AUK_LIAR¥ PROPULSION SYST_The S-1VB Auxiliary Propulsion System (APS) provides vehicle attitude control_. ._,jringpowered flight in the roll axis onl

,.S-IVB STAGE PROPELLANT MANA(;L'MENTSYSTE,_!lThe propellant manap, er_ent system provides a means for _ontrolling andmonitoring prope]lant_ duri

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INSTgUHENT UNITThe Instrument Unit is a cylindrical s'tructt_rc arproximately 260 inches inditeter and 56 inches high which is attached to the fo

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As the vehicle rises from the launch pad, a yaw maneuver is executed to tnsurethat the vehicle does not collide with the tower in the event of h_.gh w

ENVIRON_._ENTAL CONTROL SYSTEH (ECS)The Environmental Control System (ECS) has been developed to maintain anacceptable _perating environment for the I

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-%r - °.SPACECRAFT DESCRIPTIONL The Spacecraft for the AS-50_ mission is composed of:Launch Escape System (LES)Command Module (CM);. Service Module (S

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Lunar Hodu]e Desccr_t. Approxlmntely fourteen hours later, two membersof tilethree man crcw, (A[_istrongand A]drin), wJ]1 enter the I_ through theconn

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