TECHNICALIHFORMATIOHSUMMARYAPOLLO-11(AS-506)

APOLLOSATURHV: SPAC,EVEHICLE*

ABBRF,VIATTOI_S AND ACRO,_fMS

ac (AC) Alternating Current H2 HydrogenAccel Accelorometer lle HelII_

AM Amplitude Modulation liP High Pressure

amp Ampere HOSt Huntsvil!e Operations SupportAPS Auxillary Propulslcn System CenterAUTO Automatic Hr Hour

C.O. Cutoff llz Hertz (one cycle per second) •CCN Covnterclockwlse

CCS Coanand Communication System IBM International Business MachinesCECO Center Engine Cutoff IGM Interative Guidance Mode

I

CC Center of Gravity in Inch

CIF Cmtral Instrumentation Facility IU Instrument UnitCIU Computer Interface Unit

CM C_mmand Module J-2 S-IVB & S-ll EnginesCSM Coumbnd and Service Module

C-T Crawler Transporter

CN Clockwise KSC Kennedy Space Center

dc (DC) Direct Current Lat LateralDCS Digital Command System Lb_ Pounds

DDAS Disltal Data Acquisition System L_C Launch Control Center

DEE Digital Events _valuation LEg Launch Escape System

des Degree LET Launch Escape TowerDin Diameter

LH Liquid HydrogenLI_F Launch Inform_tlon Exchange

EBW Rxplodtng Bridgewire FacilityECO bglne Cutoff LH Lunar ModuleECS Environmental Control Assembly L.O, Liftoff

EDS Emergency Detection System LOR Lunar Orbital Rendezvous

_4R F_ne Mixture Ratio LOX Liquid OxygenEnS Engine LV Launch Vehicle /._Elec Electric (Electrical) LVOA Launch Vehicle Data AdapterEP0 Earth Parkin_ Orbit LVDC Launch Vehicle _gitsl Com-EOM End of Mission purerESE Electrical Support Equipment

EVA Extra Vehicular Activity Max Maximum

Max "q" Maximum dynamic pressureF-I S_IC _ngines Mech MechanicalFCC Flight Control Computer MCC Mission Control Center

F_ Frequency Modulation _ MDC MacDonnel Douglas Corporation ,,Fwd Fo_ard MH_ Mesa Hertz (1 Million Hertz)

Min Minute

_A_C Grtmman Aircraft _igr. Corp. Mod Model ,.Gal Gallon (s) Mux- Multiplexer

- GN_ Gaseous N_trogen Mist -MiscellaneousGOX Gaseous Oxygen ML Mobile LauncherCpm Gallon par minute MR' Mixture RatioGRR Guidance Reference Release MSC Manned Spacecraft Center

GSE Ground Support Equipment MSFC Marshall Space Flight Center' OHo Gaseot_ Helium MSFN Manned Space Flight Network

._ GUID Guidance MSS _obile Service Structure

.' j

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1970011707-003

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\

ABBREVIATIONS _ANDuACRO[;)_IS(Cont'.._d)

NAR North American Rockvell USB Unified S-BandNASA National Ae_onautlca and Space

Administration Vel Velocity

_o Number vac Volts, alternating current

" h_I (n.ml,) Nautical Hlle VAB Vehicle Assembly Building"" OAT Overall Test Equipment vdc Volts, Direct Current

OECO Outboard Engine Cutoff VIIF Very llighFrequency

02 Oxygen (30-300 mHz)

' p (p) P_tch Y (y) Yaw

P_I Pulse Amplitude ModulationPC4 Pulse Code Hodulatlon SYmbols

I Ff)GO Underslreable Launch Vehicle

Longltudinal Oscillatlons A Delta_ POI Parking Orbit Insertion B Thrust Vector AngularPress Pressure Deflection

Prep Preparation A v Velocity Incremontpsi Pound_ Per Square Inch Lp Vehicle Attitude, PitchPsig Pounds per sq. in. (gravity) _y Vehicle Attitude, YewPsia Pound per sq. in. (absolute) _r Vehicle Attitude, RollPU Propellant Utilization _p Vehicle Attitude Rate, Pi_ch

_ _y Vehicle Attitude Rate, Yaw

_i, Vehicle Attitude Rate, RollR (r) Roll

_ RCA Radio Corp. of AmericaRCS Reaction Control System:'- RF Radio Frequency

PJ-1 Ramjet Fuel (used for S-1C lb/dro Fluid)

_-_/_" RP-1 S-IC Propellan_RPH Revolutions per mlhute

_ RSO Range Safety Officerm

S/C SpacecraftSec Second

.?

SEP Separation_- SLA Spacecraft Lunar Hodule

Adapteri_ SH Service Module

_ SPS Service Hoduls Propulsion System_ Sys System

_.. T (with subscript) Time Base_, TBC The Boeing Company_- TD&E Transportation, Dockln_ and

% Ejection

._ Temp TemperatureT° Used in countdown, time left •

until launch ' -

TI.I Translunar Injection"./M. TelemetryTV Television_vC Thrust Vector Control

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1970011707-004

GENERALINFOIiI4ATION

Abbreviations 2List o£ _isuree 4Mission 5mmary 6 .Dintribution List 92

/

LIST OF FIGURES

Is

GENERAL

1 Countdown Sequence. ..... , . . . . . . .'.......1

- 92 Nlm, ion _ro£ile . . . ...... . . . . . . . . . . . .3 Tra_lectory Information--Boost to TLI........... I04 Lunar Descant end Ascent Pnase_ . . . . . . . . . . . . . . 12$ Spacecraft Re-ent_. and Splashdown. o . . . . . . . . . . . 146 Space Vahicl ' 15e # 4 8 4 4 * 6 4 4 4 4 4 d 4 O # O ei 4 i # 4

7 UC h mple 39 ' 17""LAUnC Co x . . . . . . . . . . . . . . . . . .g Hobile l.a_p_chsr . . . . . ................ 199 Integrated Launch ESE . . . . . . . . . . . . . . .'.... 31

SPACEVEHICLE

10. S-XC/S-ZI Stage FIish_ Saquencins . . . . . . . . . . . . 2211 S-II/S-IVB Stage ]'lish_: SaquaneinSi , . . . . . . , . • . . 2312 S-IVB Stage Flight Sequencin$-............... 2413 S-XVB Stage Flight 8equencin$ . . . . . . . . . . . . . . . 2514 _lte_ata Time Base Sequencing. , . . . . , , . . . . . . ,.2615 Guidance and Control SystQm ,. , , , , , , , , . , , • , . , 2816 _marsancy getaction System... , . . . . . . . . . . • . . 3117 Secure _n_, Safety System ..... . . . . . . . . . . . 33l'J Typical LV Stage _asur_n$ Systa_ _ . . , . . . . . . • • . 3419 Measurement Smunary . . . . . . . . . . . . . . . . . . • • 3520 Vehicle Tracking Systems . . . . . . . . . . . . . . . . . 3721 Space Vehicle Wei;ht yJ Flight T_e . . . . . . . . . . . . 39

S- c s,c,xa_

_2 S-IC Conf_gura_ion . . . .................. 4123 S-IC F-I _giua System . . . . . . . . ........ , . .-4324 S-IC Propallan_ System, . . . , , , , , , , , _ , , , , , , 4525 8-IC _hrust Vector Centre] System . . , , . , , ,-, , , , 47 ",t6 S-lC Electrical Po_sr _d Distribution SyStem ', , , , ,., , 4827 S-IC Telnetry System , , _, , , ,. ,_'.. , , , , , , , , , , 49

28 S IX Configuration - ' 51do t * 0 e _ • • • • • • • • 0 4 4 • • 0_" 4' •

29 8-11 J-2 Englne System . , ,_,_, . . , , , , . , , . , , , 5330 S-ZI P_opeiiant System . . , . , , . ,_, , , , , , , ,., , 553_ S-lI 'fhruet Vector Control stem , . , , , . • , . ._. , , 5732 S-IT ?ropallant Management System . . • . • . , . . . . , . 59 ._

1970011707-005

i LIST OF FIGURES (Continued)

i Tit__1 PaS__.is

! S-IX STAGE (Continued)

, 33 S-II ElectrlcalPower and Distribution System.. , .... 6034 S llTelsmetry Sys 61I " - tem... , . . . ° ...........

.e

i S-IVB STAGE

{ . 35 S-IVB Con£1guratlon.............. ° ..... 63# 36 S_IVB J-2 Engin_ System ..... , ............ 65

37 S-IVBPropellant System . . , . ..... , . . . . ° . . 67" J 38 S-IVB Thrust Vector Control System .... ° . ...... 69

i?' I 39 Auxiliary Propulsion System ....... . .... . , . ° 71"I

_: 40 8-IVB PropellantManagement System , , , . , . , , , . , , 7361 S-IVB Electrical Power _d Distribution Syst_ . . . . . . 7462 • S-IVBTelemetry System ....... , . , . . . . . . . . 75

INSTRtTefENTUNIT

43 Irmtrument Unit Con_Iguratlo_. . . . . . . . . . 77_ 44 Instrument Unit Electrical Powe and Distribution . 78

45 Inetztment Unit Telemetry System . . , , . . . • . . • . . 79

_ 46 IU/S-IVB EnvironmentalControl System .... . . • . . , . 81e

_ _PACECRAFT

•_ 67 Spacecraft Confisuration . , . . , . . . . . . . . . . . . 8368 Spacecraft Guidance and _evisation System. , . . . . . . . 8_49 Spacecraft Electrical Powe_ end Distr£bution System .... 8550 CosmandModule (CM) ...... , . , . . . .... , . . . 8651 CM Telecommunication System ..... . ..... . . . . . 87_2 Lunar Module (LM) , . . . . . . . . . . . , . . , , . . , 8853 LgGuidance and Navigation Section , , , : , . , . , , , , 6954 LM Co_aunications Subsystem..... , . , . . . . , . , , 9055 Lunar _urface Communication, . . . . . . . . . . . . . . . 91

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1970011707-006

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 presents a

• brief and concise description of the AS-506 Apollo Saturn Space VehJcle and the •AS-506 mission. Where necessary, for clarlflcatlon, additional related Infor-mation ha_ bean _ncludad.

It is not intended that this document comp!et#ly defJne the Space Vehicle,

its systems or subRystems in detail. The information presented herein by textand sketches, describe launch preparation, ground support activities, and the

space vehicle. This information permlt8 the reader to follow the sequence ofevents bealnnlng a few hours be£ore Ill,off to mission completion,

1. Hiss:on PurpQse:

AS-506, Apollo Ii, Mission O-l, is the first manned Lunar Landing_Isslon. It uses Launch Vehicle SA-506; Commend/Service Module 107, Lunar

Module $| Launch Complex 39A; Mobile Launcher #1 and LCC Firing Boom #1.purpose is (1) to perform a successful lunar landing (2) assess the capabilitiesand limitations o£ the astronauts and their equipment in a lunar surface environ-men,, (3) perform lear action of the lunar surface and obtain soil samples, and(4) to safely return the crew _o earth. The crew consists of Nail A, Armstrong,

Spacecraft Commander, Fdwin E. Aldrin, Lunnar Module Pilot, and Michael Collins,Command Module Pilot.

2. Launch Vehicle.Objectives:

Demonstrate launch vehicle capability to inject the spacecraftonto a free-return, translunar trajectory.

3. Mission DescrIpt_0ns

&q-506, (Apollo 11), has a flight duration of approximately 8 days.

The AS-506 mission profile, illustrated in Figures 2 through 5, consistsof the following phases| Launch and boost to earth parking orbit, coast in earthparking orbit, translunar injection, translunar coast, S-IVB "slingshot", lunarorbit insertion, lunar module descent, lunar surface activities, lunar moduleascent, _ransearth injection, transearth coast, reentry, splashdown and recovery. .'

Launch and Boost to Earth Parkin_ Orbi¢ _EPO). AS-506 will b_ launchedfrom Kennedy Space Center, Complex 39A on a lal,nch azimuth of 90" East of N, rth.The launch days and the earliest liftoff time, for each day, for the month ofJuly are:

July 16. 8:32 a.m. CDT 72e - 108"• July 18 10:30 a.m. CDT 89" - 108"

Jt_ly21 II:09 a.m. CDT 94",- 108"

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1970011707-007

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 wind$ or asingle engine failure. Once tower clearance has been accomplished, a p_tch androll maneuver is initiated to achieve proper flight attitude and a flight azimuth

• o_ientation of between 72 and 108 degrees.

A successful boost sequence, as illustrated in Figure 3, will _nsert the°" S-IVB/IU/SC into n 100 NNI circular earth parking orbit.o

Coast in Earth Parkin_ Orbit (EPO). The vehicle will coast in earth park-ing orbit while space vehicle subsystems checkout is performed. Preparation for

• translunar injection takes place during this period, The reignition time and' orbital position of the S-IVB injection burn will depend on lunar declination and

upon the injection window opportunity to be selected. The first injection opportunity

occurs midway through the second parking orbit revolution while the second opportunityoccurs midway through the third revolution.

Translunar injection, Followlng the selection of one of the _wo injection

opportunities described above, the S-IVB stage relgnltes to provide translunar

injection. The nominal injection provides a free return trajectory to earth If thedeboost to the lunar parking orbit is not initiated.

Translunar Coast. _nortly after traaslunar injection, the Transposition,

Docking, and Extraction (TDbE) of the Command and Service Module (CSH) and the

Lunar Hodule (124)will take place. To initiate this maneuver, the CSbl,assistedby the service module's reaction control system, will separate from the S-IVB.

Spacecraft Lunar-Module Adapter (SLA) panels are then Jettisoned =o expose the

docklngmechanlsm of the lunar module. Following separation, the CSM will trans-late approximately 50 feet, pitch 180 degrees, roll 60 degrees and move to dockinginterface with the lunar module. As soon as the crew has c_pleted verification

that docking latches are engaged, and that CSM/LH tunnel pressure has been equalized,the LM/SLA attach points are severed and the I_ is extracted and moved approximatelyI00 ft. from the S-IVB. During translunar coast ( _pproximately 75 hours), mid-course corrections are made if required.

S-IVB "Slingshot". In order to minimize the probability of spacecraftand latmch vehicie collision, and to avert S-IVB earth or lunar impact, a S-IVB"slingshot" procedure is executed. To initiate this maneuver, the launch vehicle(S-IVB/IU/SLA) will move to a predetermined attitude and execute a retrogradedump of residual propellants_ T_is will reduce vehicle velocity by approximately115 feet per second. Following retrograde propellant dumping, the S-IVB is"safed" by dumping the remaining propellants and gas from gas bottles through

•. the latch-open, nonpropulslye vents. This velocity change in the S-IVB will per-turb the S-IVB trajectory so that the vehicle will be influenced by the moon'sgravitational fleld. This Influence will increase velocity sufficiently _o as

. to place the S-IVB/IU/SLA in solar orbit•

Lunar Orbit Insertion. Prior to lunar o_bit insertion, the crew willcheck the LM for operational readiness and return to the CSH• If all conditionsare "go", the Service Module (SN) propulsion system will be used to deboost theCSH/LM into a moon orbit ranging from 60 to ]70 NMI above the moon's surface•Two orbits later, approximately four hours, the astronauts will circularize the

• orbit at 60 NMI.

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1970011707-008

Lunar Hodu]e Desccr_t. Approxlmntely fourteen hours later, two membersof tilethree man crcw, (A[_istrongand A]drin), wJ]1 enter the I_ through theconnecting tunnel, Upon compietion of a LH checkout, they will undock the LM

" and begin maneuvers:which wil] take them to the moon's .surface. Landing, via

the Junar module descent propulsion system, will occur approxlmately 2-I/2

hours later. (The LM can ],overlike a helicopter for approximately 60 secondsto select the _moothest landing spot.) W_,i]e separated, the astronauts will useLhe radio for communication using Code names "Snowcone" for the Command Module

and "flays___tp/k" for the Lunar ModuJe. Present plannlng calls for lurer touchdown tooccur at 3:21 p.m. CDT on July 20, 1969. The third crewman (Collins) wl)]. continueto orbit the moon in the CH.

Lunar _:urfaceActivities. Following touchdown, Armstrong and Aldrln

are to rest fo_ -ppreximat_y eight hours, Lhen don their portable llfe supportbackpacks and ma]'e other necessary preparation to walk the moon's surface. At1:09 a.m. CDT on July 21, 1969, Armstrong is to climb down a nine-step ladder and

, become the firs_ man to plant his footsteps on the moon's surface. This activity!: is to be relayed llve to television viewers on earth with Aldrln handling the TV

camera_ Armstrong will stroll alone for about half an hour, gathezlng a quick

: sample of lunar sell so that they won't come home empty-handed if they should have' to make an early takeoff Then Aldrln is to Join Armstrong on the surface for

' approximately 2 hours during which they are to gather about 80 pounds of lunarrocks and soil and to set us a scientific experiments package which will transmitlunar data after the astronauts leave,

Lunar Module Ascent. After returning to the LM, the astronauts are

to rest for nearly six hours. They will have been on the moon for approxlnmtely21 hours and 30 minutes. The LM ascent stage is used to llftoff from the moon's

surface and to fly a 3-hour and 30 mlnute rendezvous course to catch-up and llnk-up with the CM. Orbital plane changes, trim burns, or maneuvers required to

achieve CSM/LM rendezvous are made with the LM reaction control system. As soonas CSM/LM docking has been accomplished, the two crew members, the lunar sellsamples and the exposed film are transferred to the CSH and the LM is secured.

Service module RCS is used to separate the CSM from the LH,

Transearth injection and Coas E. The SH propulsion system is used toboost the CSM out of lunar orbit. During transearth coast (approxlmately 64hours) midcourse corrections are made if required.

Reentry, Splashdown. and Recover. The Command Module is separated from

the Service Module prior to atmospheric reentry. The nominal range from re-entry (400,000 feet) to splashdown is approximately 2000 miles. Splashdown will

take place in the Pacific Ocean approximately 12:00 p.m, CDT July 24, 1969. -"Immediate recovery of the crew after splashdown has been arranged.

Quarantine Period. Upon recovery, the astronauts will be transferred to

a special sealed van on the deck of the carrier for the sea-alr-truck trip to theManned Spacecraft Cen_er in Houston, Texas. There they are to be quarantinedwith the lunar soil samples In a lunar receiving laboratory for 18 days. Doctorswlnt to be certain they do no_ bring back any lunar germs.

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1970011707-009

1970011707-010

_INAL PAG ;__ EIS POOR

1970011707-011

i

BASES

°

,

LAUNCII COMPt,EX 39

• Launch Complex 39 (LC-39), Kennedy Space Center, Florida, provides all the

facilities necessary for the assembly, checkout, and launch of the Apollo�Saturn

space vehicle. The vehicle assembly building (VAB) provides a controlledenvironment in which the vehicle is asse,nbled and checked out on a mobile launch-

er (ML). The space vehicle and the launch structure are then moved as a unit by

. the crawler-transporter (C-T) to the launch site, where vehicle launch is ac- .compllshed after propellant loading and final checkout. The major elements of

the launch complex showa in Figure 7, are the vehicle assembly building (VAB),

tll_ laulluh control center (LCC), the mobile launcher _L), the crawler-trans-

porter (C-T), the crawlerwsy, the _aobile service structure (MSS), and the launch

pad •

D

1970011707-017

• Om O " _ ' • , "___U¢IBIL.J TY.OE THE ORIGI.N_ALPAGEIIS,POOR_/

1970011707-018

MOBILE LAUNCHER

The Mobile Launcher, figure 8, is a transportable steel structure which provides

the capability of moving the erected vehicle to the launch pad via tilecrawler-transporter. The umbilical tm' r, permanently erecte_ on the mobile launcher

base, is a means of ready access to all important levels of the vehicle duringassembly, checkout and servicing prior to launch. The intricate vehicle-co-

ground interfaces are established and checked out within the protected environ-

ment of the Vertical Assembly Building (VAB) and then moved undisturbed aboardthe mobile launcher to the launch pad.

S-IC 7ntertank (preflight)• _ S-IVB Forward (Infllght).

Provides LOX fill and drain. _-_ Provides LH2 and LOX trans-Arm may be reconnected to fer, electrical, pneumatic,

vehicle from LCC. Retract and alr--condltioning inter-time 8 seconds. Reconnect faces. Retract time 7.7

l: . time 5 minutes, seconds..

_ S-IC Forward (preflight). Q S-IVB Forward (inflight).Provides pneumatic, elec- Provides fuel tank vent,trical, and air-conditlon- electrical, pneumatic, ai--

ing interfaces. Retract- conditioning, and preflight

: ed at T-16.2 seconds• conditioning interfaces.Retract time 8 seconds. Retract time 8.4 seconds.

(A s-nAft(preflight) (.b ServiceMod.le(inflight).' _ Provides access to _ Provides air-conditioning,

vehicle. Retracted vent line, coolant, electri-

! prior to llftoff as calm and pneumatic interfaces.required. Retract time _.0 seconds.

v_ S-If Inter=edlate (in- Q Command Module Access Armflight). Provides LH2 (preflight), Provide access

and LOX transfer, vent to spacecraft through en-llne, pneumatic, Instru- vironmental chamber. Arm

" merit cooling, electrical, controlled from LCC. Re-

and air-condltlonlng in- tracted 12° park positionterrace. Retract time until T-4 minutes.

6.4 seconds.

Q S-ll Forward (inflighO.Provides OH2 vent, elec-trical, and pneumatic ' .._.nterfaces. Retract time7.4 seconds.

e

Note:

• Preflight arms are retracted Infllght arms retract at

and locked against umbilical vehicle liftoff on commandtower prior to launch, from service arm control

switches (located in hold-down arms).

1970011707-019

GROUND SUPPORT EOUIPMENT

A computer controlled automatic checkout system is used to accomplishcheckout or testJn] of the launch vehicle when in the Vertical Assembly

Building (VAB) highbay and on the launch pad.

An RCA IIOA Computer and other equipment necessary for service and check

out are installed with the vehicle on the mobile launcher. Simi]ar equipment,

Joined by an integration system (relay network), a facilities cable tunnel and

video cables for visual display are located in the Launch Control Center (LCC).

A Digital Data Acquisition System (DDAS) collects vehicle and support

equipment responses to test commands and formulates test data for transmission,

deco_mutation, and display to the LCC or ML.

Digital Events Evaluators (DEE) monitor the status of input lines and

generate a time labeled printout for each detected change in input status.

High speed printers in the LCC are connected to each DEE to provide a means

for real time or post-test evaluation of discrete data.

The propellant tanking computer system (PTCS) determines and controls the

quantities of fuel and oxidizer on board each stage. Optimum propellant levels

are maintained and LOX and LH 2 are replenished as boiloff occurs during thecountdown. The propellant tanking operation is monitored on the PTCS control

panel.

: Final countdown begins at T-I02 hours. A countdown clock, located in the

LCC, officially records this countdown.

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1970011707-021

I Inh_irwl(dL,aunchFig,.'_"g F__,E..... --- ' Z!

1970011707-022

i! I ,l_Z.fof_

I I I

I II

f_ul,'t_pt_En£;n_. Cufo'F_Er_b_eNOLin 14"5Ec

I II I

/_ FD3 Enqi_¢ CutoCt EnaSIt - Omi_ 50}¢c! I

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# - I %

1 I" _k _-IC Inboard E_o__£¢ "_ Zmin 15<_c :

I _ s-,c o_ `._i._._r2m_n 41 _C .

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_._-. NOTE: [ II _,-I J E_lg;,l_ P_.arf -

,-- I I

i:_ -I " _! /',_,,cox_,p"_dizaf_on

_,_.,,..,,..,to -- " t_- " _i_:. ' " _::,_:;._'_.2Z

1970011707-023

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,', I- °

_, 5/r "_,¢rol D;_abl_ ,.-,2hr-3Srqin

/_O_/H2 Burner On -- :]Smi_

I/_ LOX ¢ LH z C..hilldouJn Pu_p Or, ..-. 2hr _&rnln

_5-1V_ Ullaqe On _" ZhrZ_r.in

0zIUz 13urncr Of"/ " 2 hr 42 r_'m

• ".. /_ LOX _rLHz Chilldo_n Pump Off""-'2hr 4¢rnin

S-W/5 Ullag_ 0¢¢" _-Zhr 44 rain

" " i

5"IV5"l'aq,,Ib.na.in__ -,.,2h_. 4¢_n/

iNOTE- /_=_5-1V& LOXt, LHz Poin �LevelOensor Ertabt¢-, 2hr4gmin

Approximef¢ +;t,='s

I if4_FP

• • If" re@arf i_ 6e':eqed _ _--IV_ _t_aqe En_ln¢ _nd Cu_ro¢¢_ 2hr =30rainun._il the _econd in_cCrionopRortunlt,, j "t'hi'_ ahd I

m_jor .'sub_eq.;e_'t" - I _mA=c3.1Vb LO_LHz l:_inflev=l 5_nsor" Di,_a,'m"2/'cSOmin• • ." _wn1_ _|l becor" I

apwox;_laC:¢lq on e Ih_ur and "h_elve.

r_inut_,_later "Hun I_houan. /_ LH= Vulf Valve Open _"2 hr 50 rain• @lnhiblt_d _'or_r I -"

I _ _/_ Con'_ol Enable. ,., 2hr 50m;n

! ,I_a,"ro(" :_rt-art- of.

.. "lqr_tba_e¢u "T;_ _c 7

1970011707-025

LHz Vlnf VaJv£ Close N .5hr 05 m;n I

/

I U Command _ t"ent Enable --' 3ht-IOr_;n1° I• .

• m #

I I

i I I

.i /_ kbl2"]'ank L_rtching i_elieF',lelv_ Open Off ,_4hrOSr4in ;J#;t I

I I:-_: It

IP"_'_iva'Hon Enable ~ 5hrOZmin

, II.

: I; /_ Engine I..I£Con't'_ol Valve Olin On "_ 5hYOZ rain

I

'; L_ Engine H_. Cord'ml Valve Open Of'? ,,, 5hr D4mln

- J .o-rE: Ii /_prr,_im_m+i_ I

- _ -_how.,e'e_a _ l_$sivafion bi_._b|t. ~ 5hr 2groin' I- .

t !I

:, .. _ .._lVl_ Ulleq_ Enq;ne_ No.I _.No.Z On ~Sh¢_,bmin

_: I_". I

_SMr 4lmin

"' " I_.i •

3terf oP

' ii II5-lVl_ 5faq_

I: __ Fli_t,_l- 3¢o(u¢flt..irt9 25

1970011707-026

{_ "r_,e,oslor, e2,¢"l:_'_e._'ho_"l',,h:bi'l-(6/C_wi_tch)

. NOTE: in o_e.r fo poor;de ¢_o¢Tl)_g _',_E_,-_h O,-b,t. a

*_ 2&, ............

1970011707-027

CUIDANOE AND CONTROL SYSTEM (G&C)

• F_,nction and Description

J e G&C system provides the following basic functions during flight:

I. Stable positioning of the vehicle to the commanded position with a

minimum amount of sloshin_ and bending.

2. A first stage tilt attitude program which gives a near zero lift tra-

jectory through the atmosphere.

3. Steering commands during S-Ii and S-IVB burns which guide the vehic, e to

a predetermi,led set of end conditions while maintaining a minimum propellant

trajectory for ea_Lh orbiL i.,b_rtlon.

4. The proper vehicle position during earth orbit.

5. Guidance during the second S-IVB burn, placing the vehicle in the proper

waiting orbit.

G&C Hardware

The Stabilized Platform (ST-12_:) is a three gimbal configuration with gas

bearing gyros and accelerometers mom_ted on the stable element. Gimbal angles

are measured by redundant resolvers and inertial velocit_ is obtained from inte-

grating accelerometers.

The Launch Vehicle Data Adapter (LVDA) is an input-output device for the

Launch Vehicle Digital Computer (LVDC). The LVDA/LVDC components are digitaldevices which operate in con_unctlo_, uo carry out the flight program. The flight

program performs the following functions: (i) processes the inputs from the

StT-124M, (2) performs navigation calculations, (3) provides the first stage tilt '_

program, (4) calculates IGM steering commands, (5) calculates attitude errors,

(6) issues launch vehicle sequencing signals.

The Control/Eds Rate Gyro Package contains nine rate gyros (triple redundant

in three axes). Their outputs go the Control Signal Processor (CSP) where they

are voted and sent to the Flight Control Computer (FCC) Eor damping vehicle

angular motion.

The FCC is an analog device which receives attitude error signals from the"Q

LVDA/LVDC and vehicle angular rate signal s from the CSP. These sig_als are

filtered and scaled, then sent as commands to the S-IC, S-II, and S-IVB engine

actuators and to the Auxiliary Propulsion System (APS) Control Relay Packages.

The Control Relay Packages accept FCC commands and relay these commands to

operate propellant valves in the APS. During spacecraft control of the launch

vehicle, the FCC receives attitude error signals from the Command Module Compu-ter or the Astronaut hand co_troller.

The Switch Selectors in each stage are used to control the inflight se-quencing as commanded from the LVDA/LVDC.

1970011707-028

SPACECRAFT BACKUP GUIDANCE AND CO;;TROL/F_M,_IAI,ATTITUDE COi_"I';<OLCAPABILITY

The Launch Vehicle Flight Control Computer will accept attitude commands

from the spacecraft instead of the LVDC during (i) boost to Earth Parking

Orbit (EPO); (2) orbital coast mode; (3) TransJunar Injection (TLI) burn; and

(4) tile post TLI coast mode, with the follow_ng constraints"

, DurinK Burn Modes

I, .. The Spacecraft attitude commands wiil be accepted by the flight

control computer only in the event that the LVDA signals that the LV ST-124M

: Platform has failed followed bv the Astronaut enabling the LV Guidance Switch.

If the ST-124M Platform should fail before Time Base 6 (TB6) !nitiation, a

navigation update by ground command will be required to start TB6 (S-IVB preps.

: and second burn). There are two modes to the backup system operations and they: a)Fe :.

: (i) Automatic Backup Guidance and Controli ,i

In the automatic guidance mode both the control and guidance

functions will be provided by the Spacecraft. This backup mode is used during

S-IC stage flight and S-II flight up to LET jettison. The sequence of eventsare as follows:

a. Failure of ST-124M is verified by LVDA.

, b. LVDA illuminates warnin_ light in S/C.

c. Astronaut enables LV Guidance switch.

-_ d. S/C transmits error signals to LV flight control computer.

, (2) Manual Backup Guidance and Control

_ : In the manual guidance mode both guidance and control loopswill be elose¢' through the Astronauts. ._m Astronaut cont_ auously adjusts

i _ vehicle attituCe via the Rotation hand Controller to maintain the desired tra-

Jectory. Sequence of events following a Platform failure after LET Jettisonare:

!

a. Failure of ST-124M verified by LVDA.

b. LVDA illuminates warning light ia S/C.

' c. Astronaut enables LV Guidance Switch.

.. d. Manual guidance and control is initiated by the Astronaut

enterlnK a word into the S/C computer to switch AUTO/MANUAL switches to _[ANUAL.

" e. If automatic backup guidance is in operation at LET Jettison,

switching to manual backup is accomplished by performing step

• (d).

During Orbital and Post TLI Coast Mcdes,]

\:L In earth orbit ana post TLI coast mode8 the Astronauts have a manual

' attitude control capability. The takeover follows somewhat the procedure for

Manual Backup Guidance and Control takeover.

.i ,q0.,

1970011707-030

!

EMERGENCY DETECTION SYSTEM |

The Emergency Detection System (EDS) is designed to sense and react to

emergency situations resulting from launch vehicle malfuDctions which may arise

during the mission. Crew safety and protection is the primary function of the

EDS. Triple redundant sensors and majority voting logic are used in the auto-

matic abort system. Dual redundancy is used for most of the manual a_ort sen-

sors. The redundancy in the sensing systems is designed to protect against "

inadvertent aborts. I

Automatic Aborts - During most of the S-IC flight, the EDS provides the

c_pabi!!ty of au_omat_e_11y ah_rring the m_ssion. The automatic abort system

is enablcd at liftoff and disabled by the crew at approximately 2 minutes or by "

the IU switch selector prior to S-IC inboard engine cutoff. The system re- isponds to failuze modes that lead to rapid vehicle breakup. The parameters andd

the associated limits monitored for an automatic abort are:

_ 1." Simultaneous loss of thrust on two or more S-IC engines

2. Vehicle rates in excess of ±4°/sec in pitch or yaw; or ±20°/sec in roll

3. S/C to IU breakup.

Manual Aborts - After the automatic abort mode is disabled, aborts may be

initiated manually by the astronauts. Manual aborts are initiated based on at

least two separate and distinct indications. The indications may be a combina-

tion of EDS sensor displays, physiological indications, and ground information

to the astronauts. EDS displays for the crew consist of light and meters which

; indicate loss of thrust of each engine, staging sequences, launch vehicle attitude

reference failure, angle of attack, tank ullage pressures, spacecralt attitude

error and angular rates. The manual abort overrate limits are:

1. Pitch and Yaw - L.O. to S-IC/S-II Staging - ± lO°/sec

- S-IC/S-II Staging to S-IVB C.O - _9°/sec

2; Roll - L.O. to S-IVB C.O. - ±20°/see

Aborts occurring during the launch phase will be performed by using either

the Launch Escape System (LES) or the Service Propulsion System (SPS). The

LES is used to propel the CM a safe distance from the launch vehicle and to

ensure a water landing. Aborts prior to 30 seconds of flight do not terminate

S-IC thrust in order to protect the launch area. The SPS aborts utilize the

Service Module SPS engine to propel the CSM away from the launch vehicle, and t"

to maneuver to a planned landing area or boost into a contingency orbit.

I "J

7

i;

1970011707-031

1970011707-032

LAVNCII VEIIICLE SECURE P_%NGE SAFETY .,¢\'_'i'c"¢',,.• ,..,

The Secure Range Safety Systems, ]ocatcd on th,, S-IC, S-II and S-IVB st_L_',e_,

provide a means to terminate the flisht of an er_atic w, hiclc by the tr._.,._missionof coded commands from ground stations to th_ w,hic]e during l,oo,_t pl,_:;e. 'fh_

Range Safety Officer (RSO) terminates the fl_Eht of an erratic vehicle (tra-

jectory deviations) by initiating the c::erg,:ucy _._gin_ cutoff co::_,.namland, if

necessary, the propellant dispersion conx "_d.

11ae certain,and destruct system in each stag. i:s completely separate and lnde-

pendent of tho.°e in the other stages wiO_ the exception el a 2 for "3voting

arrangement between the S-]C and S-!T Range Safety System Ccntroxters. This

arrangement eliminates a single point failure in the S-IC ralge safety system

controller, which, if it failed would cause an unnecessary S.-IC engine cutoff.

The system in each powered stage consists of a range safety antenna sub-

system, two aec_re command receivers, two Range Safety Controllers, two Secure

Range Safety Decoders, two Exploding Bridge Wire (EBW) firing units, two EBW

detonators and a common safe and arm device which connects the subsystem to the

tank cutting charge. Electrical power for all elements appearing in duplicate

is supplied from separate stage batteries.

Prior to launch, the safe and arm device is set to the "ARM" position by

ground support equipment and the system remains active until orbital insertion.

After orbital incertion, the S-IVB stage range safety receiver is deactivated

._ (Safed) by ground command from the Range Safety Officer.

ii

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1970011707-034

MEASURI_E._' S_$T_

The ve_icle measurement systems senses performance parameters and feeds

signals to the stage a._dspacecraft telemetry systems. It includes transducers,signal conditioning, ariddistribution equipment necessary to provide the required

measurement ranges sud suitably scaled voltage signals to the inputs of the tele- i

merry syst¢_mSo _'nevehicle measuring systems performs three main functions_

I¢ _ec-':ion of _he physical phenomena to be measured a:idtransformation of

_se pF.enomena into electrical signals°

,_ 2, lhn_,:e_sand condition tke measured s_.gnals into the proper form fort._..le_ate rJng.

-_ 3. Distribution of the data to the preper channel of the vehicle's telemetry

:-.

_e table _ Y.heopposite page contains a measurement breakdown for the launch

vehicle ae_ s;x_cecraft, and a measurement summary of past Saturn V flights.

f

_" "i'_,,,,_,-,,,:,_l_ ___._ r-----_ _ J II I

I

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I

1970011707-035

.

AS-506Launch Veldcle

Measuremc_nt Summary ** Included illLaunchVehic]_.Totals

-- j " I i,Designation ,, S-IC S-if S-IVB IU [| Totals

_ccel. Flow Rate, ' " -- Jl -'|_ 17 ] ].2 i]. 8 48l,iqu!d Level.E ! II

Temperature 66 87 61 13 227

• Pressure 89 105 79 i0 283

Voltage, Current, 6 33 38 17 94_,, _[Trprl t I_n Pv . = -- ,,

i " Signals 127 221 71 65 484

Position, AngularL 25 54 i0 42 131_ Vel., Stlain & RPM

'" Misc. RF &- 2 9 46 57

T_ 1 _m_ try

_ TOTALS 330 514 279 201 ii 1324. . ,, , , .....

ESE Displays 65 185 98 175 523**

Auxiliary Display 37 57 69 15 178"*

_; Flight Control 50 215 64 102 401"* !

AS-506 '" ',Spacecraft Measurement Summary ;.

Measurement_ m To_(_ls

i _Sj_n_tlon i

15 35 98 148 iPressure

Temperature 18 43 160 221 "

: Discrete Event 80 I0 320 410

,_ Voltage, Current &5 7 190 242& Frequency "

_ Miscellaneous 35 50 120 205

t_

........ Previo,4s ' Fitghts_-Measurement Sum.a_:w . ....

Vehicle S-IC S-'II I- S-IVBI *U LV ,,Tgt a,,.l* .1 ,Space¢ra f t:

" ---AS-5'01 872 976 589 . 337 2774 "[-- -- "

AS-502 891 " 960 612 _ . 338 2801 i .leL, _ ,

• AS-503 87"6"' 992 " 351 450 2669 338_, ,. . _ _ - , ..

A5-504 666 989 294 296 2245 _ 1218",, ,, , , ...... :

AS'505 644 936 279 218 2077 1218'i _ __ i. _ _ i | _ ,i i .... . I

• LM measurements added to AS-504 & 505 . :

Note:̂ n mea,ureme.t F .gure!7 Me.s.re -e.tnumber_ approximate

J

|

1970011707-036

, COMMAND _.ND CO_MUNICATION INTERFACES }:OR MISSION CONTROL

Mission Control Center (.UCC) Manned Spacecraft Cehter, Houston, Texas.

Contains communication, computers, display and co,m_and systems go monitor and

•' control the space vehicle.

! Kennedil_Space Center z Florida (KSC), The space vehicle is assembled,

i checked-out, and launched from KSC. Central Instrumentation Facility (CIF)

: collects powered flight data and data received flom Merritt Island Launch

i Area (MILA) and Ai___/rFo___rceEastern Test Ran__ (AFETR).

F Goddard Space Flight Center (CSFC). Greenbelt, Maryland operates the

I Manned Space Flight Network (MSFC) and NASA communications network. The MSFC

i is under control of MCC during flight.!!

I George C. Marshall Space Flight Center (MSFC) Huntsville, Alabama. Using

i I The Huntsville Operations Support Center (HOSC) and the Launch I _ormation

_i Exchange Facility (LIEF), real-tlme support is provided to KSC and MCC for! preflight, launch and flight operations.

i The Manned _ Fl_ght Network is a global network of r_nd stations

: ahi_, and aircraft designed to "_,Jpport manned and unmanned srace flight.

While selected ground stl.tlons throvghout the world monitors all phases

_I of flight aetlvity from liftoff to recover_/_, p_e-destlned ships and aircraft

are strategically situated to monitor "Insertion to Earth Parking Orbit",

"Translunar Injection" "Reentry and Recovery".| , .1i!

:t!

1

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! ,.

1970011707-037

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.- VEHICLE TI_CKZI_ $YST]_[$

_, In the Saturn V space vehicle there is a continuous requirement to transmit tn-fo_ation to ground stations in order to determine the vehicle_s trajectory. _isrequirement is satisfied by the RF tracking systems• The t_acking data is used bymission contro_ range safety, and for _ost-flight eva_ation of the vehicle_s per-i ".formance. The tracking systems used are:

C-Baud _I_ and S/C)_4

C-Band is a pulse radar system which is used for precise tracking during power-ed flight into earth orbSt, orbital flight_ _nJection into trans-lunar traJectory_and coast flight after injection.

s-sanS_zu and s/c).

The Unified Side Band fUSS) System provides tracking capability to the USB

ground stations and these stations track the spacecraft to _the moon.

Zo Trackln 9 5V_4"em"J - I

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-mately 161 second.;) is apprc.xlmnt¢.ly :,,67.'J,300 pounds. Propellant consumptionduring S-I I po;'er_.d f_i}9_t (;,ppr_,._t;_m,:Iv 3_9 seconds) is appz'oximately971,_50 pounds. Duriqg S-IVB powur,.J fl;::ht, lncludtng first and second burns,(approximately 46] sccond:_) the propellant co,_sumption is ,.pproximately 223_900pounds.

Vehi__cje We___/llhtData_(,A;_d)roxlrn:,te) Pounds

Yoial ut S-IC ISnILIu_, 6,484,300 .

Total at liftoff 6,398,500

Total at S-IC OECO 1_826,900

Total at S-If ignition I,h53,800

Total at S-II OF.CO _69,700

Total at S-IVB Ist ignition 367,C00

Total at S-IVB Ist ECO 297,500

Total at S-IVB engine restar'. 294,600I

i Total at S-IVB 2nd ECO 133,600

Total at S-.IVB/CSM separation 130,900

Total at SC translunar injection 100,800

1970011707-039

i

iS-IC STAGE STRUCTURE

The S-IC stage is approximately 138 feet lo-g and 33 feet in diameter and

is powered by fiv_ liquid-iuei_d Rocketdyn_ F-I engines which generate a nominal

thrust of 7,610,000 pounds. StaI_e engines a;'e supplied by a hi--propellant system

of liquid oxygen (LOX) as the oxidizer and i_-i as the fuel.

The Fo1_ard £kirt

The Forward Skirt accommodates the forward _,ibilical plate, the electrical

and _lectronic canisters, and the venting of the LOX tank and interstage cavity.

The aluminum skin panels are stiffened by ring frames and stringers.

The Oxidizer Tank

! The 343,600 gallon capacity LOX tank is the strucLural link between the

forward and intertank sections. Stiffened by machined "T" stiffeners the tank

is internally equipped with ring baffles for additional stability as well _b £o

reduce IOX sloshing and to provide support for four helium bottles.

The Intertank Section

The intertank section provides structural continuity between the _ andRP-I tanks.

The RP-I (Fuel) Tank

The RP-I fuel tank, located between the thrust structure and the intertank

section, is a cylindrical aluminum structure with a capacity of 218,900 gallons.

Antislosh ring baffles are located on the inner walls while cruciform baffles

a_e located on the _ower bulkhead. A lightweight foam material, bonded to the

= lower bulkhead, serves as an exclusive rise to minimize unusable residual fuel.

The Thrust Structure

The _hrust structure provides support for the five engines, the base heat

shield, engine falrings and fins, propellant lines, retro rockets and environ-

mental co,_trol ducts. The lower thrust ring also has four-holddown points to

restrain the vehicle, as necessary, from liftlng off at full F-I engine thrust.

P_ogo Sup ress_on

The longitudinal o_cillation in the LV, or "Pogo" effect as it has been ,-

called, has been supressed by utilizing the iOX prevalve cavities in _he fou__[

; outboard englnes as surge chambers. Each of the four cavities is pressurized

with gaseous helium (GHe) at T -Ii minutes from ground supply. Initial fill is

: closely monitored using liquid level resistance thermometers. Ground fill main-

rains cavity pressure until umbillcal disconnect after whlch pressure is main-

talned by the cold helium sphere_ in the LOX tank. Pressure readings are

. transmltted via telemetry to ground monitors during flight.

40

1970011707-041

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1970011707-042

F-I En_2_.IneOperation

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

,0.. _ r tank pressure to the thrust chamber and allows control fluid to enter

the gas generator. Opening of the gas generator va]ve permits LOX and RP-I toenter the gas generator combustion chamber where they are ignited by the turbine

:. ,:xhaust igniters, k_ile the RP-I reache.= ,"_proximately 375 psiF_ a valve in thehypergol cartridge opens allowing LOX and ]_-i to build up pressure against thehypergol burst diaphragm. At approximately 500 psig the diaphragm ruptures

allowing hypergol and RP-I to enter the thrust chamber causing spontaneouscombustion upon contact with the LOX, thereby estahlishing primary ignition.

As thrust pressure builds up the RP-I valves open admitting RP-I to the thrust,: chamber and the tr_nsistion to mainstage operation is achieved.

Th( inboard engine engine is cutoff by a signal from the IU. Outboard engines are

cutoff oy optical type LOX depletion sensors with fuel depletion sensors as back-

up. A command from the IU supplies a command to the switch selector to enablethe outboard engine cutoff circuitry. W11en two or more of the four LOX level

sensors are energized, a timer is activated. Expiration of the timer energizes

• a stop solenoid for each engine which energizes the main LOX and main RP-I valves.

: _ TI, sequence closing of the main LOX valve followed by sequence closing of themain RP-I valve interrupts propellant flow and terminates engine operation.

J

Enq'lne. Confrol Valve "Open" 5i.3n_t .- -

_:-. Oxb_i_r Va|vcs Open _=_ -_- _ I

O,_s Oznerat"=, _4alvz _ _ r_ "Open

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1970011707-043

S-!rC ST.\GE PROPELLAI(T SYS'J t,7,I

Tile S-IC stage propell:,nt svstem is co:,lpnsed of one LOX tank, one RP--1 tank,prope11;mt ]ines, control valves, vcnts, and pressuri_'ation subsystems. Load-

ing ol L0X and RP-I tanks is controlled by ground computers. RP-I loading is

completed approxii,_,r,tcly nine d-ws prior t_ ]iftoff. },OK bubb!in?, is startcd ia

at the (,e,_:inningof LOX chllldo,<n operation aad is continued throughout LOX ._

loading and again before liftoff to prevent possible gcyscring. Prior to Jilt-

off the RP-I tank and the LOX tank is pres.qurized by hcl_um from a good source.

At liftoff the RP-] tank is pressurized with helium stored in bottles located in *_o

the LOX tank and heated by passing the helium through.the heat exchanger. LOX

tank pressurization is maintained by LOX'bled from the engine and converted to

GOX in the heat exchanger. :1

S-IC PROPELLANT I,OAD A)_ OPERATIO'CAL SEQUEXCE _"

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1970011707-045

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1970011707-046

,¢_,!S-IC SI'AGE TIIRLI'ZTVkCT9R CONTROL S_. _EI-i

The fo_,r outboard F-I engines are gimbal mounted on the stage thrust

_tructure to provide attitude control durlnp S-_C stage powered flight. Each

]_dt-pendent gimbal system employs t,:o hydraulic servo actuators. These servo

actuators copvert electrical command signals (from IU Flight Control Computer)

and hydraul_c presmure into mechanical outputs ,.:hlchgimba] the outboard engines .

on the S-IC stage. ._n integra_ mechanic,l feedback, varied by piston position,

modifles th.. effec= of the control signal from t:_e FCC. Built-in servo actuator

po_entiemeters se_,se servo actuator p,_si_ions for telemetry as well as providing !

an _.nterleck to preclude !iftoff with a,, engine hardover.

Hydraui_c pressure is supplied to the X1lrust Ve'etor :ontrol System from a

• GSE pressure source duz'iug prelaunch checkout and engine start. The GSE pressure

source utilizes RJ-]. ramjet fuel as the hydraulic fluid. During engine operation,

hydr-.ulic pressure _s supplled from the fuel discharge of the engine turbo pump

to the se_vo actuators. The fuel returns th:ough a check valve to the fu;! inlet

of the turbo pump. RP-.I, the fuel used by the S-IC stage, is used as the hydraulic

fl,dd during englnc operation.

_B

1970011707-047

S-If STAGI"STRUCTURE

The S-II stage ib a large cy]Indrlcal booster approximately 8] feet in length

and 33 feet in diameLer. The _tag¢:is powered by five llquid-prop=l]cd J-2 rocketengln-7, _'bich combine to develop a total thrust of 1,i50,000 pounds.

Forward Shirt

_he forward skirt, z, part of the S-If body shell structure, is a cylindricalaluminum alloy material, strenghened and supported internally and externally 'stringers and circumferential ring frames, the fo£ward skirt also houses theLelemetry and command (range safety) antennne.

, The Fu_Tank

The LH2 tank ts a long cylinder with a concave bulkhead forward and a con-vex bulkhead aft. The tank structure is made up of six cylindrical sections whichincorporate stlffonlng members in both the ]ongitudlnal and circumferentialdirections.

The /:on=on Bulkhead

This is an adhesive-bonded assembly of aluminum alloy and flberglass/phenolic

honeycor_b core to prevent, heat transfer and retain the cryogenic properties of thefluids to which it is exposed (LOX and LH2). Fiberglass core materiel varies inthickness between .080 inches to 5 inches. No connections or lines pass through_he common bulkhead.

The LOX Tank

_ha LOX tank consists of _.!lipsoidal fore and aft halves with reinforced

gore segments. Three ring type slosh baffles control propellant sloshing and

minimize surface disturbances. A six part sump assembly at the lowest point

provides fili and drain openings for the five engine feed lines,

Aft Int_

The aft interstsge, also part of the body shall structure, is made up ofaluminum alloy mater_al and is supported internally by hat stringers and circum-

t ferential ring frames. The af_ inter,_tage has four ullage rockets mounted in itsouteg surface,

System Tunnel ,.

The systems tunnel houses el_ctrlcal cables, pressuri_atlon llnes and the

propellant dispersion ordn_aca, The runnel is attached externally from the $-I! ,.stage aft skirt to the forward skirt,

i

,':,......: I II I

1970011707-051

•bv_t:-'l_,goO Ib'_.,_t }'11 Iq,_ifion: ID_a_,qOOIk_

, ,,/t__,'11CufuF_':" q4,xa(l_lb,_•At '5-11"_p_ra_ior_:.., q4, I0 0 tb_

51

1970011707-052

J-2 EN(; NE OPE,.AI_ON S-If STAGE

T_ ,perating cycle of the J-2 Engine consists of prestart, _ttatt, steady-

..tat, :. _ation and cutoff sequences. During prestart, LOX and L|{2 flow through

tlle e,_},ne to temperature-condltion the engine components, and to assure the

presence of propellant in the turbopumps for starting. Following a t_med cool- !down period, the start signal is received by the sequence controller which ener-

gizes various control solenoid valves to open the propellant valves in the proper

sequence. The sequence controller also energizes spark plugs in the Ras generator

and thrust chamber to Ignite the pTopel!ant. In ,dditlon, the sequence controller

release GH 2 from the steer tank. The GH 2 provides the inlt_al drive for the turbo-

pumps that deliver propell_t to the gas generator and the englne_ The propellant

ignites, gas geo_rator output accelerates the turhopumps, and engine thrust in-

crea es to main StaRe operation. At this time, the spark plugs are de-en-°rgized <

and _he engine is in steady-state operation,

I

_teady-state operatlcn is malnta._ned until a cutoff signax is received by

the sequence controller. The sequence control]er de-energlze= the solenoid valves

which in turn close the engine propellant valves _n the proper sequence, As a

result, engine thrust decays and the cutoff sequence is complete,

%

ED%,_aeStart q

Main F_l Valve Open m 'i

•:'. '.". _,dn Fuel PropelleJ,t Flow ...... -_,_ II _4_lRk_.

Start Tank Discharge Valve Open IllPump Buildup _ _ ' .!

Bypass Flow Through Oxidizer ---,_ __ __Turbine B'j-pass Valve

• • Main Oxidizer Flow "-" i _' '

[G_.e Generator Propellant Flow ___ _-T. __ "_-

, . Main Oxidizer Valve Open R .. ,

' Mainstage OK Signal V . i

t"

90 Percent Thruet V

_' IGNFI _ON. SgC ,_.C S¢C Slr.c St:, •., COM_U,4D=

e_TIME FROM I_N|TION

g_

9700]]707-053

S-II STAGE PROPELLANT SYSTEM

The S-If Stage propellant system is composed of integral LOX/LH2 tanks,

propellant lines, control valves, vmts, and prepressurization subsystems.Loa@ing of propellant tanks and flow of propel]ant_ is controlled by the pro-

i " pellant utilizatlon systems. The LOX/LH2 tanks are prepressurized by groundsource gaseous helium. During powered flight of S-II Stage, the LOX tank Is

pressurized by GOX bled from the LOX heat exchanger. The LH2 tank is pres-! " surlzed by GH2 bled from the thruqt chamber hydrogen injector manifold:

pressurization is maintained by the LH 2 Pressure Regulator.

S-If PROPELLANT LOAD AND OPZP_TIONAL SEQUENCE

54

] 9700] ] 707-055

P LHz Tank Venf Valve {.2)

--15_, 2_o tb_ LK._ i

". Res_ia_or of.m, -?._ --'[3seconc[s aN_r 5-11

t' _jniHort ¢_1drdm_a;ns

ti

Ll%. F_Hana Dra,nr-_l- : ___o_T_,,kv...-v.,...(_I I II op.n :{4z p,a

L I LOX T..k CIo,e 39p._a

i ! ,..,@Z.l, ooo 16_,.LOX Ia+ 19_;,_;0.i I '

ii I

H. �E_d_.S,,'--[]Co.v.r s I.OX Jm t I

, G,OX_er LOXTank F_ur';_.,_+;?-

O"_'Englnc (6)

_bo_e LOX aM LH_,

; tach en_3tl_ To t�À�pr_p_l_n__ Ig_if_o__" - 9_93.50 ibm.

_,, _,__r._.,_ _-_

1970011707-056

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. ,\t'_tude c_ntr61 is maintained by gimballing theoutboard engines in response to electrical control signals flora the IU flight _._

_'ontroi computer.

i The system consists of four independen_ closed-loop hydraullc control ,_subsystems which provide power for engine gimballing. The primary components

of the subsystem are an auxiliary pump, a main pump, an accum,.,iator/_eservoir _

: manifold assembly and two servo actuators. The auxiliary pump is electrically . ._driven from the GSE to prov.ide hydraulic fluid circulation prior to launch. The

, main pump is mounted to and driven by the engine LOX turbopump. The accumulator/ ._.... _,_ .,o_,,,_j consisEs of _ pressure _cumu±_Lu_h_g,L which r_c,:iv_

' _ high pressure fluid from the pump and a low pressure reservoir which receives re-

_ turn fluid from the servo actuators. The servo actuator is a power control unit thatconverts electrical signals and hydraulic power into mechanical outputs that gimbal

i the engine.

! During the preTaunch pcriod, the auxiliary hydraulic pump circulates the ._

i hydraulic fluid to preclude fluid freezing during propellant lo_ding. Circula- Ition is not required during the S-IC burn due to the short duration burn. After a

! S-IC/S-II separation, an S-II switch selector command unlocks the accumulator

I lock up val_,es, releasing high pressure fluid to each of Zhe servo actuators. iThe accumulator_ provide gimballing power prior to the m.._inhydraulic pump

operation. During S-If mainstage operatiou, the m_lu hydraulic pump supplies

high pressure fluid to the servo actuators. The r_turn fluid from the actuators

! is routed to the reservoir which s_ores hydrarlic f_uid at sufficient pres_,,re

i to supply a positive pressure at the main pump inlet°

i

I

7; 6_

] 9700] ] 707-057

I

J-2 ENGINEOPET_ATIONB-lV_ STAGE

T'n_operating, cycle oi the J-2 Engine consists of preetartj startt steady-stat_ operatlo_ snt! c_toff sequence_, During prestart, LOX and LH_. flew through

' the engine to temperature-condition the engine components, and to assure thepre_enec of propellant in the turbopumps for _tartin8, Following a timed cool_d_n period, the start signal is received by the _equence controller which on, r-

• glzes variou_ control solenoid v.alves to open the propellant va]veo in the proper .sequence. The sequence controlJer also energizes spark plugs in the gas generatorand thrust chamber _o ignlte the p1"opellant, In addition, the bequonce controller

'_ , releases G]I2 from the start tank, The 01t2 provide_ the initial drive for the turbo-pump_ thet deliver propellant _o the gas generator _nd the engine, The propellant ."

il/ ignites, gas get;crater output accelerates _.he _urbopumps_ and engine thrust in-

creases to main sts3e operation, At this ttme_ the spark pl,ags ere de._energtzedand the engine is in steady-state operation,

Steady-state operation is metntt;ined until • ct_toff signs1 is received bythe sequence controller, The sequence controller de-energizes the solenoid valveswhich in turn cloe,e the engine propellant valves in the prope_ sequence. As itresult, engine thrust decays an_ the cutof_ sequence is eompleteo

I, Engine 8tart _

Main Fuel Valve Open i

Main Fuel Propellant Flow

• _tart Tank Discharge Valve Open m

'2.rap Buildup ........... "......

Bypass Flow Through Oxtdt_er .....i Turbine By-pass Valve

' Main Oxidizer Flow II II II Jl[ Ill[_ ..... :-

Oas Generator Propellant Flow .............

Main Ogldi_4,r Valve Open ..

Malnstage OK Signal

i y ""90 Percent Thrust

1ONIWIOM , _g{. MC egO, JJ_ _g¢_

:"i COld_ktlL_._. FROM ,,MIT,ON

.Ll

9700 707-068

e 41_e'

! $-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 and pre_urlzat£on _ubsygtemso Loadtngcf the prc_ella_c tank_ and flo_ of propellants i_ contro]led by the propell_,ntutilization _'_tem. Both propellant tanks are lni_ially preosurized by groundsource cold helitn..

_JX tank _ressurizatJo_ during S-IVB stage burn is maint.]_.ned by hellumsuppi_.ed from spheres in the L]I? tank, _hich is expanded by passing through the

; heat ex'.'han_r, to maintain positive pressure across the co_on tank bulkhead! and to satisfy engine net positive auction head, I,E z _.ank pressur_zation during; 5-ZVB stag_ burn is maintained by GII2 from the J-2 engine injector, Pressuriza-

tion o_ _he LH2 tank strengthens the stage in addition to satlsfying engine natpositive suction head.

Repressurization of the pr_ellnnt tanks, prior to J-2 engine .restarts, is

! sttalned by passing cold helium, from the helium spheres in the LH2 _ank,

i through the O_/H2 burner, The heated _ellum is then routed to the propellant' ranks, Should the O2/H2 burner fail, ambient repressurlzation will ensure

propellant p_essure engine restarts,tank for

$-IVB PROPELLANTLOAD AND OPERATIONAL S_NCE

_r.,,

1970011707-070

\

!i4

• _ S-IVB TBRL'-ST VECTOk COntROL SYSTEM

i.The single J-2 F_gine is global mounted on the lengltddtnaI axis of thei

S-IVB Stage to provide pitch and ya-_ coatrol ddring S-IVB powered flight. Engineflmb__Itpg is ac¢om_llshed by an independent closed loop hydrauli.:system _:hlch

, sapplies IxJaer to the two servo-actuators. T._o. two servo-actuagor3 may extend erI: retract In41v!dually or simultaneously. Gimbal position Is propoctlonai to the •

} magnitude of an elec trical input to the electro-hydraulic serve valve located on

each actuator. Mechanical feedhack from the actuator to the sfcvo valve completes •the closed engine position ]oop.

J

l Duriu_ S-IC and S_II stage burns, the actuators hold _he engine position to ,

i null. 1%is is accomplished by utillzi_g the electrically driven auxiliary hydraullc

pump. _he auxiliary hydraulic pump is also used during orbit to periodically cir-culate the hydraulic fluid to prevent freezing. Durir& t_e S-IVB burn, the main

I hydraulic pump, driven by the engine, provides the _ccessary pressur_e and circulation

for actuator opecation (pitch and yaw col,trol). Rc_l control is pzovided by theAuxillary Propulsion System (see page 71).

j "1

.t"t

! •

'i

1

t -2

t

'! y

I

_ 2

3 _

! -

1970011707-072

"%

--I'!0 p_i9 |Vehicle Thrust _t_

!! I _...... " - , I / Ad_tor \ i-

)' _ . :

, bri,te_ Engine.

put 80_ af __E_50+_Opi_ M _O°F

)

) _ _oxili_iel__ _._ _T_:/ Au_ilia_l _mp cr_edd_vl_t pr_|ic_hf

i!! iEled'_c Mof_" d_.,%u't _ doHn9 _'li_hf

¢Iriven _ l'J.O00 RI)M

I) _l_l poitft // Yauu_xls , _,"

..I_,.

: "_,, Glmbal

] 9700] ] 707-073

\

AUK_LIAR¥ PROPULSION SYST_

The S-1VB Auxiliary Propulsion System (APS) provides vehicle attitude control

_. ._,jringpowered flight in the roll axis only and durln B S_IVB coast provides

contzol in the pitch, yaw, and roll axes. Attitude corrections ar_ made by firingthe control englnes, indivld,:ally or in combination, in short bursts of approxl-

¢ -

mately 65 ms minimum duration, Commands from the Flight Control Computer actuate "fuel and oxidizer solenoid valve clusters that admit hypergolic propellants to •the control engine combustlon chambers. 4

The attitude control engines are located in two aerodynamically shaped ._.

i modules, 180 degrees apart, on the aft end of the S-IVB s_age (positions I and

I!I). Each module contains four hypergolic engines, three 150 pound thrust :,; , ".- attitude control engines and one 70 pound thrust ul3age engine. The 70 pound

!. • thrust (ullage) engine £n each module is used to settle the main stage propel-

' I lants a§ter SrlVB cutoff and again prior to restart. One control engine of

_ each module is used to control the vehicles' attitude in pitch, while the other ,two are used for yaw and roll control.

Each APS module contains its own propellant supply and pressurization system•': _ The hypergolic propellanLs used by the engines are monomethyl hydrazine _)

i for the £uel and nitrogen tetroxide (N20_) for the oxidizer_ Helium is thepressurant used in the system.

,•

!

1970011707-074

,.

S-IVB STAGE PROPELLANT MANA(;L'MENTSYSTE,_!l

The propellant manap, er_ent system provides a means for _ontrolling andmonitoring prope]lant_ during ground loadin_., powered flight and engine shut-down,

Continuous capacitance probes and point level sensors in the LOX and LH2 ,tanks monitor propellant mass. During the propellant loading sequence, a signal . wmifrom each capacitance probe is transP._,ttcd from the on board propellant elec- • 1' iron!c__ to GS£ +o _,',_-'_ _,_ level _ ..... 11.....in the _-"'....; ................ v."r ................ Overfill pG_,_,.level sensors are pxc.-,ided for LOX and LH2 systems, k_en the propellant mass in the

; tanks re_ch a predetermil_ed _=.__t,-,- the GSE loading co_.,_uterautomatically stops ,; the loading sequence.It

J i

!_ The propellant utilization (PU) subsystem controls the mixture ratio (MR)

_' of the LOX/LH2. The PU subsystem consists of a rotary valve, t_ control _ ,et : amount of LOX flowing to the engine, and electrical controls for th._valve.

The }LR is controlled by _he switch selector outputs wh'_ch are used to _perat_: the PU valve.

Prior to engine start the PU valve is commanded to the neutral position to

= obtain a MR of 5.0:I. Th_ PU valve remains at the 5,0:I posltloll during the: first burn. Prior to engine restart (first opportunity) the FU valve xs tom-

• mended by the switch selector to a MR of 4.5:1 and remains at this position for_ _ appruxlnmtely one minute m:d 55 seconds of the S-IVB burn. The PU valve is then

commanded to the neutral position (5.0:I). If the S-IVB restart is delayed to: the second opportunity, the MR is shifted from 4.5:1 to 5.0:1 when the engine

j, •

• reaches 90 percent thrust.

"__ Engine shutdown, during first burn, is initiated by a programmed command

2 (velocity) from the IU through the switch selector. Engine shutdown after_ second burn is Init_e_.c_ by a programmed conma,,d (velocity) from the IU through_ the S-IVB switch selector. Backup shutdown is provided by any two of the five

liquid level sensors in either, propellant tank indicating propellan ._ depletion.

i

_i ,"

C

] 9700] ] 707-076

o

INSTgUHENT UNIT

The Instrument Unit is a cylindrical s'tructt_rc arproximately 260 inches inditeter and 56 inches high which is attached to the forward end of the S-IVB

• stage. IU s_ructure is composed of an aluminum alloy honeycv_b sandwich material

which was selected fo_ its high strength-to-weight ratio, acoustical insulation,and thermal condmcclvity properties.

The cylinder is composed of three 120 degree segments--the access door J! segment, the flight control computer segment, and the ST-124-H segment°

'/he IU Stage contains:

Guidance, Navigation and Control Equipment7

Telemetry Systems

Tracking Systems

Crew Safety Systems

Envlronmental Control System

The guidance_ navigation and control equipmen t contained in the IU includesthat. which is necessary for _ehicle gu._dance and control during boost throughor_,Ital coast and subsequently for translunar injection.

Telemetry along with measuring systems is used to monitor certain conditions

and events which take place in the IU and to _rans_it these monitored signals toground receiving stations,

Tracking _yst__ms assist in the determination of the vehicle's trajectory.Tracking data is used for mission control, range safety and post flight evalua-tion of vehicle performance.

Crew Safety is provided by the Emergency Detection Systcm_ a portion of whichis located in the IU stage. EDS senses conditions in the vehicle during boostphase which could cause vehicle failure.

_nvironmental Control maintains an acceptable o._tating environment duringpreflight Ind flight operations.

@-

1970011707-080

%

¢/y.

1970011707-081

1970011707-082

ENVIRON_._ENTAL CONTROL SYSTEH (ECS)

The Environmental Control System (ECS) has been developed to maintain an

acceptable _perating environment for the IU/S-IVB equipment during preflight

' and _nfllght operations.

The ECS is made up _f the following: .

' Thermal Conditioning__'stem - maintains a circulating Methanol Water ,

coolant temperatuee of approximately 59 ° _ I°F.

! Preflight Purging System - maintains a supBly of temperature and ."

pressure regelated air/GN 2 in the IU/S-IVB equipment.t

:_ Gas BearlngS_ - furnishes GN 2 to the ST-124-M3 inertial

platform gas bearings.

Hazardous Gas Detection Syste___mm- monito:s the IU/S-IVB forward inter-

stage area for the presence of hazardous v_pors.

J

:]

z

1970011707-084

I_/I'IVB _vi_m_.t"al ' ---

19700"I1707-08,5

-%

r - °.

SPACECRAFT DESCRIPTION

L The Spacecraft for the AS-50_ mission is composed of:

Launch Escape System (LES)

Command Module (CM)

;. Service Module (SM)

Lunar Module (_I) 0Spacecraft Lunar Module Adapter (SLA)

Launch Escape S_ste m

The Launch Escape System, which is Jettisoned approximately 35 seconds after

S-II Ignition, is made up of a Launch Escape Tower (LET), and a three-motor pro-

pulsion system (Tower Jettison, Launch Escape and Pitch Control Motors).

jl; "Command Module

The Command Module is a Block II Configuration. The module's inner struc-

ture, or pressure vessel, is separated fzom the outer structure by a layer of

" insulation. A heat shield structure is made up in three segments consisting of

a forward heat shield, a _rew compartment hea_ shleld_ and an aft shield. The

(24 is slightly over ii feet in length and is about 12 feet in diameter. A"

• propulsiot_ system consists of Reaction Control Engines which may operate pulsedor continuous.

Service Module

' The Service Module maybe described as a cylindrical, aluminum shell which

• is mad& up of honeycomb-sandwich panels and a forward and aft bulkhead. Oke

gimballed propulsion engine (capable of up to 30 restarts) and a reaction control

system (4 clusters, 4 chambers each) make up the Sl! Propulsion System. The Com-

mand and Service Module are Joined by three tension ties each of which is

equipped with explosive charges for SM/CMseparation.

Lunar Module

The Lunar Module consists primarily of an Ascent and Descent Stage. The

Ascent Stage, which contains the crew compartmettt_ is equipped with a Reaction

Control System which provides thrust capability, an ingress and egress hatch to

the _rew's instrumentation and controls. The Descent Stage_ consists primarily

. of a descen_ engine a,d four retractable landing gear assemblies. Over all

, weight of the Lunar _odule is approximately 30,000 pounds. -"

Spacecraft Lunar Module Adapter

The spacecraft Lunar Module Adapter (SLA) Joins the S_rvlce Module (SM) to

the S-IVB/IU. The SLA encloses th6 Lunar 14odule. Adapter panels which enclose

the Lunar Module are Jettisoned prior to docking and Lunar Module extraction.

_/

i; _z

1970011707-086

II

a

_io I t fError" J Guidance J

ba LCom_nd_

Error" I Co_,,_ J P_ef\ I Module I

5ub_#e_i i Z_V Power"

I n,l,,, /.

c_ronic_ q PowerI (AccM.,5"_ai:iliztHiDn I'---'" _ 3upplit._

IU ,.

r'U-- I

L ou'_nce I• <...c_,__.j

1970011707-088

"__M To_ To_P_ To_Mdetti_,o¢_ E_;mb_l Eir_bal ,3¢ffi<Jot_

i-_, _ao 1i J

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Oni_ I un;_ l

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1970011707-089

_¢.: tblock ]]. (manrted,)

• --,lO0Ib-_ "TT_rv_r_ach

/_¢,z ."

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1970011707-090

_ _V,_,l._mL':_ 8"f "' Ii

1970011707-091

a PRou..'!I_IBI_LITYOF,THE e]@[_I_J__

• _ ,,- "55,_00 Ibs. 1

J

V_idJrh"-"3_0i,_ (;t.q'__'x'l'endcd)

•Di_e?er~t'_7 in (. ..... =_nt s+_3__ w_°,,_ tSodj) "•Propubion __{_m :-ID°,c.n{-Eo,,o._ ITh'ro'H'I¢con,IroIIe.dfhrus'I"

_' _ror_ I000 ]fo lO,r_OO ',b_.

\ - I A_cen_" En.91ne.." '" ':,500 _b_. i'_.vu_'t

" ; l_e_c}ion con_rolle_J _o'I'o_5(_ ctusfev-_/Ac.h_rnbev-_ e_h')

",oo lb. thrusf ..c6 m.to.. I Lun.r Module" II:. _Figure _?.-, .. h;2

1970011707-092

o

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Af_it_a _af_

. _"' l

• I Tr_la 0�Ì�_on_roller / h;qltal Uplinl_J' ! -- Mu_Ication

Tr_.',_i_¢ion I .Update

P_nq_._.at¢ _dar /f'_,C_,inq I

Throffle

Conw_nd_

I I_>urin_ t _ Guldance _'Elec_rr_nlc'_,_ _"_'_ u.i_ I A_lev_tlon Compute r -on-_or_o_--/_ec+_°n

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F_ .+L_ �Œ�F--_J.e La-/-. ' /

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_ure 5_ He_iqa_ion "_re_

9700] ] 707-093

VH_ 5-5ond _-lSand 5- bar_JInf'li_Wt EVA Cr_n; 5_,'e.rabl& [/ccfabl_

A,_+_nna Arrf_r_ra. A,Nenr_a¢ A,vl'e_,,a An+,:_na

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1970011707-094

MOON St;_.7A_E

ti f.)/A (Ev,fr._Vih;c_lar Ac _,lt cx,n'_i_.'i-oF;* Lu.,-_¢ W,Bllc

' • • , :_ll< 4, "at': ,_,_d rock "_tapl,'_.' ".,_f ,a;- t_r_.r;,,lcm4", £o¢ u_

LOk.'S,a_a_AC_-_'_q..7_.3_ ,CoM,_,',JkiiCATI..0 !45 _ ...... ,

1970011707-095