Apollo 10 as-505 Apollo Saturn 5 Space Vehicle Technical Information Summary

8/8/2019 Apollo 10 as-505 Apollo Saturn 5 Space Vehicle Technical Information Summary

1/95


2/95


3/95


4/95


5/95


6/95


7/95


8/95


9/95


10/95


11/95


12/95


13/95


14/95


15/95


16/95


17/95


18/95


19/95


20/95


21/95


22/95


23/95


24/95


25/95


26/95


27/95


28/95


29/95


30/95


31/95


32/95


33/95


34/95


35/95


36/95


37/95


38/95


39/95


40/95


41/95


42/95


43/95


44/95


45/95


46/95


47/95


48/95


49/95


50/95


51/95


52/95


53/95


54/95


55/95


56/95


57/95


58/95


59/95


60/95


61/95


62/95


63/95


64/95


65/95


66/95


67/95


68/95


69/95


70/95


71/95


72/95


73/95


74/95


75/95


76/95


77/95


78/95


79/95


80/95


81/95


82/95


83/95

ENVIRONMENTAL CONTROL SYSTEM (ECS)

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

acceptable o perating environment fo r th e IU/S-IVB equipment during preflight andinflight op eration s.

The ECS is made up of the following:

Thermal Conditioning System - maintain s a circ ulat ing Methanol Watercoolant te mpe rat ure of approximately 59'

*1'~.

Preflight Purging System-

maintains a supply of temperature and pressureregu la ted a i r /~Nz n th e Iu/S-IvB equipment.

G a s Bearing Supply System - fur nis hes GNa to the ST-124-M3 in er ti al---platform ga s bearings.

Hazardous Gas Detection System - mon itor s the IU/S-IVB forward in ters tag ear ea for the prese nce of hazardous vapors.


84/95

Methanol.

(closed

Watersysfem)

Wa*

TW)

,Tapped holes

\ Coolanf core


85/95

SPACECRAFT DESCRIPTION

The Spacecraft fo r the AS-505 miss ion i s composed of:

Launch Escape System (LES)Command Module (CRI)Service Module (SM)Lunar Module (LM)Spacecraft Lunar Module Adapter (SLA)

Launch Escape System

The Launch Escape System, which is jettisoned approximately 35 seconds afte rS-II Ignition, is made up of a Launch Escap e Tower (LET), and a three-motor pro-y lision system (Tower Jettison, Launch Escape and Pitch Control BIotors).

Command Module

The Command Module is a Block II Configuration, The module's inner str uct ure ,or pressure vessel, is separated from the outer structure by a l ayer of insulation.A heat shield structure is made up in th re e segments consisting of a forward heatshield, a cre w compartment heat shield, and an aft shield. The CM is slightly overli feet in length and is about 12 feet in diameter, A propulsion syst em cons ist s ofReaction Control Engines which may op era te pulsed o r continuous.

Service Module

The Service hlodule may be d escribed as a cylindrical, aluminum she ll whichis made up of honeycomb-sandwich panels and a forward and aft bulkhead, Onegimballed propulsion engine (capable of up t o 30 re st ar ts ) and -a reaction controlsyst em (4 cl us te rs , 4 chambe rs each) make up the SM Propulsion System, I"lle Com-

mand and Service Module are joined by 3 tension ties each of which is equipped withexplosive cha rge s fo r SM/CM separation .

Lunar Module

The Lunar Module con sis ts prima rily of an Ascent and Descent Stage. The AscentStage, which contains the cr ew compartment, is equipped with a Reaction Control Systemwhich provides thr ust capability, an ingr ess and e gress hatch to the crew's compartment,VHF, S-Band and Rendezvous Radar capabi liti es plus numero us instrumentation andcontrols. The Descent Stage, consists primarily of a descent engine and four retractablelanding ge ar assemblies. Over all weight of the Lunar Module is approximately 32,000pounds.

Spacecraft Lunar Module Adapter

The Spacecraft Lunar Module Adapter (SLA) joins the Service Module (SM) to theS-IVB/IU. The SLA encloses th e Lunar Module. Adapter panels which enc lose theLunar Module are jettisoned prior to docking and Lunar Module extraction.


86/95

Launch E5cape S y s

C o m m a n d M o d u \ e

W e i h :

L i f t o f f -* 107,400 Ib)A t Inje~%on98.500 \b.

*(LES ~ g t .ncluded i- L E 5 &eight - 8900 b5.-Command kfodult - Z.300lbs.Service Module * O.bOO Ibs

-Lunar Modu\e -. 30.850 1bs.

k 26 0 " 0ia .--4


87/95

Oroaua Chutes bedoue- I rnin after parachute, &

descent beg1 ns droque chutc.sart jetf;soned and mainchutes are deployed.

3 5 D ~ o r b i t Rurn and CM/SM Separation

Marn Chutes Rebased

Main ChutesFul lg Deployed

Note:

The desired Clob+,on modeaCfer splashdocon j 5 w i t h

M ain Chuteas Releas.-_-_

To achieve -this m o d e ,are feleascd

from the fovward hatchceusinq t h t modute t of l o a t upriqht.

A W X DOUIR


88/95

r

VHFRecovery

8agcorl

omniAntenna

(3)( 4 )

r 9

Triplcxcr

i

S -Band RondavoL)~Radar

AnCenna Transponder

Ir

U p - Data +TO PCML i n k

6

*V

7

vH F A t 4

Tran6cei vev

4a

5- BandPower

Ampl ifid

1

t

A

r

4 LlniFied5 Band

E q u i p m e n +

FZ-ernduiatim (PM,F l r l \ )Processor

42

Central

C

T V +

4I

Avd iaCe n+et-

?-

4

-A Yi m i n q

Equipment4

. 1 +-

T

PCM SignalTe\eme+r./ Con di Cioning

Eqoi prnenf Ealuipmen+i

Da as t o r a q eEeo; ? m a t

4-


89/95

To Reaction Control SysftmFuel Pump I Sequetwers

115112 Vac , 400-, 3 d ToD a f t chaqer #

SIC Y power ~ y s t e m B a t t q A4

B a i t r y BA 4 To f l iqhf f

Ti EDS, ELS, Loqic Cbd hndinqMission Seq*ncers, bus

Qimbal Control 1 (comnonicati~h

f r o m Batt. Charger

Scienfif icScitnf Qic

I n ~ u m e n t a t i o n

Command Module

Service M b d u \ t To SPS

J 4 H i s o n 3etkisan

Con+ro(lers I I Conf r o I er s*

Fuel Cell Fuel Gll Fuel &UUnit 9 h ii t 2 Uni t 3 -

PowerTo S C System

I n c t ~ m e n t a * n


90/95


91/95

3 - Band AscenS VHF Docking

RC3 Thrus+Cham ber


92/95

_- .

I . . . , . . - * . - . . . _ , , . , .. ,... -. . . . . -. . . _ . - , . . . .. . .


93/95

Section II

hiqita\ Uplink A % m b \ y(Cmmurlication

Subrystem)

Crew Dirplays

4 4 4

t t

b q cFG & hR e n d t ~ v o u ~

Radar'

rInert ial

Aeifudt LM

1

.

,RW,todcMcawr'nq Accrtera t ion

Unit Section

bJ+ttudc Cadins Aliihde R C 5 J &Altitude Ra)c Radar !l%tudc Fbh. Ld CommandsFwd+La+ V t I ~ t i I y +Lot veiociiy

Abort

scctian

I

I S+ar: Siq)l+ingI bata


94/95

LM Communicat ionsSub ~ y z i t e m


95/95

DISTRIBUTION

DIR

AD-S

DEP-T

P A

DIR-PM

I-K

P M - E P

PM-MO-MGR

PM-MO-F

PM-MO-OL

PM-MA-OB

I-RL -(MSC L iai so n)

KSC (LVO-5)

KSC (SO)

PM-SAT-MGR

PM-SAT-MGR

PM-SAT -E

PM-SAT -E

PM-SAT-T

PM-SAT-QPM-SAT -F

D r. v o n B r a u n (1 ) A&T-MS-IL

D r. R e e s (5) S&E SSL-DIR

M r. N e u b e r t (40) S&E DIR

M r. J o n e s (2 ) PM-SAT-MGR

Gen. O'Connor (1) PM-SAT-ED r. M r a z e k (1)D r. F a r i s h (56)

M r. M o n t g o m e r y ( l o ) S&E -CSE

M r s . Wa t s o n (2 5)S&E-COMP

S&E-ME-DIRD r . S p e e r (5 )

M r. P a r k ( l o )S&E-QUAL-J

M r s . N o r m a n (15)

M r. N u b e r ( lo)

M r. H a m i l t o n (200)

M r. Wi l l i a m s (250)

M r. G o r m a n (9)

M r. J a m e s (2)

M r. B r a m l e t (1 )

M r. B e l l (1)IBM Te c h . L i b r a r yHSV

M r. B e a m a n (5 ) IS-CAS-42CKSC

M r. B u r n s (2 )NA/Rockwell

Mr . Moody (1) Boeing SIDM r. R o w a n (1)

L i b r a r y (2)

D r. S t u h l i n g e r (2 )

M r. We i d n e r (2)

M r. T i e r (1 )

Mr. Huff (1 )

M r. Te a g u e (60)

M r. R i c h a r d s (2)

M r. C o c h r a n (6)

M r. K u e r s (10)

M r. K l a u s s (10)M r. C r e w s (1 )

M r. D r i s c o l l (5)

Dist "El1 (258)

M r. A r d e n (20)

M r. S c h a r (12)

Dist "E" (140)

M r. M o o n (60)

P. 0 . Box 1250 (2)Huntsv i l l e 35807

H. C. Kel ley (2)L i b r a r i a n

M r. A n d e r s o n (1)

Mr. Runkel (I)

Date post:	09-Apr-2018
Category:	Documents
Upload:	bob-andrepont
View:	215 times
Download:	0 times

Apollo 10 as-505 Apollo Saturn 5 Space Vehicle Technical Information Summary

Documents