AS-203 Technical Information Summary

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P r e p a r e d by:

R-ASTR-S- 85-66

J une 14, 1966

ABAMA

TECHNICAL INFORMATION

SUMMARY

R-AERO-P

R-ASTR-S

R-P&VE-VA

- Form 45 4 (Revised September 1961)



AS-203

TECHNICAL INFORMATION

SUMMARY

This r e p or t ou t l in e s , t h rough a s e r i e s of ske tc he s wi th accom pany ing

te x t , th e gen era l fe a t ur es of th e SA-203 Launch Vehicle and informat ion on

l a un c h p r e p a r a t i o n , t h e l au nc h f a c i l i t y a nd m i s si o n p e c u l i a r e x pe r im e nt s .

1. Mission Purpose:

The ba s ic purpose of th e Apollo-Saturn 203 Mission i s t o i n s e r t a

mo di fi ed S-IVB/IU/Nose Cone i n t o a 100 n.m. c i r cu l ar o r b i t wit h maximum l i q u i d

hydroge n on boar d t o e v a lua t e th e hydr ogen ve n t a nd e ngine r e s t a r t syst e ms i n

a n o r b i t a l e nv ir on me nt .

2. Pr imary Mission Obj ec ti ve s:

a. Ev alu ate t h e S-IVB LH2 continu ous ven ti ng system.

b. Eval uate 5-2 engine LH2 c h i lldown a nd r e c i r c u l a t io n sys te m , andu l l a g e r e q ui r em e nt s f o r s i mu l a te d en g in e r e s t a r t .

c . Deter mine c r yoge n ic l iqu i d lva p or in t e r f a c e c onf ig u r a t ion a nd

f l u i d d ynam ics i n n e a r z e r o - g environment.

d. D et er mi ne t h e h e a t t r a n s f e r i n t o l i q u i d t h ro ug h a t a n k w a l l an d

ob ta in da ta re qu ire d f o r a pro pe l lan t the rmodynamic mode l.

e . Eva lua te S-IVBIIU checkout i n ea r t h or b i t .

f. D em on st ra te t h e m i s s io n s u p p o rt f a c i l i t i e s r e q u i r ed f o r l au n ch

an d m i s s io n o r b i t a l o p e r a t i o n s .

g . D em on st ra te o r b i t a l o p e r a t i o n of t h e la un ch v e h i c l e a t t i t u d e

c o n t r o l and the r m a l c on t r o l sys te m s.

h . Demonst rate th e launch ve hi c l e guidance sys tem oper a t io n .

i. D em on st ra te t h e s t r u c t u r a l i n t e g r i t y o f t h e l a un ch v e h i c l e a nd

c o nf ir m t h e s t r u c t r u a l l o a d s a nd dynamic c h a r a c t e r i s t i c s .

3. Secandary Mission Obj ectiv es :

a . Eva lua te launch ve hi c l e powered f l i g h t ex te rn a l envi ronment .

b . Eva lua te launch ve hi c l e sequenc ing system opera t ion .

c. Ev alu ate performan ce of t h e Emergency De tec tio n System (EDS) i n

open-loop con£ gu ra ti on .



d. Ev al ua te se pa ra ti on of t h e S-IVB/IU/Nose Cone from th e S-IB.

e . E v a lu a t e t h e l a un c h v e h ic l e p r o p u l s io n s y s t e m ' s o p e r a t i o n .

f . E v a l u at e t h e MSC s u b c r i t i c a l c ry o ge n ic ex pe ri me n t.

4. P r i n c i p a l Di ff er en ce s Between AS-203 and AS-201:

a. S-IB Stage:

( 1 ) Weig ht r ed uc e d b y r e d e s ig n o f : p r o p e l l a n t c o n ta in e r , b a r r e l

a ssembly , o u t r ig ge r s , and by remova l o f ou tboa rd eng ine s k i r t s .

( 2 ) GOX in te rcon nec t and ven t sys tem redes igned .

b. S-IVB S ta ge :

(1 ) H e av ie r f o rw a rd an d a f t s k i r t s d ue t o r e v i s e d l o a d in g c o n d i t i o n s .

(2) F orw ard s k i r t mo d if ie d t o i n c l u d e n o z z l e s a nd f a i r i n g s f o r t h e

LH2 ta nk cont inuo us ven tin g system.

(3) S pe c ia l LH2 ta nk manhole cov er su pp or ti ng two T.V. cameras

and l i g h t s f o r v iewing LH2 behavior .

( 4 ) Hydrogen ta nk ve nt system modif ied t o s im ula te Sa tur n V/S-IVB

c o n f i g u r a t i o n .

( 5 ) A d d i t i o n a l b a f f l e r i n g i n t h e LOX t a n k du e t o o f f l o a d in g of

LOX.

( 6 ) LH2 exper iment i ns t r ume nta t ion i n t he LH2 tank co ns i s t i ng of

a n a d d i t i o n a l p ro be f o r t e m pe r at u re , p r e s s u r e and l i q u i d v ap or s e n s o r s .

(7) LH2 t a n k b a f f l e t o p r e v e n t p r o p e l l a n t s l o s h in g f o l l o w in g S-IVB

cu to ff and durin g LH2 experimen t.

(8) Add i t io na l LOX tank ve n t sys tem t o s i mul a te Sa t urn V/S-IVB

APS u l la ge eng in e th ru s t .

(9) Ambient he l ium sphere added f o r pa r t i a l LH2 tank rep ress ur -

i z a t i o n f o r si mu la te d r e s t a r t .

c. I n s t r u me n t U n i t

(1 ) C o n t ro l a c c e le r o m e te r s r e l o c a t e d from s k i n t o c o l d p l a t e s .

( 2) T e l e v i s i o n a n t e nn a s , c o n t r o l u n i t s , e x c i t e r s a nd r e l a t e d

equipment added.



d. Nose Cone:

(1 ) Apol lo spac ecr af t rep lace d by a doub le ang le aerodynamic

e n c l o s u r e b o l t e d t o I U ( n ot s e p a r a t e d ) , a nd h ou si ng t h e MSC s u b c r i t i c a l

cryogenic (LN2) experiment.

5 . M i s s i o n P r o f i l e :

( a) Launch Phase:

The AS-203 v e h i c l e w i l l be lau nche d from Launch Complex 37B a t

Cape Kennedy on a 90' E of N l aun ch az im u th and ro l l e d t o a 72' f l i g h t az im u th .

S t ag i n g o ccu r s . 8 seconds a f t e r S-IB outboa rd engine cu to ff . The S-IVB st ag e

i s i g n i t e d ap p ro xi m a t el y 2 seco nd s a f t e r S-IB o u t b oa rd en g i n e cu t o f f a t 1 4 3

seconds . Approx imately 12 seconds a f t e r S-IVB i ng i t io n , a c t iv e adap t ive

g u i d an ce i s i n i t i a t e d , and t h e v e h i c l e i s g ui de d i n t o a 100 n a u t i c a l m i l e

c i r c u l a r o r b i t b y t h e I t e r a t i v e Gu id an ce Mode (IGM). Due t o th e sh or t burn

tim e of t h e S-IVB St ag e, t h e LH2 ta nk w i l l be abou t 50% f u l l a t S-IVB cu to ff

(436 sec) .

(b ) Or b i t a l Phase :

The o r b i t a l p ha se f o r t h i s m is s io n i s d e f i n ed i n two p a r t s :

(1 ) The ac t i ve veh ic le o r b i ta l phase , which occurs f rom S-IVB

cut o ff th rough the LH2 exper imen t and o r b i t a l checkout t e s t s (approx imate ly

6 h o ur s a f t e r l i f t - o f f ) . D uring t h i s p ha se , t h e s i mu la t ed e ng in e r e s t a r t

c a p a b i l i t y w i l l b e e v a l u a t e d , behav io r o f l i qu id hydrogen w i l l be observed ,

and t h e S-IVB/IU s y s tem s ' s t a t e o f r ead i n es s and ab i l i t y t o p e rform wi t h i n

d e s ig n t o l e r a n c e s w h i l e i n a n o r b i t a l en vi ro nm en t w i l l b e ev a l u a t ed .

(2 ) The i n a c t i v e v eh i c l e o r b i t a l p h as e whi ch co v e r s t h e rem a in i ng

v e h i c l e o r b i t a l l i f e t i m e from t h e c e ss a ti o n of a l l o r b i t a l t e s t s t o t h e t im e

o f r e e n t r y .

(c ) Recovery Phase:

Two camera ca pul es ej e ct e d from th e S-IB st ag e w i l l be recovered .

No recovery of t h e or bi te d hardware i s a n t i c i p a t e d .



DISTRIBUTION

D I R D r . von Braun

DIR-T D r . Rees

M r . Neubert

I - D I R Gen. O'Connor

D r . Mrazek

D r .Far ish (50)

I-IB-MGR M r . James

Col . Te i r

I - IB-B M r . Vreuls (2)

I- IB-G M r . Dunlap (3)

I-IB-T M r . Fikes (3)

I-IB-S-IB M r . Thompson (3)

I - IB -U M r . Simmons (3)

I -K M r . Montgomery (10)

I-E-A M r s . Watson (25)

I-MO-MGR D r . Speer (10)

I-KO- F M r . Casey (10)

I-MICH-D M r . Quinton (25)

R-DIR M r . Weidner (2)R-OM M r . Fel lows (5 )

R-TO M r . Richard

R-RP-DIR D r . S u h l i n g e r

R-AERO-P M r . Teague (60)

R-P&VE E (A ll Su pe rv is or s)

R-ASTR E (A ll S up er vi so rs )

R-COMP-RP M r . Cochran (6)

R-ME-DIR M r . Kuers (10)

R-QUAL- J M r . Klauss (10)

R-TEST-S M r . D r i s c o l l ( 5 )

PA M r . Jones

KSC M r . Williams (250)

MSFCIDAC throughR- ASTR- BV/DAC M r . French (20)

DAC/H M r . P e te r son ( 5 )

IBM-H M r . Mart in (20)

IBM-H M r . Robin (10)

CCSD/M M r . Jue ng l ing ( 5 )

Add i t ion a l copi es of t h i s repo r t may be obta ined f rom th e fo l lowing

pe r sonne l :

R- AERO-P R. Teague, 876-4443 Bldg 42001408

R-ASTR- S E. Noel, 876-1860 Bldg 4487lAA211

R-P&VE-VA 0. E. Moon, 876-1277 Bldg 4610/1091



Intentionally Left Blank



F i g u r e

LIST OF FIGURES

T i t l e P a g e

GENERAL

AS-203 Spa ce V eh ic le . . . . . . . . . . . . . . . . . . . 8

Launch Compl ex- 37 . . . . . . . . . . . . . . . . . . . 9

. . . . . . . .C-37B I n t e g r a t e d Launch ESE Blo ck Diagram 10. . . . .C-37B Pr op el la nt and Pr es su r i za ti on Subsystems 11

LC-37 (Pad B) Co nf ig ur at io n . . . . . . . . . . . . . . . 12

Launch Countdown . . . . . . . . . . . . . . . . . . . . . 1 3

SPACE/LAUNCH VEHICLE

Se cu re Range S a f e ty Command System . . . . . . . . . . . . 15

Emergency Detection System (EDs) . . . . . . . . . . . . * 7

S-IB Sta ge Fl ig ht Sequencing . . . . . . . . . . . . . . . 18

. . . . . . . . . . . . . .-IVB S t a g e F l i g h t Sequencing 19

T r a j e c t o r y I n f o rm a t i o n . . . . . . . . . . . . . . . . . . 20

Guidance and Control System Block Diagram . . . . . . . . 23

Guidance and Control System Information. . . . . . . . .

24

Vehic le Contro l Sys tem Informat ion . . . . . . . . a . e . 25

. . . . . . . . . .ehicle Tracking and Television Systems 27

Example of O rb it a l S ta t i on Coverage . . . . . . . . . . . 29

Space Veh icle Weight vs Fl ig ht Time . . . . . . . . . . . 3 1

S-IB STAGE

S-IB Stag e Con figu rati on . . . . . . . . . . . . . . . . . 33

H - I Operational Sequence . . . . . . . . . . . . . . . . . 34

H - I Engine System . . . . . . . . . . . . . . . . . . . . 35

S-IB Stag e Pr op el la nt System . . . . . . . . . . . . . . . 37

S-IB Stag e Thrus t Vector Cont rol System . . . . . . . . . 39



Figure

LIST OF FIGURES

Title Page

S-IB STAGE (Continued)

S-IB Stage Measuring System . . . . . . . . . . . . . . . 40

S-IB Stage Telemetry System . . . . . . . . . . . . . . . 41

S-IB Stage Electrical Power and Distribution System . . . 42

S-IVB STAGE

S-IVB Stage Configuration . . . . . . . . . . . . . . . . 45

J-2Engine System . . . . . . . . . . . . . . . . . . . . 47

S-IVB Stage Propellant System . . . . . . . . . . . . . . 49

S-IVB Stage Propellant Utilization System . . . . . . . . 50

S-IVB Stage Thrust Vector Control System . . . . . . . . . 53

Auxiliary Propulsion System . . . . . . . . . . . . . 55

S-IVB Stage Measuring System . . . . . . . . . . . . . 56

S-IVB Stage Telemetry System . . . . . . . . . . . . . . . 57

S-IVB Stage Electrical Power and Distribution System 58

INSTRUMENT UNIT

Instrument Unit Configuration . . 61

Instrument Unit Measuring System . - . . . . . 62

Instrument Unit Telemetry System . . . 63

Instrument Unit Electrical Power and Distribution System . 64

IU/S-IVB Environmental Control System . . . . 67

NOSE CONE

Nose Cone Configuration . . . * 68



Nose C o n e (MSFC)

I n s t r um e n t Unit (MSFC/IBM)

S - V B S+age (DAC)

Overa \

S- 18 S taqe (cc s0)

AS-203 Space Vehicle



Fiaure 2 Launch Complex 37=



Launch Control Ce,nter ( LCC) ! Automatic Ground Control Station (AGCS)

(Blockhouse)

- - 7 CoaxialI Cab le

Operator ControlC

Oisplay' Stations

Launch Vehicle

Director

Launch Direc tor

Test Conductor

Supervisors

System

Engineering

Instrument Unit

- S-IVB Stage

* 5-16 5taqe

Meeh. GSE

Measurinq 4 RFStablization C

Guidance

* Propellant

Loading

Figure 3



MSE FACILITY

PROPELLANT 6 PRESSURIZATION SUBSYSTEMS

Pneumatic ControlDistributor

&To RP-1 , LOX 6LH2 Control

Conso lesToEnvironmental

Control System

. J

GN2I

GaseousHelium D

~ H 2 2 J

Subsystem

Storaqe6,000 PSlG

r

HeStoraqe

Gaseous Hydroqen GH2 I To S-IVB StaqeI-MSE .. Mechanical Support

Equipment-

D. I

From PortableRecharqer

Fiqure 4

GN2 50 PSIG I D

- - - - - - - - - - - - - - - - - - - - - - - - IFrom Supply

IValve Panels

Storaqe

6,000 PSlGb

D Pneumatic Servicinq

I ControlTrailers D is f r ibutor

6,000 PSlG

D To Pneumatic



Swinq A vm Wo.45evvic.s ibe S- IVBforwrod skirt and the

t n s t r u ~ r n funit. ( ~ O e rI,

Sevvices the S - IVB

aft skirt,tanks and JQenqrna,(~Ckr isconnee+~ w i ~ g rI OCYW I ~C )



I 1111 R c A i i o A Sea. c h e c k s I I

Manrcal Sequence

I Coqnt+in?e in Hours

-1 5 - 1 2 -9 -6 - 3 -r/2f 1 1 I

A B q i I t - i~ h0td3 A4 5 hrs. I Ii r.

I L V Power on

I I

I I

Aq+on\a+ i c S e q u e h c e

C o q n t t i m e i r ( Seconds

- 3 0

RF,TM, Prop. , G ~ C o &r n a * d C h e ks

1111Power Tvansfer Tests- ropellqnf Transfer Chcc ks

0 C l o s e I U Doov I -I-18 artial Lox Loadircj y Leak c A e c bI

If Mqtfrrnct ior\I

Occqvs: -- - Hold or recycle to T- 15q i n - p Recycle .

I4

s c r u b

LV B a t + e r y Inst4 latior\

IG $ C Sy s t em or(

I 1I P r p p . r a l i o n ~ camp./ O K T O Launch A

IP r e s s y r i z e Tqnks

N o + e : 5-16 u e l l o a d i n g , I P o k e r T r a h s f ev

S - L V R A P S l o a d i q 9 , h Gqidance Ref .

Rclea sea h d LV ~ r d ; o a n c e q s t a l la + or\

are c o r \ d Y c f e d p r i o r t o

Jqr ioch d a y .C o b m i + AI L i f t o f f 4

P q v g e av\d F l q s h PqdI I Area

-4 6 3 s -28s -3s 0

I I I



LAUNCH VEHICLE SECURE RANGE SAFETY COMMAND SYSTEMS

The se cu re ran ge s a f e t y command systems on th e S-IB and S- IVB s t a g e s p r o v i d e

a communica tions l in k t o t r a nsm i t commands from ground s t a t i on s t o th e veh ic le

d u r in g po were d f l i g h t , a nd a p o s i t i v e means o f t e r min a t in g t h e f l i g h t of a n

e r r a t i c v e h i c l e by i n i t i a t i n g emergency e n gi n e c u t o f f a n d, i f n e c e s s a r y , p r o p e l l a n t

d i s p e r s i o n .

Each powered s t a ge con ta i ns two UHF ra di o rece iv er s . Both command re ce iv er s

on each of t h e two s t ag es respond t o th e same command s ig n a l , each providi ng a

b ac ku p s y st e m f o r t h e o th e r .

The sa fe ty and arming dev ice loc a te d on each s ta ge i s a rmed by a s ig na l

from t h e b lo ck ho us e b e f o r e v e h i c l e i g n i t i o n . F ol lo wi ng o r b i t a l i n s e r t i o n t h e

S-IVB ran ge sa f e t y system i s "saf ed" by a command from Range Sa fe ty C on tr ol t o

p r e c lu d e a c c i d e n t a l d e s t r u c t .



Fiqure 7



ENERGENCY DETECTION SYSTEM

Mi ss i o n AS-203 d o es n o t c a r r y a n Apo l l o Sp a c e c r a f t a n d t h e r e f o r e d o es n o t

have a comple te EDS. The EDS cannot in i t i a t e an au to ab or t . A l l EDS a b o r t

p a r a m e t e r s a re t e l e m e t e r e d f o r m o n i t o r i n g by t h e Lau nch Di r e c t o r .

La un ch V e h i c l e r a t e a b o r t l i m i t s a r e :

P i t c h and Yaw 5.0 '0.6 d e g l s e c .

R o l l 20.0 '0 .5 de gls ec .

An o v e r r a t e c o n d i t i o n mu st b e i n d i c a t e d by two o f t h e t h r e e g y r o s i n an y

o ne a x i s t o a c t i v a t e t h e a b o r t b us . A l l EDS r a t e s a re f i l t e r e d t o e l i mi n at e

lo w f r eq u e n c y n o i s e d u e t o v i b r a t i o n a n d a c o u s t i c s .

Two o f t h e t h r e e t h r u s t OK swi tche s on two B-1 eng ines must in d i ca te l o s s

o f t h r u s t b e f o r e t h e a b o r t b us i s a c t i v a t e d .

There i s a red und ant Q-Ball on th e Nose Cone.



On A S -203 he EDS CANNOT

activate an a b o r t ( f l o w n in

"open loop" configuration )

Instrum.ent Unit

Excessive EDS Di st r i bu torAnqulat- Rates

from cont ro lsignal p r o c e s s o r

FromSwitch

Se lec t or 1 line/

Rate Parameters are:

t 5 % 2.6'in P # Yf 20% t . 5 " i n Roll

I-EngineCutoff

Adapter

/ vehicleI reference

f a i l

H - IEnqine

C . 0 .

Figure 6

Switch Closesat - 00 PS IA ,

Opens at 425PSIA

ea located on

t h e s i n g l e J-2e n q i n e

v ....................... 1, , , , / , / '

To5-16 TM

Switch Closesat - 800 PSIA,opens at - 750

PSIA3 ea. l o c a t e d o n each ofthe e i q h t H -1 enqines

Emerqency DetectionS y s t e m ( E D S )

>



ILIFTOFF 1

I I IA Disconnect IU Umbilical II l o so c

I III>t Enqine Out" capability

II I I

I IFuel Tank ress. valves openPI I I

- 1 3 4 . 8 , I

A prop. level sensor armingI I

.u136.6 I

A Any prop. level sensor actuates (predic ted)I-- 139. e

III A Inboard Enqine C u t o f f

I ~ f 4 1 . 1

II

A O p e n S-IVB LO X 6 LH2 prevalvesI I-141.3,

I a n a b k Lor depletion c u t o f f

I - 4f4. 8I

III

Note:

Approx. t imes

I

shown are in secondsI

measured f r o m II U umbilicaldisconnect I

I

I

A Outbo a rd Enqine Cutof f

144 -147

Ullaqe rocket f i r inq

143.6I Se pa ra t ion Command

1 1 - 2 1Ret rorocke t f i r i n q

I I A S - I 6 Separa t ion

I II II II I

+ 1 2 - 2 3 DS t a r t o f S t a r t of Start of

Time B a s e 1 Time Base 2 Time B a s e 3

Time Base Divisions

5-10StaqeF l i q h t Sequencing



- 143.7

S- IB S e p a r a t i o n (Physical)I

I I~ 4 4 3 . 8 I

Switch control siqnals to S - I V B staqe ( Act i va te APS t o c o n t r o l r o l l 4 enables1 1145 I J -2 ertqine qimball inq)I

* l A J-2 enqine start command- 46.5I

IA J -2 rnainstacje (open main oxidizer v a l v e )

- 1 56IIA Jettison ullaqe rocket motors i- 64.7

M o v i e Camera eject ionI

-420.5 II

Arm poini level sensors (back-up enqine c. 0 . )-435.5A S- IVB Guidance Cutoff

I -436

Note:

Approx. t imesShown are in seconds

measured from I U

umbi l ica l disconnect

I A Secure 5-1V6 Staqe and Switch

to orbital mode

1 - 4 3 6

I Begin LH1 e x p e r i m e n t operations

IIIIIII

*This t ime from separation Iallows fo r a minimum o f40 f t . c learance b e t w e e n t h e

IS-1VB enqine bell and the 1Separated a f t in+erstaqe I

~ t a i tCTime Base 4

Time Base Divisions

Figure 10S - I V B Staqe

Fl qht Sequenc inq



I E C O -Inboard Engine Cutof f

OECO -_Out board Enqine cu+oc$

I G M - t e r a t i v e Guidance Mode

9 - S e c o n d s From L i ~ + o f f

I

Apogee 184 km

Pe r gee ( 8 2 m

Inclination 31.96"L i f e t im e 3 days

T i l t Anqle

67./"Ti Lt

. - 4 3 5 9

- V s 7785"Is

S t a r t IGM - 5 7 5\

Orbits\ In s e r t i o n

- 6 5 k m 10s f t er cuto f f

5 e p " 1 4 5 . G ~\

- V s 7773 M/s

OECO- 1 4Z . BB , V s 3 0 5 9 m/s

I E CO - 139 . B s \w.067 O/s Confinuous

q man. \Orbital tilt

-- 69s \

\ - 574s-- - 783 krn

re+ercnce

r e l e a s e 5 5

b e { o * e I l f t o ~ f

LAUNCH DATA

LaclncL Comp l ex - 3 7 Pad 0

l a u n c h A3imu+L- 90°Eo rN

* Fli,L& A3imuCh- 7 Z 0&o f N

S - I f 3I E C O - - 134 . 8s ; ropallnnt level

Sensors a r m e d .

O E C O - - L e v e l sensin +4.5s enable Loxdepletion c 4 d f .(we1 deplelio*, cutot4 enabled I ec. later)



GUIDANCE AND CONTROL SYSTEM

F u n c t io n a n d D e s c t i p t i o n

The G&C s y st em p r o vi d es t h e s e b a s i c f u n c t i o n s d u ri n g f l i g h t : ( 1) s t a b l e

p o s i t i o n i n g o f t h e v e h i c l e t o t h e command p o s i t i o n w i t h a minimum amount of

s l o sh i n g a nd b e n d i n g, ( 2 ) a f i r s t s ta g e t i l t program which g i ve s nea r z e r o

l i f t t r a j e c t o r y t h r o ug h t h e at mo s ph e re an d p r od u ce s r e a s o n a b l e en d c o n d i t i o n sa t Outboard Engine Cutof f (OECO), (3 ) red uc t i on o f wind load s dur in g th e h ig h

d y n a m i c p r e s su r e r e g i o n , (4) s t e e r i n g commands du ri ng S-IVB b urn which gu id e

t h e v e h i c l e t o a p re d et er mi ne d s e t o f e n d c o n d i t i o n s wh i l e m a i n t a i n i n g a

m i n i m u m p r o p e l l a n t t r a j e c t o r y , (5) f i n a l c u t o f f an d s e qu en ci ng s i g n a l s , ( 6)

a t t i t u d e s i g n a l s f o r t h e s e n s i n g, c om pu ti ng , a nd a c t u a t i o n e le m en ts o f t h e

G&C sys tem. A b l o c k d i a g r am of t h e h a rd wa re u se d t o i mp le me nt t h e se f u n c t i o n s

i s shown i n F ig ure 12 .

The s t a b i l i z e d p la t f o r m (ST-124M) i s a t h r e e g i m ba l c o n f i g u r a t i o n w i t h

g a s b e a r i n g g y r o s a nd a c c e l e r o m e t e r s m ou nt ed on t h e s t a b l e e le m e n t . Ve h i c l e

a c c e l e r a t i o n s a nd r o t a t i o n s a r e s e ns ed r e l a t i v e t o t h i s s t a b l e e le me nt .

G im bal a n g l e s a r e m ea su re d by r e d u n da n t r e s o l v e r s a nd i n e r t i a l v e l o c i t y i s

o b t a i n e d f r om a c c e l er o m e t e r he ad r o t a t i o n i n t h e f or m o f e n co d er o u t p u t s

( a l s o r e d u n d a n t ).

The l aunch v eh ic l e d a t a ad ap te r (LVDA) i s a n i n p u t -o u t p u t d e v i c e f o r

th e LVDC. These two components a r e d i g i t a l dev ices which op e r a te i n con-

j u c t i o n t o c a r r y o u t , t h e f l i g h t p rog ram . T h is pro gram pe rf or m s t h e f o ll o wi n g

fu nc t ion s : (1 ) Proce sses th e in pu t s f rom th e ST-124M, (2 ) pe r fo rms nav ig a t i on

c a l c u l a t i o n s , (3 ) p ro vi de s f i r s t s t ag e t i l t program, (See F igure 14 ) , (4 )

c a l c u l a t e s IGM steer ing commands, (5) r e s o l v e s g i m b a l a n g l e s a n d s t e e r i n g

commands i n t o t h e v e h i c l e sy s t e m f o r a t t i t u d e e r r o r commands, (6) i s s u e s c ut -

o f f a nd se q ue n ci n g s i g n a l s .

The c o n t r o l a c c e l e r o m e t e r s s u p p l y s i g n a l s t o t h e c o n t r o l co mp ute r d u r i n g

S-IB b u r n w hi ch a r e p r o p o r t i o n a l t o t h e ae ro dy na mi c l i f t f o r c e s a c t i n g o n t h e

ve h i c l e . They a r e sp r ing-mass dev ices which a r e mounted on I U c o l d p l a t e s .

The Cont ro l /EDS r a t e gyro package co n ta ins 9 g y ro s ( t r i p l e x r e du n da nt

i n 3 a x e s ) . T h e i r o u t p u t s g o t o t h e c o n t r o l s i g n a l p r o c e s s o r (CSP) wh er e

t h e y are v o t e d a n d s e n t t o t h e c o n t r o l c om pu te r f o r dam ping a n g u l a r mo t io n .

T he se o u t p u t s a r e a l s o p ro c e s s ed i n t h e CSP f o r u s e a s a n a b o r t p a r a m e te r .

The co n t r o l computer sen ds commands t o th e S-IB and S-IVB en gi ne

a c t u a t o r s a n d t o t h e c o n t r o l r e l a y p a ck ag e b a s ed o n s i g n a l s f r om t h e LVDA,

c o n t r o l a cc e l e ro m e t e rs , a nd r a t e g y r os . T he se s i g n a l s a r e f i l t e r e d a nd

sc a l e d ( See F i g u r e 1 3 ) , t h e n summed i n m a g n e t ic a m p l i f i e r s . T h i s c om pu te r

p r o v i d e s redundan t op e r a t i on dur i ng S-IVB burn and coas t on ly .

The co n t ro l r e l a y packages a ccep t computer commands and re l ay th es e

commands t o o p e r a t e p r o p e l l a n t v a l v e s i n t h e Au x i l i a r y P r o p u l s i o n Sys te m ( APS).

A l l r e l a y s a n d v a l v e s a r e r e du n d an t . The APS ha s 6 n o zz l es ( t h r e e i n e ac h

module ) which ope ra t e spon taneous ly when f u e l and ox id iz e r a r e mixed .



The 8 hyd r a u l i c a c tu a to r s o f th e S-IB s t a ge a r e use d t o gimbal th e ou t-

boar d e ng ine s a nd p r ov ide c on t r o l i n a l l a xe s . The two hydr a u l i c a c tu a to r s

of th e S-IVB s t ag e a r e used t o g imbal the 5-2 engine and provide c on tr o l i n

pitch and yaw axes. These two ac tu at or s use mechanical feedback.

The swi tch s e l e ct o rs a r e used t o r e l ay di s cr et e commands from th e LVDA

t o o t h e r l o c a t i o n s i n t h e v e h i c l e . The cu t o f f s i g n a l and ti m e b as ed e v e n ts

a r e i s s u e d th ro ug h t h e s w i t c h s e l e c t o r s .

Opera t ion

The vehic le i s e r e c te d on the l a unc h pa d wi th pos i t ion I a t a 90' E of

N azimuth. The s ta bi l -ze d p la t form i s al ig ne d t o 72' azimuth duri ng countdown

a nd h e l d i n a n e a r t h f i x e d p o s i t i o n , p e rp e n d ic u l ar t o t h e g r a v i t y v e c t o r . A

r o l l p r e s e t t i n g o f 1 8' i s u se d t o e l i m i n a t e t h e a t t i t u d e e r r o r wh ich would

r e su l t from t h i s d i f f e r e n c e i n az im uth. The LVDC ope r a te s i n g round r ou t i ne s

p r i o r t o GRR and a t t i t u d e e r r o r s i g n a l s a r e s e t t o n u l l . A t t h e i n s t a n t o f

GRR, th e p la t for m becomes space f i xe d t o es ta bl is h th e guidance coordian te

system and t h e LVDC en te rs t h e f l i g h t mode. I n t h i s mode accel erom eter

p r oc e ss ing , s t e e r i ng , na v iga t ion , t e l e m e t r y , and o the r f unc t ions a r e per fo rm ed

e x ac t ly a s th ey a r e a f t e r l i f t o f f .

L i f t o f f s i g n a l (IU u m b i li c a l d is c on n ec t ) i n i t i a t e s t i m e b a s e 1. Ten

s ec on ds l a t e r , t h e p i t c h program s t a r t s a nd t h e i n i t i a l r o l l p r e s e t t i n g i s

r e s e t t o ze r o . The v e h i c l e r o l l s i n t o a li gn me nt w i t h t h e pl a t fo r m a t

1°/second. There i s no ac ti ve pat h guidance during S-IB burn. Control i s

main tain ed by gim ball ing t h e fo ur ou tboard engines on command from th e co nt ro l

c om pu te r. S eq ue nc in g s i g n a l s a r e i s s u e d t o t h e v ar i o u s s w i tc h s e l e c t o r s t o

perform t ime dependent func tio ns .

P r o p e l l a n t l e v e l se n s in g s i g n a l an d OECO a r e i n t e r r u p t s t o t h e LVDC

w hich s t a r t t i m e b a s e s 2 an d 3 . Pat h guida nce (IGM) begi ns about 14 seconds

a f t e r OECO. S-IVB en gi ne cu t of f i s i s s u e d b as ed o n t o t a l s p ac e f i x e d v e l o c i t y

a nd s t a r t s t im e b a s e 4.

The APS i s used f o r c on t r o l i n a l l axe s du r ing S-IVB c oa s t . A p i t c h

o v e r maneuver s t a r t s a t 5 seconds af t e r S-IVB engine cuto ff and continu es

a t a b ou t . 0 67 " /s f o r t h e d u r a t i o n of t h e mi s si o n.

The d i g i t a l command sys tem car r i ed i n t he I U i s a ph as e s h i f t

keyed/frequency modulated (PSKIFM) syste m. The LVDC w i l l b e programmed t o

r e c e i v e two typ es of commands from t h e I U Command Decoder: Mode Commands

an d Data Commands. Mode Commands w i l l be decoded t o de te rmine wha t r ou t i ne

o r sub - r ou t ine i s t o be exec ut ed by t h e LVDC. Da ta Commands w i l l be used t o

s a t i s f y th e da ta requirements of t he commanded rou t in e . The pr in c i pa l

f u n c t i o n s of t h e I U Command System are : t o i n i t i a t e a l t e r n a t e LH2 expe ri-

ment sequences, t o update t he t im e sequence, t o command si ng le sw itch

s e l e c t o r f u n c t i o n s , t o c o n t r o l t h e TV s ys te ms , a nd t o i n i t i a t e o t h e r s ys tem

f unc t ions on a t e s t ba s i s ( na v iga t ion upda te , sys te m s c he ckou t ).



I Q - Ball

~ansducer TO I" ED5 di&ibu$oyNOSE CONE

INSTRUMENT UNITIU Command

5y54em-T- 12464 3' Accel vk

A c c e l . Siqnal-

stabi l ized Condit ioncr

P l a t f o r m A d a p t e r on-OFF ,C

Att i tude Signals + p r y , pt

- R a n q e t l Om / s l

Active f r o m ~ o n r r o l - 5 9

30 t o 110 SeC.Control

C o mp u t e r

Yaw(Fi l ters,

scales, sums Discrete siqnals

and d i s t . t o I U s y s t e msControl/EDS Control i n p u t

Ranqe -+ 10 "/seeSelector

- Active prior t ol i f t o f f

Provides roll comtrol

duri nq 5- V8 poweredFliqht and p i tch , yaw ,

and rol l dur inq coastc o mma n d

To pitch a n d y aw

control a c t u a t o r s i 7O

5-16 STAGETo control a c t u a t o r s

for enqines 1, 2 . 3 & 4

+_8' wivel angle

G o c a n t an91e E l e c t r i c a l f e e d b a d ;

Inboard en91nes

3'can t anqle Discrete siqnatsto S - I B S y s I e m S

Fi ure I2---



Functional Diaqram o f G $ C Systems

SEWS1NG ELEMENTSCOMPUT l NG ELEMENTSI 4

LVDA/LVDC--Naviqation CaLouWions

-5cnsimq .o f angular Calculatton o$ stoetingorientatwon and velocity commands baseda nrelat ive tb tk e inert ia l -time or ISM.

eoirdinate System 17 ~ a l c a i a t i o n f Y'.

Genera&kon ofseouencino sionats I ACTUATION ELEMENTS

4Control Accel. . 5-18

Sensinq o f Y *? ' 4 4 ? rs

Control Computer

kt% * , gom -Calcula*ion o f con+roP%LF<ueactuator and APScommands to

SA-203 CONTROL SYSTEM DESIGN OBJECTIVES

The d e s i g n o b j e c t i v e s u se d i n d e te r m i n in g t h e c o n t r o l g a i n s a n d s h a pi n g

ne tworks du r ing bo t h S -IB and S -IVS S tage burn a r e t o p rov ide adequa t e ve h i c l e

r e s p on s e and s t a b i l i t y m a rg i ns t hr o ug h ou t f l i g h t . P a s s i v e sh a pi n g n et wo rk s

a r e us ed i n t h e a t t i t u d e e r r o r and a t t i t u d e r a t e c ha n ne l s. A c t i ve s ha pi ng i s

u s ed i n t h e a c c e l e r o m e t e r c h a n n e l s . The n e tw o r ks a r e tu n e d t o p r o v i d e m i n i-

mum p h a se l a g a t s l o s h f r e q u e n c i e s c o n s i s t e n t w i t h g a i n s t a b i l i z i n g a l l bend -

i n g modes e x c e p t t h e f i r s t b en d in g mode d u r i n g S-IB S t a g e b u r n . T he f i r s t

ben din g mode dur in g S-IB Stag e burn i s p ha se s t a b i l i z e d .

Typical Shapinq Network Characteristics - S - 1 0 Burn

, Shap;nq network

b e n d i q modes

Pitch and yaw attitude error (9 , y

Shaping network

Note: S-10 - 4 ~nd S-1VB 7p , y, R f i l te rs

h av e similar c ha r a c te r i s t i c s ;

also t ru e fo r P p , y , R f i l ters

Fiqure 13

yp , Shapinq neiwork

System Information



Control Sy s t e m Gain Factorsa0 = deg / d e q ( Attitude rate)a1 =deq/deq /s (At t i tude error)

92 deq /m/s2 (Acceleration )

I - - - - - - - - - - - -1I path guidance active IL - - - - - - - - - - - - I

I I

L.0 . 80s SEP, S-IVB C.O.

- - - - - - - - - - - - - - - - - - - -control rate 9yros active

I I

Vehicle Pitch Prooram

I

5.0--.I)

a l

1.0

-,*

w

Orbit +

Begin continuous orbitalpltch proqram at .0670/s 5 See.

I , af+er S-IVB cutoff

I I I -157s I

-

a0 # at = 0.67

5.0-,,,,,,-,--al1.0 a

1 S-IVB *

-Axis Term

60s 1 1205II 6.0 I

1 End tilt - tart. A/-

Roll-

Guidancereference

release-- 5 s

before l i f t o f f

SEP.-

5-18 -2

Figure 14

S- IVB

30 5 f 1 0 S

I 0.30 ' 10

S - I V B C . O .

0.252!,,,,,,,

-- 03.5'

ORBIT-

0.20

Vehicle Co n t ro l Sy s t e mInformation

I 1 L2'E-



VEHICLE TRACKING SYSTEMS

1. Azusa and C-Band Rad ar Sys tem s.

The A zu sa g ro un d s t a t i o n d e t e rm i n e s s u c c e s s i v e t r a j e c t o r y p o s i t i o n s

o f t h e ve h i c l e by c on t i nuous pha s e com pa ri son be tw e en t h e s i g na l s t r a ns m i t t e d

t o t h e r e c e i v e r f rom t h e onboard tra nsp on de r. The C-Band Radar Transp onder

o nb oa rd t h e v e h i c l e p r o v i d e s (up on i n t e r r o g a t i o n f r om t h e g ro un d) a s i n g l e

p u l s e r e p l y t o g ro un d r a d a r s ys te m. T h i s s i g n a l i s f e d t o t he g r ound c om put ercomplex t o o b t a i n p o s i t i o n , v e l o c i t y , and a c c e l e r a t i o n i n f o rm a t i on . T r a j e c t o r y

da t a f r om t h e l a unc h ve h i c l e A z usa a nd C-Band a r e p r e s e n t e d on p l o t t i ng boa r ds

f o r t h e r a ng e s a f e t y o f f i c e r t o u se i n d et er mi ni ng " r e a l t im e" v e h i c l e t r a j e c t o r y

pa r a m e t e r s . I n a dd i t i on , t h e l a unc h ve h i c l e A zusa a nd C-Band a r e u s e d f o r t h e

p o s t f l i g h t d e te r m i n at i o n of t h e v e h i c l e t r a d e c t o r y .

2 . ODOP System

T h e v e h i c l e ' s ODOP t r a ns po nde r t r a ns m i t s a c on t i nuous wave s i g na l

( a t 70 mc above th e rece iv ed f r equenc y) t o t h e gro un d r e c ei v i n g s t a t i o n s

w he re t h e d o p p le r s h i f t (d ue t o t h e r a d i a l v e l o c i t y of t h e v e h i c le ) i s used

t o p r o v id e t r a j e c t o r y d a t a f o r t h e p os t f l i g h t e v a l u a t io n of v e h i c l e p er -

formance.



Itore cone NO-

-

wed to fu(Ct\I mn e 4 e t ytrdc kinq reqoir%mentr.

s-rs r u q e

~ r ~n 5m i i - - i ow 3 - 2 whft'atceivc --so60 mc

A ? O S

<yc.tem

(@setand

L

mmpadw



STATION COVERAGE SUMMARY

RANGE I U

STATION TRACKING SAFETY TV- TM- COMMAND

1. Cape Kennedy Area X X X

2. A t l a n t i c F i e l d X

3 . Eleu the ra X

4 . Grand Bahama X

5. Bermuda X

6 . In s e r t ion Sh ip

7. Antigua

8. Canary Is la nd

9 . Ascension

10. Tan ana rive , Madagascar

11. Carnarvon, Aust ra l ia X X

12. Canton Is la nd

13. Hawaii X

1 4 . Point Argue110 X

15 . Guaymas, Mexico

16. White SandsX

17. Corpus C hr is t i X

18 . Houston (MCC-H) D ir ec t command c a p a b i l i t y t h r u

f a c i l i t i e s a t KSC, Corpus Ch r i s t i

and Bermuda.



ovbitol Path tlevcltion mqle

kTV 5vstem on

4€-TV L ~ ~ W T I n (~UIIpower)

--Im min.5ince i im r in minutes~ a n a n a v ~ v e ( ~ e l e v . )

?#

LH, Nor.prop.vent opcu I

0 I 'L 3 4 Z 6

F iqure 16

7

Example of O r b i S a l

S t a t i o n C ~ u e r a q ed b

1- Imin.

II I I I I I II I I I I

uw L ~ G H T ~N Y4 y a w

1 LOX ul~.mrurt omt.uohro open 1

J4min



GROUND TRACKING

O p t i c a l

1. CZR Cameras and Theodolites -- Pr i m ar i l y us ed up t o - 500 meters

a l t i t u d e . T a r ge t s f o r t r a c k in g

a r e v e h i c l e p a i n t p a t t e r n s .

2. Long Range Cameras -- To t r a c k v e h i c l e du r in g f l i g h t u n t i l

lo ss o f v iew.

1. Skin Track ing -- The S-IB s t a g e a f t e r s ep a r a t i o n w i l l b e s k i n

t r ack ed b y r ad a r s l o ca t e d a t t h e Cape. The

S-IVB/IU w i l l b e s k i n t r a ck e d d u r i ng t h e

rema i nd e r o f t h e t r a j ec t o ry by Cape and

downrange radars.

2 . GLOTRAC -- Downrange stations w i l l use th e Azusa t ransponder

a f t e r - 140 seconds.



SPACE VEHICLE WEIGHT VS. FLIGHT TIME

VehicleWeisht(Pounds)

The total flight time from liftoff to orbital insertion of the S-IVB

stage is cr, 7.3 minutes. Propellant consumption during S-IB stage flight

( - 144 seconds) is4 885,500 pounds and during S-IVB stage flight at'90%

thrust ( - 298.4 seconds) is -136,000 pounds.

In case one engine of the S-IB Stage malfunctions and is cut offduring flight, the remaining engine will consume the propellant intended

for the "dead" engine. Burning time of the stage would increase, and the

overall vehicle performance loss would be minimized.

Vehicle weight Data (Approximate) Pounds

Total at S-IB ignition

Total at liftoffTotal S-IB O.E.C.0

Total at S-N B ignition

Total at S-IVB cutoff

i,201,000 Ibs. ( ~ o t a lVehicle @ Iqnition)1,187,000 Ibs . (Total Vehicle.@Liftoff) (0 see.)

S-I6 Propellant Consumption .~6,200bs/sec.

-

- S-IVB Staqe nitio ion (-f45 sec) (i95,000 lbs.)

-

- S-IVB Propellant Consumption -455 Ibs./see.

-S-IVB Enqine Cu t o f f

- -435 sec. (58,700 lbs)

-

40,0001 AFtev the end of active att i tudecontro l the rate of mass lossis about 12,000 Ibs. per day

Residual LH2 - 49,000 Ibs.

0 7I I I I I I

L i f t o f f 100 300 500

( O see)Time (sec. from lif+off)-

I



S-IB STAGE STRUCTURE

The S-IB s t ag e con s i s t s of fo ur 70-inch d iamete r fu e l cont a in ers mounted

a l te rn a t e l y wi th fo ur 70- inch d iamete r LOX con ta in ers a round a 105-inch d iamete r

LOX c on ta ine r . The c o n t a i n e r s a r e s u p p or t ed a t t h e b a se by a t h r u s t s t r u c t u r e

a ssem bly t o which a r e a f f ixe d t he e ig h t H-1 e ng ines . The s pi d er beam assembly

p r o v i d e s t h e s u p p o r t s t r u c t u r e a t t h e f or w ar d end of t h e c o n t a i n e r s a nd s e r v e s

a s a n a d a p t e r f o r t h e S-IVB i n t e r s t a g e . E i g ht f i n s a r e mounted a t t h e b a s e ofth e S-IB s t a g e t o improve a er odynam ic s t a b i l i t y , p r e - f l i gh t suppor t , a nd ho lddown

of t h e v e h i c l e .

PROPULSION SYSTEM

The f i r s t s t a g e of t h e l a u nc h v e h i c l e i s powered by a c l u s t e r of e ig ht

Rocketdyne H-1 e ng ine s deve lop ing a t o t a l s e a l e ve l th r u s t of 1 ,600,000 pounds.

Four engines a r e mounted outboard and fou r inboard; th e fou r outboard engines

a r e g im baled f o r ve h ic l e c on t r o l . The p r o pe l l a n t s a r e LOX andR P-1 .

EJECTABLE CAMERA CAPSULES

Two e je c t a b le c am er as a r e t o be c a r r i e d onboa rd t he S -IB s t a g e f o r the pu r-pose of viewing S-IBIS-IVB st ag e sep ar at io n and oth er phenomena as so ci at ed wi th

pe rf o rm a nc e of th e ve h ic l e du r ing se pa r a t io n . The camera e je c t io n system co ns is ts

o f a h igh - p r e s su r e s to r a g e sphe r e , two soleno id con tr o l va l ves , two camera e j ec t i on

mechanisms, and th e necessa ry va lv es , tubing , and ass oc i a te d hardware .

The c am er a c a psu le s a r e mounted i n th e s e a l p l a t e a t t he to p o f th e S-IB

s t a g e a n d w i l l be e j ec te d twenty- f ive seconds a f t e r S-IBIS-IVB sep ara t io n . The

c a p s u l e s w i l l f o l lo w a b a l l i s t i c p a th t o a n a l t i t u d e o f a pp ro xi ma te ly 1 4, 00 0

f e e t . A t t h i s p o in t , pa r a c hu te s w i l l b e d e pl oy ed t o d e c e l e r a t e t h e c a p s u l e s.

A f l o a t a t i o n ba g ( ap p ro x im a te l y 20 i n c h es i n d i am e te r w i t h a l t e r n a t e c o l o r e d

p a n e l s of i n t e r n a t i o n a l or an g e an d s i l v e r ) w i l l k eep t h e c a p s u le s a f l o a t a f t e r

impact .

For recovery , th e capsu les a re equipped wi t h SARAH tr an sm it te r s th a t op era te

on a frequency of 242 mc, a nd have a ba t t e r y l i f e o f a ppr ox im a te ly 30 hour s . The

e f f e c t i v e r an g e of t h e t r a n s m i t t e r s i s approximate ly twenty- f ive mi le s . I n

a dd i t i on , a dye m ar ke r i s a l s o r e le a se d t o a i d i n a e r i a l s i g h t in g .



AP S M o d u l e s (2)

I-NBAII Skivtl n s t r . Compwfment F-2

M e a s . racks

Antenna Arrangement

! + r o r o c k t * (4 )

, w s t r . Cornpartmen+

Range Sa fe+4

Talemc+rJ(

Area Above Tanks *r. otion picture c a m

* E B W t i r ing units

70 nch LO%-

and Fuel Tanks.

Measuring racks

D i r f v i butovs

~ e m o k ;,i+a( sub-muI+iphuers

--- -..- . --. .

View L e o k i m j R t t

:cep+

eva s

S y s tern Tunnel (4 )(Elactitcrl Cable TVWC)

W e i q h t :

Dr3 :- 86 ,

Fin 7

L o r Fill 4 Dram

S - 1 0 S t r ge a t S c p a ~ f i o n97,300 Ibr.

F 1 d ~ 2 )

ystem

F i y u r e 18 9-10 Staqe Cowfiquvation



H- 1 ENGINE OPERATION

A s t a r t s i g n a l i g n i t e s t h e s o l i d p r o p el l a nt g as g en e ra t or (SPGG) which

a c ce le ra te s th e LOX and RP-1 pumps. I n c r e a s i n g f u e l p r e s s u r e o pe ns t h e m ain

LOX va lve which, i n t u rn , o pe ns t h e s e qu e nc e v a lv e p e r m i t t i n g f u e l p r e s s u r e

t o r u p t u r e t h e h y p e r go l i c c a r t r i d g e . Pr imary i gn i t io n occ urs when th e RP-1

a nd h y p e r g o l i c f l u id c o n ta c t LOX in th e t h r u s t c h ambe r. The i n j e c t o r f u e l

p r e s s u r e o pe ns t h e ma in RP-1 v a lv e a nd p r o v id e s p r o p e l l a n t f l ow t o t h e l i q u id

p r o p e l l a n t g a s g e n e r a to r (LPGG) w hich s u s t a i n s t u r b in e o p e r a t i o n .

The d i g i t a l co mp ut er i n i t i a t e s i n bo a rd e ng i ne c u t o f f 3 .0 seconds

a f t e r t h e p r o p e l l a n t l e v e l s e n so r a c t u a t i o n . O utb oa rd e n g i ne c u t o f f i s

i n i t i a t e d by e i t h e r t h e t h r u s t OK swi tches , the backup t imer ( from th e

computer) , o r t h e f u e l d e p l e t i o n p ro be s. Bo th c u t o f f s i g n a l s a r e r o u t e d

th r ou g h th e S-IB s t a g e s w i t c h s e l e c t o r . The c u to f f s i g n a l o pe ns t h e

e x p l o s i v e l y a c t u a t e d Conax v a lv e e q u a l i z in g t h e RP-1 p r e s s u r e a t t h e

main LOX v a l v e . The v a l v e c l o s e s t o i n t e r r u p t f u e l f lo w and t e rm i n a t e

e n g i n e o p e r a t i o n .

SPGG I g n i t i o n 1 ISPGG Combust i on 1Main LOX Val ve (Open)

Hypergo l Car t r i dge Ruptures1 15 1 1 I

P r i m a r y I g n i t i o n

Main RP- 1 Valve (Open)

Main I g n i t i o n ( S t a r t )

LPGG O pe ra t io n

Mains tage Thrus t

Conax Valve Actuates

0 1 2 3I sec. s e c . sec.I

I q n i t i o n Lif-toff

Command

- T ime from I qn i t i on

0 f 2I sec . sec .

Cuto f fSiqnal

* T ime from Cu t o f f

H - f Operational



1

R P - I LOX

Pressure System

Gas Generator

LOX TankMixture Ratio

PressurizationLOX: RP-I, 2.D:I

Th rus t Chamber

RP - I Preheat200,000 Ibs Thrust

H - Enqine System



S-IB STAGE PROPELLANT SYSTEM

The S-IB Stage propellant system is composed of five LOX tanks, four

RP-1 tanks, propellant lines, control valves, vents, and pressurization sub-

systems. The sumps of each group of tanks are interconnected to provide

uniform propellant levels and pressures. Loading of LOX and RP-1 tanks is

controlled by ground computers. After the RP-1 has been loaded and just

before the start of LOX loading, ground source GN2 is bubbled through the

RP-1 suction lines to prevent temperature stratification. At the start ofthe automatic sequence the RP-1 tanks are pressurized with ground source

GN2. During S-IB burn, fuel tank pressurization is maintained by GHe

from two 20 cubic foot spheres located above two of the fuel tanks. Ground

source helium is bubbled through the LOX lines and tanks at the start of

the automatic sequence to prevent temperature stratification in the engine

LOX suction lines. Prior to engine ignition the bubbling is discontinued

and the LOX tanks are pressurized with helium from a ground source. After

liftoff, the LOX tank pressurization is maintained with GOX converted from

LOX in the heat exchanger.

-4

Sta r t Automatic

I

- 2 hr. ; 5 hr. -10 min -163 sec. - 3 sec.

before I I

Launch -Time t o Li f to f f 1 Liftoff

IA

GN2 Bubbling

RP-1 Sta r t- Final Adjust t o 100%

LoadingSystem RP-1 Pressurize Tanks

!I I

ALOX- S ta r t

I

Loadi nq

System LOX

I r essu r i ze7Tanks --OX



19.3 cu. t.

H e Spheres ( 2 )f o r RP-1 Tank

Pressurization

GOX Vent jRelief Valves

Ven t Reliefopen - 67.5 ps ia 60-62 psia

close - 64psia 59.0 psia GN2/He Vent Valves

open - 21 psigclose- 19psig

I

I

Outer

LOX Tank ( 4 ) ICenter I /RP-1 Tank (4 )

LOX Tank-

RP - I below container

LOX below container bo tt om atbottom at

L i f to f f ~5,700bs.

Liftoff ~ 8 , 7 0 0bs

LOX Fill 6 Drain

GHe from GSE for --in i t ia l LOX Tankpressur i za t ion

H e a t Exchan e r

2roduces GO forin+ l iqht pressurizat ion

Total a t l i f t o f f 897,200 bs.

To ta l propeltant consurn ad after liftoff

- 805,500

Propellant Sys t em



S-IB STAGE THRUST VECTOR CONTROL SYSTEM

Each of the four outboard H-1 engines is gimbal mounted on the stage

thrust structure to provide engine thrust vectoring for vehicle attitude

control and steering. Two hydraulic actuators are utilized to gimbal each

engine in response to signals from the Flight Control Computer located in

the Instrument Unit.

The actuators are part of an independent hydraulic system on each

gimballed engine. Hydraulic fluid flows to the actuators from the high

pressure accumulator and returns to the low pressure reservoir. The

electric motor driven auxiliary pump operates only during prelaunch check-

out of the thrust vector control system.



L o w Pressure 53 p s i q

Vehicle T h r u s tSt ruc t ure - A c t u a t o rAttachment Point

movement as commanded

by Flight Control Computer

Hydraulic A c t u a t o r ( 2 )

Dr iven by EngineElectric M o t o r T u r b o p u m p a t 4000 rpm

Drive at 11,300 b pm O u t p u t 18 qp mOutput 3.0 gpm

Outboard Engine (4)Gimballed ;

I n b o a r dEnqine

(4 )Fixed Pos i t ion ; ICanted O u t b o a r d 3"

Fiqure 2 2 S-I6 Staqe Thrust V e c t o rCon t r o l System

39



rS u mm a ry o f M e a s u r e m e n t s -

S- IB-JI n f l i q h t

f. L;q. Level 482. Temperature 903. Pressure 302

4 . S t r a i n 4245. Vibration 6 2

6. Siqnals 62

7 Voltaqe, Current, Frcq. 258. Miscel laneous 30-

o ta l -503

LCC ( B l o c k h o u s e ) - 67 *--

* - 122 blockhourr mee.arealso ~nCligMnea. Note:There w e r e - 418 inCliqht w d 176

LCc measurement on O-tB-l

TO Blockhouse th ru p re f iqhtd a t a a c q u i s i t io n s y s t e m

Used f o r q ro un dcheckou t on l y

r - - - -1I

IT r a n s d u c e r orS i qna l Sources

II

T hermocoup l e I

Is t r a i n Gauqe I

IA cce l e romete r I

(V i b ra t i on ) I

Vol taqe, ISensor, e t c . Meas. I

Di r t .I

II

I

TO T e l e m e t r y

IS y s t e m

I

IM e a r u r i n q R a c k / L 8Vdc(7 in 5-16 Staqe I 5 V d c

I - - - 7 11 IValtaqe IS i q n a l s ( l i f t o f f , C.O., Dividinql 1

etc . ) * Network1 I

zevdc l L---1- 1 I

II

II

P oten t i ome te r t ype 0 - 5 V ~ C

[ (pressure qauqe, Ilong. accel., et~.) I

5 Vdc 1 III

I

L - - - - - l

C o n t i n u o u s l i q u i d D i g i t a l O at a To

l e v e lT e l e m e t r y

S y s t e m

Fiqure 2311 S-IB Staqs Measuring

Syr+rm I



Aniennas Command Signa lsFrom S-11 Ctrqe$wii& Seleo+or

SS - S i n q l e SidebandFM - F r e q u e n c y M o d u l a t i o nDDAS - D i q i t a l Data A c q u is i t io n SystemPAM - Pulse Amplitude M o d u l a t i o n

PCMP u l s e C od e M o d u l a t i o nTM - T e l e m e t r y

R F - R a d io F r e q u e n c y

9From.

measur~ngdistr ibutors

Hardwire to

LOCtai l

FromSwitch S e l e c t o r

input

I

CalibratorA s r ' y

+To F1, F2 P1 M u l t i p l e x e r

*AISO c a r r i e s m u l t i p l e x e 2data f r o m F1 4 FZ

Fiqure 24



To Se~a ra t i on BW

Signals f rom meas. racks

and meas. transducersTo

Retrorocket EBW

. transducers

I 28 vdc

MasterTo S - I 0 Stage

Switch Selector To both desfruct Voltagesystem controllers

meas. racks

- - - - _ _ _ _

I -I8 Staqe E utrirul Power

ard 0 l r t r ~ uf~onSystem

-'I 1 Siqnals from Siqna l~ r om (~npressurized)

Tail Area

meas. racks and meas. racks andPropulsion System

rneas. transducers meas. t ransducersD is t r ibu to r

To meas. ra cks To meas. r a c k s

To TM Measurinq Measuring To TMsystemd Dis tr ibutor Dis tr ibutor 1 * System

C----

+To EnqineControls

Meas.

tMeasur inq ' To TM

- - - -

D i s t r i but o r

TO all t a i l

me as. d i s t . J,s~,u,,,+Compartmhi F-2

(Pressurized)- - - - - - - - - - - - - - - - - -

System

t






S-IVB STAGE STRUCTURE

The S-IVB Stage is a 260-inch diameter semimonocoque structure consistingof a cylindrical propellant container with hemispherical ends, a thruststructure assembly, a forward skirt, an aft skirt, and a S-IB/S-IVB interstage.

The propellant tanks are separated by a common hemispherical bulkhead.The liquid oxygen tank is located aft of the liquid hydrogen tank. A singleJ-2 engine is attached to the stage by a conical thrust structure assembly.

PROPULSION SYSTEM

A single Rocketdyne 5-2 engine mounted on the vehicle centerline powersthe second stage. Using LOX and LH2 as propellants, the engine develops a thrustof 200,000 pounds. 'During powered flight, vehicle pitch and yaw control momentsare attained by gimbaling the engine. The Auxiliary Propulsion System providesroll control during powered flight and provides control in all axis duringorbital coast.

LH2 EXPERIMENT PECULIAR EQUIPMENT

1. La2Tank Venting Systems

The LH2 tank can be vented by two systems. The non-propulsive ventsystem rapidly reduces the LH2 tank pressure. The smaller propulsive vent systemis enabled shortly after insertion into orbit and produces a minimum vehicleaxial acceleration of 2 X G to bottom the propellant.

2. TV System

Two TV cameras and two 300-watt lamps, mounted on a modified LH2 domemanhole cover view the interior of the LH2 tank. Electrical heaters will beoperated continuously during the experiment to keep the camera temperatures fromfalling below the camera operating limits.

Instrumentation

Instrumentation has been added to the basic S-IVBIIU for the experiment.These instruments consist of numerous temperature and liquidlvapor sensors withinthe LH2 tank of the S-IVB for the purpose of locating the liquid and studyingthe convective patterns within the LH2. Also, a quality meter has been added tothe hydrogen continuous venting system to measure the liquid-vapor ratio in thevented gas. Other appropriate temperature and pressure measurements are includedin the hydrogen vent systems, and the ullage thrust system to permit calculationof flowrates, thrust, and thrust unbalance. Temperature and pressure of theambient helium bottle are measured to determine tank repressurization requirements.The hydrogen recirculation system and engine bell are instrumented with appropriate

temperature and pressure sensors to provide'for detailed assessment of enginechilldown for engine restart.



View Looking*4

Gox utloqe Uotzles(2)ox utloqe Uotzles(2)

L _UL kon pvopulriue vent

L U ~ ropulsive vent- -(2,\80e \psrt)

Inclodinq %in. pwlnnconoC LUt tank beyond S-\VB/IUmatinq suvCaca

LUz NOU-pvopulsive vent0)

LU2 Propolsive Vent (2)

rnmon I k lkhead

Salve stoqe wr iqg *

'Dry: -2$ lOO lbe:* A t + lVb qnition ;-187,000 Ibs . -----4 ~ 4 - ~ VB utoff r -60,400 I s.

b - - 0 i a . 2 ~ in.--.(

ifErctudec wt . aC v e + m v c k e k4 6 t iruberstaqe

S . 1 ~ 0Staqe C ~ ~ g u r a t i o n

4



5-2 ENGINE OPERATION

The normal operating cycle of the 5-2 Engine consists of prestart, start,

steady-state operation, and cutoff sequences. During prestart, LOX and LH2flow through the engine to temperature-condition the engine components, and

to assure the presence of propellant in the turbopumps for starting. After

a timed cooldown period, the start signal is received by the sequence controller

which energizes various control solenoid valves to open the propellant valves

in the proper sequence. The sequence controller also energizes spark plugs in

the gas generator and thrust chamber to ignite the propellant. In addition,

the sequence controller releases GH2 from the start tank. The GH2 provides

the initial drive for the turbopumps that deliver propellant to the gas

generator and the engine. The propellant ignites, gas generator output accel-

erates the turbopumps, and engine thrust increases to main stage operation.

At this time, the spark plugs are de-energized and the engine is in steady-

state operation.

Steady-state operation is maintained until a cutoff signal is received

by the sequence controller. The sequence controller de-energizes the solenoid

valves which in turn close the engine propellant valves in the proper sequence.

As a result, engine thrust decays and the cutoff sequence is complete.



Propellant ut i l izat ion

valve regulates LOX

Flow to minimize LHzand LOX residuals a tcutoff. Varies mixtureratio +_ 10%

LH2

I

- - - - - - - - - - -

Thrust ChamberTank Pressure

Mixture Ratio

L H 2 circulates thruThrust chamber wallt o cool wall

200,000 Ib s Thrust

Fiqure 27



S-IVB STAGE PROPELLANT SYSTEM

L O A D-LOX-ystem

LHtSystem

The S-IVB propellant system is composed of integral LOX/LH2 tanks,propellant lines, control valves, vents, and pressurization subsystems.Loading of the propellant tanks and flow of propellants is controlled by

the propellant utilization system. Both propellant tanks are initially

pressurized by ground source cold helium. LOX tank pressurization during

S-IVB Stage burn is maintained by helium supplied from spheres in the LH2

tank, which is expanded by passing through the helium heater, to maintain

positive pressure across the common tank bulkhead and to satisfy net positive

suction head. The LH2 pressurization strengthens the stage in addition to

satisfying net positive suction head requirements. After engine ignitionthe pressure is maintained by GH2 tapped from the engine supply.

S-IVB PROPELLANT LOAD AND OPERATIONAL SEQUENCE



LH2 TankVent Valve

(pressure

stepped a t launch

+150 sec. to open at42psia and close at39 psia vent setting)

S IVB burn fo rSphetes For &OXTank p r e s s u r ~ z a t i o

- w

Tank - 10 sec. aher mairrstage s t a r t

LH2 tank is abou t 50%

full at J-2 enqine cuto f fLOX remainin at J-2

enqine c u t o f? is~ 4 8 0 0bs.

t a nk



TelemeieredError Signal

Telemetered ValveCommand Signal

Servo Moto r locked in null position

Telemetered

Valve Posit ionSignal

Fiaure 24






S-IVB STAGE THRUST VECTOR CONTROL SYSTEM

The single 5-2 engine is gimbal mounted on the longitudinal axis of

the S-IVB Stage. Power for gimballing is supplied 'by a hydraulic control

system mounted on the engine.

Pitch and yaw control, during powered flight, is maintained by actuator

control of the engine thrust vector. Roll control of the stage is maintained

by properly sequencing the pulse-fired hypergolic propellant thrust motorsin the APS. When the stage enters the coast mode, the APS thrust motors

control the stage in all three axes.



Turbo pump at

Electric ~ o t o ;Drive at 13,000 rpmoutput 1.5 qpmat 3550 ps i9

Poin

.aul e

t

Aciuaiors (2)

APS Nozz les

Ac t u a t o r s ( 2 )

Gimbal pattern(Looking Fwd)

S-IVB Stage Thrust VectorControl System1



AUXILIARY PROPULSION SYSTEM

The APS co ns i s t s o f two se l f -con ta ined a t t i tu de con t ro l modules mounted

18 0 d e gr e es a p a r t on t h e a f t s k i r t of t h e S-IVB s t ag e . Each a t t i t u d e co n t ro l

module con t a ins t h r ee t h r us t motors which use hypergo l i c p rope l l an t (n i t rogen

t e t r o x i d e (N204) and monomethylhydrazine (MMH). The th ru s t motors a re pu l se-

f i r e d and no i g n i t i o n s ys te m i s requ i red . The th ru s t motors provide pi tc h , yaw

and r o l l c o n t r o l d u ri ng t h e S-IVB coas t mode of o pera t ion , and ro J l con t ro l dur ing

powered f l igh t s .



Thrust StructureW id t h - 23"

Outer Module

150 Ib. Thrust

S-rv0 A f t Sk ir t

View from af tlooking f o rward o r

downr anqe

Fiqure 31

Vehicle Pitch



S u m m a r y of Measurements 1I n f l i q h t

I. Liquid L e v e l

2. T e m p e r a t u r e3 . P r e s s u r e

4. S t r a ~ n

5. V ib ra t i on

6. S i r j n a l s

7. Vol taqe / Current

8. M i s c e l l a n e o u s

T o t a l

I (B l o ckhou s e ) 1--1~1 * I

4421 Lcc measuvemetu% AVC

619 used 6%cnClcc\h~m r a ~ u v e W S .

Tranr ducer o r

S i q n a l Sources

Refe renceT h e r m o c o u p l e

R e s i s t a n c e ~he r rnome te r I

C o n d i t i o n e r 5C r y s t a l V i b r a t i o n Pickup --r i d a e Boxes

Strain Gauqe - I so la t ionBoxes

S i q n a l s ( s wi tc h es , et c .)- D i s t r i b u t o r s

( v o l t a q ed i v i d i n q

S i q n a l s (sw i tches ,e tc . ) networks)

5 vd c V o l i a g ef - s o u r c e s

L o t e n t i o m e t e r T y p e(Pressuse Gauqe , e t e . )

w To TM



U o ~ tMI e ~ u i p ~ e n touted

An t e nn a s IN Fwd 5kirt except M Aneennas,

S- I trdnimitter com-manded oFFIYami@.

From



Battery f I28 vdc

Rsnqe Safety

System (Yo.1

Battery*2

80ampkr. 4 amp. hr.

To R a n q ~ ,

Sa f e t y

A f t S k i r t

Sys tem

No.2

56 vdc25 amp.hr.

Meas. Voltaqe To Meas.sy8titon~

TO B a t f . 28 vdc

Pressu r i z a t i onSys.






INSTRUMENT U N I T

The S-IU-203 Ins t rument Uni t ( IU) s t ru c tu r e co ns is ts of th re e a r c

segm ents (numbered 601, 602, and 603) of sandwiche d honeycomb. The t h r e e

a r c s eg me nts a r e j o i n e d w i t h s p l i c e p l a t e s b o l t e d t o t h e s k i n a nd t h e c h an n el

r i ng segments , thu s forming a s i ng le un i t of honeycomb const ruc t ion . This

co ns t ru ct ion forms an assembly 260 inches i n d iameter and 36 inches h igh.

Brack e t s a r e bonded t o t h e i n n e r s k i n t o p ro v id e mo un ting s u r f ac e s fo r 1 6

co ld p la te s , which a r e 30 inches square . A c o o l a n t f l u i d i s c i r cu l a t ed t h ro u g h

t h e c o l d p l a t e s t o d i s s i p a t e h e a t g e n er a te d by t h e e l e c t r i c a l componentsmounted on them. This arrangement provid es cle ara nce fo r th e landing gear

of t h e L un ar Module t o b e i n c l u ded i n l a t e r mi s s i o n s , and f o r t h e forw ard

bulkhead of t he S-IVB hydrogen tank which extends i n t o th e I U . A honeycomb-

con st r uct ed acc ess door i n segment 601 provides acce ss t o components wi th i n

t h e I U a f t e r t he I U i s assembled as pa r t of the veh i c le .

P r i o r t o v eh i c l e l aun ch , a t emp era tu re co n t ro l l ed a t mos ph ere i s fo r ced

i n t o t h e I U and S-IVB forward s k i r t f rom a ground source t o maint ain a

temp eratur e of 60 t o 80 degrees Fahre nhei t . Compressed a i r i s used a s a

purging medium up t o t h i r t y minutes bef or e t he S-IVB s t ag e i s loaded wi th

p r o p e l l a n t , t h en t h e a i r pu rg e i s rep lac ed wi th a n i t ro ge n purge. The com-

p a rt m en t pu rg e w i l l b e d is c on n ec te d a t v e h i c l e l i f t o f f by r e t r a c t i o n of t h e

I U u mb i l i ca l s e rv i ce a rm.



C o n t r o lComputer7 111

C o l d p l a t e s (16 Requi r

I1

A c c e s s Door

Umbilical Plate

Honeycomb Panel

II

V i e w Lookina A f t

I V I

I Television 1I \ \ I- I

II

1 \,- /

Access TMD oor

A -..a-

I V I Jl111

Television

I \ \ II

W e i q h t :

D ry : - 4 2 5 0 lbs.

A t S-IVB ignition: - 560 Ibs.

* A t S - I V B cutoff : A4560 bs.

-

,-

Fiqure 35

II

1 \ IFA/

Access TMD oor

TM A zusaUmbilical Plate

Antenna Arranqement



* * A l l blockhouse meas. are a l s o u s e das i n f l i qh t meas.

+*Thevcw.*s -303 inflisht an d -172 LCC

heasuremen+s on 3-TU-201.ummary of M e a s u r e m e n t s

t n c l u d e s MSC E x p e r i m e n t measure-

m e n f s .

In f i gh t

V o l t a q e , Current { Freq.

Pos. i Anqutar Velocity.,

Temperature - - - - - - . -Pressure f Flow Rate--

Vibration - . , - , - , - -

Guidance 6 Control - - -D i s c r e t e Siqnals, - ... -

Misce l laneous- . - - .

LCC ( Blockhouse)

To othermea surinq racks

S-IU-203

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26

46

87-4-362 *

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Measurinq U s e d #o r qroundI ~ h o c k o u *on ly

Transducer or

S i q n a l Sources

Thermocouple

Accelerometer( Vibration)

Error Siqnals(computer 4

platform )

Muasurinq Rack

( T o t a l - 9 )

r - - - 1II

II

2 AC

Ampl;f i e r

II

Amplifierq-<Meas.D i s t .I I - - - - 'I

S y s t e mI I- s Vdc

I5 Vdc

I IS i q n a l ~Prst Mot;on, 1 Gohaiel 1

Separation, etc.)Dividnn I

~n. tw.d l20vdc I L---l I- 1 I

IPotentiometer Typr 0 - 5 v d c

I(pfcss. q a u e,

I Itons. accei!, cte.)

5 vdc I- I

Oiqita l Data L,,-J ToGuidance S y s t e mOiqital Command System

m T e l e m e t r ySystem



N d e i Thr fU t o emetvy sycfcmmen) an continoo.r~\y,during F\+t.

Antennas

5-18Prop l e ve l S - 1VB enqine C . O .

sensoractivation; 4 19'1.2 sec.1.0.+ 137.4 sec.

Playback Stops:- Recordin4 Stops:

S - 1V6 enqine c. o.5-18 O E C O + 225.2 eec.

42%. see.

FromSwitch Selecto To Ff, F2, S-f & P-1



To Trackinq and

Cooling Systems

TO MSC CryogenicDistributor Exp e r im en t

To L,Hz Battery IExperiment TV Battery

A 28 vdc- 28 vdc

300 Amp Hr. 300 Amp. Hr.

G r o u n d power

28 v d c

C o n t r o l4 Power

D i s t r i b u t o r

a 56 v d c56 vdc

D is t r ibu tor 29 vd c Power

4 A A A*

Su p p l y

t tBattery Battery28 vdc 28 v d c

300 Amp, t\r. 300 Amp . Hr.

To C o n t r o l

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vTo I U

Switch Seleefor

v

To

To S- IVBTM Sy

Staqeol Siqnal

V e s s o r

To 5-16

Staqe

To

TM Sy s t e

Fiqure 38






ENVIRONMENTAL CONTROL SYSTEM (ECS)

Heat g e n e r a t e d by t h e e l e c t r o n i c e q ui pm en t l o c a t e d i n t h e S-IVB forward

s k i r t a nd t h e I U i s d i s s i p a t e d by c i r c u l a t i n g a methano l -water so lu t i on

t h r ou g h t h e co l d p l a t e n e tw or k.

P r i o r t o l i f t o f f , a methano l -water so lu t i on i s s u p p l i e d a nd c i r c u l a t e d

t hr o ug h t h e c o l d p l a t e s f ro m t h e GSE. A ft er l i f t o f f t h eECS i s

a s e l f -co n t a i n ed u n i t wh ich b eg i n s o p e r a t i o n 3 m in ut es a f t e r l i f t o f f when t h e

s u b l i m a t e r i s a c t i v a t e d .



c ~ ~ d ~ \ r t e ;tc . required)(M in. ~qoar r )



MSC EXPERIMENT PACKAGE

The MSC experiment is a subcritical cryogenic storage system orbital

test. The purpose of the experiment is to demonstrate operation of the

system in a weightless condition. The cryogenic fluid will be liquid

nitrogen, which was chosen to simulate liquid oxygen to eliminate the pos-

sibility of hazard to the booster and to eliminate the need for purging.

The experiment will attempt to verify the stratification of the

liquid phase, quantity measurement of the two-phase fluid, and uniform

delivery of gas in the weightless environment.

The experiment hardware consists of a spherical tank and signal con-

ditioner plate. Sensor equipment is located on the vessel, and the sensor

output is conditioned at the equipment mounted on the plate. The param-

eters to be measured will be transmitted by the IU telemetry system.

Siqnal ConditioninqEquipment

Siqnal Conditioninq

Plate /J,*---St-~~z Storaqe Sphe r e

Sensor Equipment

(Gaseous Flow

- Temperatures,/ressures and 1

\Skin and Strinqer

Quality) To I-U ConstructionAblative Exterior

Telemetry Coatinq

I Weight: - 3700 lbs.

Nose Cone -342 0 Ibs.M S C Experiment

Equipment - 280 Ibs.\verall length

* 31U.

Documents

AS-203 Technical Information Summary