as-203 technical information summary
TRANSCRIPT
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 1/69
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)
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 2/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 3/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 4/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 5/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 6/69
Intentionally Left Blank
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 7/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 8/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 9/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 10/69
Fiaure 2 Launch Complex 37=
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 11/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 12/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 13/69
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 )
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 14/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 15/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 16/69
Fiqure 7
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 17/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 18/69
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 )
>
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 19/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 20/69
- 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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 21/69
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)
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 22/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 23/69
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 ).
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 24/69
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---
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 25/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 26/69
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-
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 27/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 28/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 29/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 30/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 31/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 32/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 33/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 34/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 35/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 36/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 37/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 38/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 39/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 40/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 41/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 42/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 43/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 44/69
Intentionally Left Blank
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 45/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 46/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 47/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 48/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 49/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 50/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 51/69
TelemeieredError Signal
Telemetered ValveCommand Signal
Servo Moto r locked in null position
Telemetered
Valve Posit ionSignal
Fiaure 24
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 52/69
Intentionally Left Blank
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 53/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 54/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 55/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 56/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 57/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 58/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 59/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 60/69
Intentionally Left Blank
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 61/69
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.
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 62/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 63/69
* * 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
2 7
45
6433
26
46
87-4-362 *
,224**,
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 64/69
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 65/69
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
Computerl 1o Da t aAdapter
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
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 66/69
Intentionally Left Blank
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 67/69
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 .
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 68/69
c ~ ~ d ~ \ r t e ;tc . required)(M in. ~qoar r )
8/6/2019 AS-203 Technical Information Summary
http://slidepdf.com/reader/full/as-203-technical-information-summary 69/69
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.