technical information summary concerning saturn vehicle sa-3

8/6/2019 Technical Information Summary Concerning Saturn Vehicle SA-3

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SATURN HISTORY DOCUMENTUniversity of Alabama Research InstituteHistory of Science & Tec iw~ logyGroupDate- - - - - - - - - - Doc.No. - - - - - - - -

h4emorondurnT O Dist r ibut ion

FROM SATURN Office,

GEORGE C. MARSHALL SPACE FLIG HT CENTERHUNTSVILLE, ALABAMA

EFNoel j l r /876-3692CBSones/876-5326

D A T E November 2, 1962Memo #M-ASTR-TSJ-33-62

Astr ionics Divis ionM-ASTR-TSJ

SUBJECT Tech nical Info rmat ion Summa ry Concerning SATURN VehicleSA-3

Th is me mo ran du m ov. tl ines , through a se r i es of ske tches , som e ofthe imp ortan t fea tu re s and sequence s concerning the thi r d SATURN fl ightveh ic l e , T he ske t ches a r e devot ed p r i m ar i l y t o t he con t rol and i n s t ru -men tat ion as pe cts of the veh icle but a l so touch on the launch faci l i ty andcountdo wn s checiule .

1. Introduction-The SATURN C -1 P r og ra m has a s i t s p r i m ar y ob j ec ti ve , t he

i development of a lar ge two stage vehicle for use in spa ce opera t ions. T enveh i c l e s a r e p lanned fo r t he r e s ea rc h and devel opm en t phase 2nd a r edivided into Block I (SA-1 through SA-4) and Block I1 (A-5 through SA-10).The f i r s t four SATURN vehicles wi l l be launched fr o m complex V L F 34 a tCape Can aver al , on an azimuth of 100 de gre es Ea st of North, T h e g e n e r a la r r ang em ent of l aunch complex VL F 34 i s s een in F igur e 1.

In t he Block I se r i e s , only the S- I s t ag e i s p rope ll ed and th er eis no sep ara t io n of the S- I s t age f ro m the dummy upper s t age s . T he S-IVstage wi l l be a ct ive on the Block 11 vehicles (SA-5 and subsequen t ) .

2. Review of Pre vio us Fl ight Te st Resul t sa . The f ir s t vehic le of this s e r ie s (SA-1) 1,vas launched with no

technical holds, a t 1006 EST on Octob er 27, i96l fr om Launch C omplex 34,AMR, on an az imuth of 100' Ea st of North.

The f l ight perf orm znce of the vehicle wa s e xcel lent ; no ma l-func tions or dev ia t ions w er e o bserved which could be cons idered a s e r i o u ssys t e m fa i l u re o r de s i gn de fi ci ency. I l ow e~ re r ,s loshing instabi l i ty wase n co u nt er e d a f t e r 90 s e c o ~ d s f f l ight ; a l though the re was m or e s loshingthan expe cted, i t did not ap pro ach the point of endange ring veh icle con tro lo r s t r uc tur a l i n t egr i ty . The maximum engine def lec t ions due to the e f fec t sof sloshing we re f1/2 deg ree in pi tch and yaw, and +1/4 deg ree i n ro l l .Addit ional ant i -s lo sh baffles have been placed into the lowe r end of the eight


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outer t anks (See F igu re 9) on SA-2 , 3 and 4 to cont rol propel lant s loshingdur ing the l a t t e r p ar t of the propul s ion period .

P i t ch ac tua tor def lec t ions of 2 degrees resu l t ed f ro m the t i l tp r o g r a m c o m m a nd s , a s e x pe ct ed . Even though this did not have a nyappr eciab le effect on the s tab i l i ty of the vehicle , a "smooth" t i l t pr og ra m(See F i gu re 8) was int roduced on SA-2 and subsequent vehic les .

SA-1 did not have act ive path guidance; however , pa sse nge rguidance har dw are w as onboard for the purpose of R & D tes t ing. In addi -t ion , c e r t a i n R & D con t ro l s en so r s w e re a l so flown .

SA-1 had a tota l of 505 inflight me as ur em en ts of which only-fai led , and 11 only pa rt ia l ly fai led. The infl ight cal i bra tor on Link 3 fa i led- -during fl ight . All R F sys t e m s pe r fo rm ed sa t i sf ac t o r il y .F or a detai led analysis of the fl ight per for ma nc e of SA-1, se eMPR -SAT-W F-61-8, SATURN SA-1 Flight Evaluat ion, dated De cem ber 14,1961.

b. The second SATURN fl ight vehicle (SA-2) wa s a ls o launchedf r o m V L F 34 with no tech nical holds a t 0900 EST o n Apri l 24, 1962, Thelaunch proc eded wi thout di ff icult ies and the f l ight te st wa s a com ple t e suc -c e s s .

.Operat ion of the cont rol sy ste m was sat i sf actor y; the s loshinginstabi l i ty noted in the SA-1 f l ight was successfu l ly s u4 pre sse d by theaddit ion of the baffles in the lower end of the ou ter pro pellan t tank s.Engine pi tch deflect ions of 2 degr ees resu l ted fr om a n unexpected bindingof the t i l t device ca m . The se t rans ie n t def lec t ions appe ared a t i n t e rva l s ofapproxima te ly 13 seconds . This condit ion ha s been el imjnated by a rede signof the f ine ze ro ca m of the t i l t pr og ra m t ran sm iss ion . In addi t ion, a spe cia lla bo ra to ry che ck of the op erat io n of this de vice is now ma de.

SA-2 did not have act ive path guidance; however , pas sen ge rguidance ha rdw are was onboard for R&D tes t ing . R & D c o nt ro l s e n s o r s w e r eaga in flown.

A to ta l of 526 inflight m easu rem en t s w e re f l o w on SA -2 . OfP -th is total , only 6 m eas u rem en t s f a il ed , and 1 m eas u rem en t pa r t i a ll y f a i l ed.-A ll R F s y s t e m s p e rf o r m c d s a t i s f a ~ t o r ' i l ~ .A water c loud exper iment ( Pro jec t Highwater ) was successfu l ly

acco mpl is hed by inject ing the upper s tage s! wate r b al la st (190, 000 pounds)


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in to the upp er a tmo sph ere a t an al t i tude of 105 km by ruptur ing the uppe rs t ages w it h p r i m a co rd a t L. 0 . t. 162 second s.

F o r a detai led analy sis of the f l ight pe rfo rma nce of SA-2, se eMPR- SAT -WF-6 2 -5, SATURN SA-2 Flig ht Evaluat ion, dated Ju ne 5, 1962.

3 . Re sum e of Main Fe atu re s of SA-3a. Fu l l Pro pel lan t Loading (620,000 pounds on SA-1 and SA-2ve rs us 780,000 pounds on SA-3).

T h i s r equ i r ed a change i n t he con t ro l ga i ns p r og r am fo rSA-3. Th is addit ional weight of 160,000 pounds ha s red uc edthe l if toff acc ele rat ion con siderably (1 .4 g on A-1 and SA-2ve rs us 1 .2 g on SA-3) .b. Proj ec, t Highwater

Thi s exper iment wi ll be ca r r i e d out fo r the second t ime onSA-3 . The mai n d i f fe rences a r e :

SA -2 SA-3T i m e L . 0 . t 162 se c. L.O. S 295 sec.Altitude 105 k mRange 81. k mc. Centaur Exper imen t

Thi s is a dynam ic study conducted in supp ort ofthe Centaur pro gra m. Th.e detai l s of the s imula ted Centaurweather sh ie ld a r e shown in F igure 3 . The fa i lu re of theCentaur f l ight is bel ieved to have re su l t ed f ro m def i c i encies ini t s wea ther sh ield .d. ST-124 P Ine r t i a l P l a t fo rm Sys t em

A labo rat ory mod el of the ST-124 s ys tem (m anufactured byM-ASTR) wi l l be f lown for the f i rs t t ime.e . The S-I re t ror ock e t s wi l l be f i red a t Inboard Engine cutofff 12 seconds.f . Outboard Engine Cutoff w il l be given by a propel lant deple-t ion signal instead of by a t i i ~ e r s in S A-1 an d S A-2.g . An umbil i ca l tower swing a r m wi ll s e rv ice the forward endof the S -1 sta ge instead of the long cab le rriast used f or SA-1and SA-2.


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b. Th.e 400 VA St atic Inv er te r which su pplies 400 cycle, 115v. a. c . power to the ST-124 Iner t ia l P la t fo rm System.

5. Guidance and Control R&D Hardw are (See Figur e 6)The following d evices a r e being tes t f lown on SA-3 to obta in

so me of the nec ess ary engineer ing informat ion re quir ed for the develop-me nt of the guidance and co ntro l s ys te m of futu re SATURN C-1 vehicle s:

a . Th ree ST-90 mounted AB - 3 Acce le romete rs which p rov idevelocity informatio n in "digital" form .b. A Guidance Signal Pr oc es so r - Repea ter (GSP-R) whichprocesses the "digital" velocity signals and conditions themfor t e lemete r ing .c. A 3 axes Control Rate Gyro Package which provides a t t i -tude r a te in format ion a s a . c, signals to the Control Signal' ~ r o c e s s o r .d. A Control Signal P ro ce ss or which conv er ts the a tt i tudera te informat ion to d , c , control s ignals and condi t ions themfor t e lemete r ing .e. Pi tch and yaw Contro l Acce le ro mete rs which mea sur ela te ra l vehic le accelera t ions , conver t the s ignals to d , c .control signals and condition them for telemetering .f , A Q-bal l Tra .nsducer which me as ur es pi tch and yaw ang les -of -a ttack and dynamic p re ssu re , conver t s the s igna l s to d . c.and condi t ions them for te lemeter ing.g . A ST-124P Iner t i a l P la t fo rm Sys tem (P la t fo rm, E lec t ron icBox and GSP-R) which provides a t t i tude e r ro r s ignals f romi t s g imbal res o lve rs to the te lemete r ing sys tem and ve loc ityinformat ion in "digi ta l" f orm fro m i ts thre e AB-3 Acce leso-m et e r s th rough i t s GSP-R where they a r e condi tioned fo rte lemete r ing .h. In addi tion, a Horizon Sensor System and a Tim e BaseSelec to r a r e a l s o be ing f ligh t t e s ted .

6. T r a j e c t o r yThe bas ic f ligh t t r a jec to ry fo r SA-3 (with 'all eight engine s

ope ratin g) i s orztJ.ined in F ig ur e 5. . The t il t p rogra m i s based on the seven5


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b. Azu.sa and C-Band Rad ar Systems: The se sys tem s pr o-vide s i gnals to a ground computer complex to obta in posi t ionand ve loc i ty in fo rmat ion . These t ra j ec to ry da ta a r e p resen t edon p lot ting board s fo r the range sa fe ty o f f icer to use in de t e r -min ing " rea l t ime" veh ic le pe r fo rmance . In addi t ion , they a r ea l so used fo r the pos t f l igh t evaluat ion of the veh ic le ' s t r a je c -to ry .c. UDOP Sys tem: Th is sys tem prov ides t ra jec to ry da ta(vehic le position and velocity) for the pos t f l ight evaluationof the veh ic le ' s pe r fo rmance .


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SA- 3---.-~W+ , C L ,CGU~


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"Q " DQll OF A*CK Timnsduccr/ (P4Y) - 1 5 - (passenger)Jup i t r r N o s e C o n e

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SA-3----Y. Co-)>is+-er A r r a n g em e n t


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MOTE: For excscb sln vslues see ~ ~ h ; o n b c ~;v;sion?e m o , NA 451 / 62 d a k d S y % , 2 5 , 19b2SA - 2 q a b ~ s Lve s h o w n t bm~ --

Conk01 E n q i n r ~ I , , 3 ,4 )Swivel an le f "~ e u n + i n ~radius 95"&q,t an le 6"3


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T i ~ t V O ~ V - Q ~w s t be s e ~ e c t e dabout one mon t h bef-ove lakncl?

ve &ire s a. n e w caw\.9

4oocps s n c h v o n o u s4moto r a n d geQ r h e a d( s t a r t e d at powev t v a v l s f e r )

ST- qop i t c h v i n 9 gear(moves w L t h t h e veh i cLe )

Mc~xirnuw ilt r a t e : 0.6 O/sec - -FinaL * l t a n q t l e : 44" f v o w launch v e v - k i c a lT i l t c t v v e s t : 1 3 2 s e c a f t e v L i f t o f f T;kt @vrestatTilt pvoovanz is based u p ow , t h e e n i n e - o x t cconsept ;9 132 sec a-t 4bDdt h a t L s , t h e t l l t a n ie is p r o p c v jr., o w l ? +-ow the9 ~ O - L L V I C ~ev-kicai;7 eviqirles opeva t i n g f v o m Llft of f -+ 20 s e c o ~ d 5 . caw devtce

keeps +uvninTilt a-gte o0 0 . 3 . 4.1" 14.9~ 29.2' "c

(engage. pitch pqw.t v a v r sm~ s s r o v~L U ~ C L \ )istc.0. zhd .O .----- 40.75ec 4 (47.8 se t(qiven by !give* b ypvo pe l 1avtt Thrust- OK"

l e v e L seMsov ) s w i t c h )


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' 7 0 " L o x Taok 105" Lox Tank 70" uel TaokPro p ell5q-t Pvopc t t a n t PropeLZan*coo-75ccwptiovl %3.8 '~ec . COMSLCWp t i o e -_~_4.0"/5e~. cons am p t b m - ~ .6'Ysec.

- S R - 2

S t a . 2 6 4 --sea. 235 ----------

FLU- '~~e v e l sevisov&cLfSLe we t c l j h t a d d e d

f o v ~ k - 2 , 3 ! 4 300 Lbs.

12"f. -sA?,- ----P r o F ~ k l ~ ~ t -a n k s


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I * For the c o n k \ frpqucncy (6 .3 Y)I) i t as a RC~ombina%on where a. 40. p h a s e lead w : f i +-D +-L,eout s g*in\ (p) i~ achihved.

CJ f r e q u e w c y (2- 4- rps) 'tt c - k as a,. Far t h e ek bend v )5 % ~ ~c%w~rk.bJh;ch prow i des ygprohimahlyAn ampliftca4 n g e e s with it but has no si3ni-f icanimpor-bnce .

3. For the i d bending eequency (6-lrcp) i t ach as on. o t ' ~ + = n u a b ~ ~Fr-uenc ics a b e 10 q s are suppressed by +?e secvo l aop.

Si-3- --~;m~l; f ie ;edxplanation of Shying ~ r t w o r k 'pp,y= =

technical information summary concerning saturn vehicle sa-3

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