Intelsat IV-A Press Kit 051877

8/7/2019 Intelsat IV-A Press Kit 051877

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N K A NewsNational Aeronautics an dSpace Adm inistrationWashington. D C 20546AC 202 ~ m ~ o

For Release IMMEDIATE

Press KitR E L E A S E N O : 77-99

Project INTELSAT IV-A

ContentsGENERAL IIELEASE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3S P A C E C R A F T D E S C R I P T I O N . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5E XPL ODE D VIE W O F AN I N T E L S A T I V -A S A T E L L I T E . . . .. . . . 6AT L AS CE NT AUR L AUNCH VE HICL E . . . . . . . . . . . . . . . . . . . . . . . 7T Y P I C A L L A U N C H V E H I C L E C H A R A C T E R I S T I C S . . . . . . . . . . . . . 8L AUNCH PRE PARAT IONS. , . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9T Y P I C A L L A U N C H S E Q U E N C E F O R I N T E L S A T I V - A . . . . . . . . . . 10NASA TEAM.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11I N T E L S A T T E A M . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 2CONTRACTORS........................,......o........ 1 2

Mailed:May 1 8 , 1 9 7 7


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N ! N e w sNational Ae ronautics andSpace A dministrationWashington. D C 20546AC 202 755-8370

David GarrettHeadquarters, Washington, D.C.(Phone: 2 0 2 / 7 5 5 - 3 0 9 0 )Dick McCormackHeadquarters, Washington, D.C.(Phone: 2 0 2 / 7 5 5 - 8 4 8 7 )Marilyn EdwardsLewis Research Center, Cleveland, Ohio(Phone: 2 1 6 / 4 3 3 - 4 0 0 0 Ext. 415. )RELEASE NO: 7 7 - 9 9

THIRD INTELSAT IV-A LAUNCH SCHEDULED

Fc lr ReleaseIMMEDIATE

The third INTELSAT IV-A commercial communicationssatellite will be launched by NASA aboard an Atlas Centaurrocket from Kennedy Space Center, Fla., May 2 6 , 1 9 7 7 .

The satellite, which weighs 1,480 kilograms ( 3 , 2 5 4pounds) at launch, is intended for service in the AtlanticOcean region.

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The 1,360 kg (1.5 ton) INTELSAT IV-A satellite willbe placed in geostationary orbit over the Atlantic Ocean at340.5 degrees East longitude, where it will provide inter-national communications services to countries from CentralAmerica to Iran. The satellite has a seven year design lifeand the capacity to relay over 6,000 simultaneous telephonecalls and two television programs.

The INTELSAT satellites are owned by the InternationalTelecommunications Satellite Organization (INTELSAT). TheCommunications Satellite Corp. (COMSAT), the United Statesmember, is also the management services contractor for thesatellite system. NASA is reimbursed for all costs of theAtlas Centaur and launch services by COMSAT on behalf ofINTELSAT, under provisions of a launch services agreement.

The Aklas Centaur 39 launch vehicle is expected toplace the INTELSAT IV-A in a highly elliptical orbit of 548by 35,787 kilometers (341 by 22,237 miles). After reorien-tation of the satellite, a solid propellant rocket motoraboard the spacecraft will be fired to circularize the orbitat synchronous altitude 35,787 km (22,237 mi.) over the

equator. At that altitude, because the speed of the space-craft in orbit matches the rotational speed of the Earth,the satellite remains in position over one spot.

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The launch of INTELSAT s p a c e c r a f t a bo ar d A t l a s Centaurr o c k e t s r e q u i r e s t h e c o o r di n a te d e f f o r t s o f a l a rg e g o v e rn -ment and indus t ry team. NASA's L e w i s Research C e n t e r ,Cleveland, Ohio , has management r e s p o n s i b i l i t y f o r t h e A t l a sCentaur development and o p e r a t i o n . NASA's Kennedy SpaceCente r i s a s s i g n e d v e h i c l e c h e c k o u t and l au nc h r e s p o n s i b i l i t yo nc e t h e v e h i c l e r e a c h e s Cape Canaveral.

The INTELSAT IV-A s a t e l l i t e s , b u i l t by Hughes A i r c r a f tCo., E l Segundo , Ca l i f . , a re 6.98 m e t e r s t a l l ( a b ou t 23 f e e t )an d w ei gh 1 , 51 5 k g ( a b o u t 3 ,3 40 l b . ) a t l i f t o f f a nd 82 5.5 kg( 1 , 8 2 0 lb.) a f t e r a p o g e e motor f i r i n g .

The INTELSAT IV-A p ro g ra m re p re s e n t s a n i nves tmen t by95 na t i on s exceed ing $295 m i l l i o n (U.S.). Each launch c o s t sapproximate ly $49.1 m i l l i o n -- $23 .5 mi l l ion for t h e s a t e l l i t eand $25.6 m i l l i o n f o r t h e A t la s C e n t a u r l a u n c h v e h i c l e .

( E N D O F GENERAL RELEASE. BACKGROUND I N F O R M A T I O N FOLLOWS.)

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SPACECRAFT D E S C R I P T I O N

The INTELSAT IV-A s p a c e c r a f t h as a n o v e r a l l h e i g h tof 7 meters ( 2 3 f e e t ) and a d i a me t e r o f 2 . 4 m ( 8 f t . ) .The h e i g h t o f t h e s o l a r p a n e l i s 2.8 m ( 9 f t . ) . L i f t o f fweigh t i s app rox imate ly 1 ,515 k i log rams ( 3 , 3 4 0 p o u n d s ) ,and i n - o r b i t w e i gh t a f t e r ap og ee motor f i r i n g i s 825.5 kg( 1 , 8 2 0 1 b a l a

Although it h a s t h e same b a s i c s t r u c t u r a l d e s i gn a si t s p r e d e c e s s o r , t h e INTELSAT I V - A s p a c e c r a f t i n c o r p o r a t e snew anten na tech nolo gy t o y i e l d a b o u t 6 , 2 5 0 two-way voicec i r c u i t s p l u s t w o t e l e v i s i o n c h a n n el s i n t h e s y st em con-f i g u r a t i on i n which it w i l l be used. T h i s i s t w o - t h i r d sg r e a t e r t h a n t h e c ommuni ca ti on s c a p a c i t y of t h e ZNTELSAT I Vse r ie s s a t e l l i t e . The i n c r e a s e d c a p a c i t y i s made possibleby a new ante nna de sig n which pr ov id es c overage of l a n dmasses on bo th s ides of t h e A t l a n t i c b a s i n , u s i n g s ha pe dbeams. The e a s t e r n and wes te rn beams a r e s u f f i c i e n t l yi s o l a t e d t o a l l o w t h e f r equency spect rum t o be u sed t w i c e-- once i n t h e e a s t and onc e i n t h e w e s t d i r e c t i o n -- t h u sd o u b l i n g t h e use of t h e f r e q u e n c y s pe c tr u m a nd i n c r e a s i n gt h e c om munica tions c a p a c i t y of t h e s a t e l l i t e .

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EXPLODED VIEW OF A N INTELSAT IV-A SATELLITE

-- TELEMETRY I COMM AND BICONESRECEIVE REFLECTOR

NUTA TION DAMPER

TRANSMIT EVENCHANNEL REFLECTOR

TRANSMIT 0REFLECTOR

TRANSMIT

EVEN CHANNELFEED HORNST R ANSMIT

G LO BAL OUTPUT INPUT FILTERSMULTIPLEXER

T R A N S M I H E R

BEARING A N 0 POWERTRANSFER ASSEMELV

CODERIDECODER

EAR TH SENSOONICAL SUNSHIELD

RADI AL JET

AXIAL JET

EART H SENSORS

OOSTER ADAPTER

SPUN ELECTRONICS STACK

SOLAR ARRAV

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ATLAS CENTAUR LAUNCH VEHICLE

The Atl as Centau r i s N A S A ' s s t a n d a r d l a u nc h v e h i c l efo r i n t e rmed i a t e we i gh t pay l oads .o f E a r t h o r b i t a l , E a r t h s yn ch ro no us an d i n t e r p l a n e t a r ymi s s i ons .I t i s u se d f o r t h e l au n ch

C e nt au r was t h e n a t i o n ' s f i r s t h ig h- en er gy , l i q u i d -hydrogen/ liqu id-oxygen pr op e l le d roc ke t . Developed andl au nc he d u n de r t h e d i r e c t i o n of NASA's L e w i s Research Center ,it became o p e r a t io n a l i n 1966 w i t h t h e launch of Surveyor 1,t h e f i r s t U . S . s p a c e c r a f t t o s o f t - l a n d on t h e Moon's surface.S i n c e t h a t t i m e , b o t h t h e A t l a s b o o s t e r a n d C e nt a ursecond s t a g e have undergone many improvements.t h e veh i c l e combi na t i on can p l ace 4,530 kg ( 1 0 , 0 0 0 lb.) i nl o w E a r t h o r b i t , 1 ,8 8 0 kg (4,150 lb.) i n a synchronous t r a n s -f e r o r b i t and 900 kg ( 2 , 0 0 0 l b . ) o n a n i n t e r p l a n e t a r y

t r a j e c t o r y .f t . ) h i g h, c o n s i s t s o f an A t l a s SLV-3D boos t e r and Cen t au rD-1AR second s tage .newtons (431,300 l b . ) o f t h r u s t a t l i f t o f f u s i n g t w o 822,920-newton (185,000- lb . ) t h ru s t bo os t e r eng i nes , one 266,890-N(60,000-lb.) t h r u s t s u s t a i n e r e n gi n e and two v e r n i e r e n g i n esdeve l op i ng 2,890 N (650 l b . ) t h r u s t ea ch . The two RL-10eng i nes on Cen tau r produce a t o t a l of 133,450 N (30 ,000 l b . )t h r u s t . Both t h e A t l a s a nd t h e Centaur a r e 3.048 m (10 f t . )i n d i am e t er .

A t p r e s e n t ,

The A t l a s Cent au r , s t an d i ng approx i ma t e l y 40.8 m (134The A t l a s b o o s t e r d e v e lo p s 1,920 k i l o -

U n t i l e a r l y 1974, Centaur w a s u s e d e x c l u s i v e l y i ncombi na t i on wi t h t he At l a s boos t e r . Now it i s a l s o u s e dwi t h a T i t an I11 b o o s t e r t o l a un c h h e a v i e r p ay l o a ds i n t oE a rt h o r b i t a nd i n t e r p l a n e t a r y t r a j e c t o r i e s .The A t l a s and t h e Cen t au r ve h i c l e s have been upda tedover t h e y e a rs .c r e a s e d a b o u t 222,400 N (50,000 l b . ) s i n c e i t s d e b u t i n t h es p a c e p ro gram i n t h e e a r l y 1960s.The Centaur D-1AR h a s an i n t e g r a t e d e l e c t r o n i c s ys te mt h a t p er fo rm s a m ajo r r o l e i n c h ec ki ng i t s e l f and o t h e rveh i c l e sys t ems be fo re l aunch and a l s o m a i n t a i n s c o n t r o l of

m ajor e ve n t s a f t e r l i f t o f f . The new Centaur system hand l e snav i ga t i on and gu i dance t a s k s , c o n t r o l s p r e s s u r i z a t i o n andven t i ng , p r op e l l a n t managemen t, t e l em e t r y fo rma t s and t r a ns -m i ss io n a nd i n i t i a t e s v e h i c l e e v e n ts . Most o p e r a t i o n a l needscan be m e t by changing th e computer sof tw are.

T h r u s t o f t h e A t l a s e n g i n e s has been in-

The Centaur D-1AR a l s o incorpora tes a redundant hydrogenp er ox id e a t t i t u d e c o n t r o l s yste m t h a t is t o l e r a n t of a p e r o x i d e"engine o u t " s i t u a t i o n . -more-. _ -


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TYPICAL LAUNCH VEHICLE CHARACTERISTICSL i f t o f f w e ig ht i n c l u d i n g s p a c e c r a f t : 147,885 kg (326,030 l b . )L i f t o f f h e i g h t :Launch Complex: 36A

40.8 m (134 f t . )

W e i g t (wi hprope1 a n t sHeight

T h r u s t

P r o p e l l a n t sP r o p u l s i o n

V e l o c i t y

Guidance

A t l a s Boos te r130,317 kg(287,300 l b . )21.3 m (70 ft.)

1,919 kn(431,300 lb.)a t sea l e v e lLiquid oxygenand RP-1MA-5 system t w o822,921-N (185,000lb.) t h r u s t b oo s t er

Cen taur S tage17,781 kg(39,200 lb.)19.5 m (64 f t . )wi th pay loadf a i r i n g .133,447 N(30,000 lb.)i n vacuum

e n g i n e s , o n e ~266,893-N (60,000-lb.) t h r u s t s u s -t a i n e r en g i n e, two2,891-N (650-lb.)t h r u s t v e r n i e r e n g i n e s .

Liquid oxygen andl i q u i d h y d r o g e n

8,970 kmph(5,574 mph) a tb o o s t e r e n gi n ec u t o f f (BECO) ,12,987 kmph (8,070mph) a t s u s t a i n e ren gin e cu to ff (SECO).Preprogrammed prof i lethrough BECO. Switcht o i n e r t i a l g uidan cef o r s u s t a i n e r p hase.

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Two 66,723-N(15,000-lb. )t h r u s t RL-10e n g i n e s , 12 s m a l lhydrogen peroxidet h r u s t e r s .

33,336 kmph(20,714 mph)a t s p a c e c r a f ts e p a r a t i o n .

I n e r t i a l g u i d a n c e .


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LAUNCH PlU3PARATIONSNASA's John F. Kennedy Space Center and i t s ExpendableV e h i c l e s Di rec t o r a t e p l a y k e y ro l e s i n t h e p r e p ar a t i on andlaunch of Atlas Centaur 39 c a r r y i n g t h e INTELSAT I V - A space-c r a f t i n t o o r b i t .The INTELSAT IV-A s p a c e c r a f t w a s rece ived by KennedyCente r Feb. 9 and underwent p re l i mi na r y checkout i n HangarAM.The A t l a s and Centaur s t ag e s w e r e e r e c t e d on Pad A a tLaunch Complex 36 a t Cape Canaveral A i r F or ce S t a t i o n i n

l a t e February .I n a d d i t i o n t o p r o v i d in g n e c e s sa r y s p a c e c r a f t s u p p o rts e r v i c e s d ur i n g f i n a l l a un ch p r e p a r a t i o n s , t h e E xp end ableV e h i c l e s D ir e c to r a t e i s r e s p o n s i b l e f o r m ati ng t h e s p a c e c r a f tand pa y lo ad f a i r i n g w i t h t h e A t l a s C e n t a u r ro c k e t .

of t h e s p a c e c r a f t w i t h AC-39 w a s scheduled for M w v 1 8 .MatingI n p ro v i d i n g l a u n c h o p e r a t i o n s , Kennedy C e n t e r h a n d l e ss c h e d u l i n g o f t e s t mi l e s t o n e s a n d r e v i e w of d a t a t o a s s u r et h a t t h e l au nc h v e h i c l e h as m e t a l l i t s t e s t requ i rementsand i s ready fo r l aunch.A l l l aunch v e h i c l e a n d p a d o p e ra t i o n s d u r i n g t h elaunch countdown a re conducted f rom the blockhouse a tComplex 3 6 by a j o i n t g o v e rn me n t - i n d u s t ry t e a m .

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TY PIC AL LAUNCH SEQUENCE F O R I N T E L S A T I V - A

F l i g h t E v e n t s

L i f t o f fBECOB o o s t e r j e t t i s o nI n s u l a t i o n pa ne lj etti onSECO/VECOC e n t a u r separa t i onC e n t a u r MES ( 1 )N o s e f a i r i n g j e t t i s o nC e n t a u r MECO ( 1 )C e n t a u r MES ( 2 )C e n t a u r MECO ( 2 )Spacecraf t sepa ra t ionR e o r i e n t C e n t a u rS t a r t b l o wdownE n d blowdown

Program E a r t h R e l a t i v eT i m e V e l o c i t y R a n g e A1 i u d eSeconds Km/hr Mph Kilometers /Miles Ki lometers /Miles0 0 0 0 0 0 01 3 9 . 3 8 , 97 0 5 , 5 7 4 8 0 . 1 4 9 . 8 5 7 3 5 .41 4 2 . 4 9 , 0 6 9 5 , 6 3 5 8 7 . 2 5 4 . 2 6 0 . 1 3 7 .31 8 4 . 3 1 0 , 2 8 5 6 , 3 9 1 1 9 1 . 5 8 9 . 9 9 7 . 7 6 0 .7

2 4 7 . 1 1 2 , 9 8 8 8 , 0 7 02 4 9 . 0 1 2 , 9 9 0 8 , 0 7 22 5 8 . 6 1 2 , 9 3 4 8 , 0 3 72 7 0 . 6 1 3 , 1 4 1 8 , 16 56 2 0 . 6 2 8 , 2 9 1 7, 1 61 , 4 9 3 . 0 2 6 , 4 2 1 6 , 9 21 , 5 7 8 . 3 3 3 , 6 6 2 1, 4 31 , 7 1 3 . 3 3 3 ,3 3 6 2 0 , 7 1 41 , 7 1 8 . 31 , 8 8 3 . 32 , 1 3 3 . 3

3 8 3 . 8 2 3 8 . 53 9 0 . 2 2 4 2 . 54 2 3 . 5 2 6 3 . 25 4 7 . 7 3 4 0 . 32 ,274 .4 1 ,413 .28 ,604 .9 5 I 3 4 6 . 99 ,245 .5 5 ,744 .91 0, 6 0 . 9 6 , 4 3 8 . 0

1 4 4 . 31 4 5 . 61 5 1 . 71 5 8 . 61 8 9 . 25 5 8 . 26 2 6 . 18 0 4 . 6

89.790 .594 .39 8 . 51 1 7 . 53 4 6 .389 .0500.0


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-11-NASA TEAM

NASA Headquar te rsJohn F. Yardley

Joseph B. MahonF. R. Schmidt

bewis Research C e n t e rD r . B r u c e T. LundinAndrew J. S t o f a nRichard E. Orzechowski

Kennedy Space C e n t e rL e e R. Sc h e re rD r . Walter J. Kapryan

George F. PageJohn G o s s e t tC. A. TerhuneJames N. McKnight

Assoc ia te A d mi n i s t r a t o rf o r S pace F l i g h tD i r e c t o r of Launch Vehicleand Propu l s ion ProgramsManager, A t l a s Cent au r

D ir e c to rD i r e c to r of Launch VehiclesINTELSAT Miss ion Pro jec tEngineer

DirectorD i rec t o r , Space Vehic le sOpera t ionsD i r e c t o r , Expendable VehiclesManager, C e n t a u r Opera t ionsChief Engineer , A t l a s Cent au rSp a c e c ra f t C o o rd i n a t o r

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INTELSAT TEAM

COMSATD r . Joseph V . CharykEugene T. J i l g

A l l a n M, McCaski l l

H u g h e s A i r c r a f t C o .A. T. OwensDon Thompson

P r e s i d e n tA s s i s t a n t V i c e P r e s i d e n t ,E n g i n e e r i n gManager, Launch V eh ic leSystems

INTELSAT IV-A P r o j e c t ManagerINTELSAT I V - A S p a c e c r a f tManager

CONTRACTORS

G e n e r a l Dynamics/ConvairSan D i e g o , C a l i f . A t l a s C e n t a u r launchv e h i c l eHoneywel l Aerospace D i v i s i o n C e n t a u r guidance i n e r t i a lS t . P e t e r s b u r g , F l a . measurement groupP r a t t and WhitneyWest P a l m Beach, F l a ,TeledyneN o r t h r i d g e , C a l i f .

C e n t a u r RL-10 e n g i n e sD i g i t a l c o m p u t e r unit /PCMt e l e m e t r y

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Intelsat IV-A Press Kit 051877

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