GMS Press Kit

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NASA NewsNational Aeronautics andSpace AdministrationWashington. D C 20546AC 202 755-8370

PressKitR E L E A S E N O : 77-110

Contents

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ForRelease I M M E D I A T E

G E N E R A L F E L E A S E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .S P A C E C R A F T ( G M S ) C H A R A C T E R I S T I C S . . . . . . . . . . . . . . . . . .V I S S R M I S S I O N . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .GMS LA UN CH P R O F I L E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .D E L T A L A U N C H V E H I C L E . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .S T R A I G H T E I G H T D E L TA F A C T S AND F I G U R E S . . . . . . . . . . . .L A U N C H O P E R A T I O N S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .T Y P I C A L L AU NC H S E Q U E N C E F O R GMS /DELTA 132.........D E LT A 1 3 2 / G M S T E A M . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C O N T R A C T O R S . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1-78-99-1010-111213-14151617-1818

Mailed:J u n e 7, 1977


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C N e wNational Aeronautics andSpace Admin s ra ionWashington.DC 20546AC 202 755 -8370

David G a r r e t tH e a d q u a r t e r s , W a s h i n g t o n , D . C .(Phone : 2 0 2 / 7 5 5- 3 0 9 0 1

Fc lr Release

IMMEDIATE

James LynchG od da rd S p a c e F l i g h t C e n t e r , S r e e n b e l t , Md.(Phone : 3 0 1/9 8 2 -6 2 5 5 )

RELEASE NO : 77-110

FIRST JAPANESE WEATHER SATELLITE T O BE LAUNCHED

An American rocke t , NASA's D e l t a 2 9 1 4 , w i l l l a u n c ht h e J ap a n es e G o ve rn me nt 's f i r s t m e t e o r o l o g i c a l s a t e l l i t ei n t o s yn c hr o no u s o r b i t f ro m Cape C a n a v e r al , F l a . , noe a r l i e r t h a n J u l y 1 4 , 1977 .

The G eo gy nc hr on ou s M e t e o r o l o g i c a l S a t e l l i t e ( G M S )w ei ghs 2 8 1 k i l o g r a m s ( 6 2 0 p o un d s) a nd r e p r e s e n t s a m a j o rs c i e n t i f i c a t t e m p t t o i mprove we a th e r p r e d i c t i o n s o v erm i l l i o n s o f s q u a re m i l e s i n t h e Weste rn P a c i f i c Ocean.

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GMS is a satellite program under the direction of theNational Space Development Agency of Japan (NASDA). TheDelta launch vehicle project i s managed for NASA's Officeof Space Flight by the Goddard Space Flight Center, Greenbelt,Md .

From its "meteorological arena" 3 5 , 8 0 0 kilometers( 2 2 , 2 5 0 miles) i n s p a c e , GMS w i l l i d e n t i f y , p i n p o i n t andphotograph every major weather pattern from Hawaii to Pakistan.The satellite's "cameras" will take a cloud cover photo ofapproximately one third of the world every 30 minutes, 24hours a day to help alert meteorologists to potential perilousstorms over the Pacific. The satellite will be positionedover the equator directly south of Tokyo at 140 degrees Eastlongitude.

Mission objectives of the GMS are to observe cataclysmicevents such as hurricanes, typhoons and regional weatherphenomena; day and night observation of regional weather;relay meteorological observation data from surface collectionpoints (ships, buoys and weather stations) to the central pro-cessing center in Japan; and to transmit processed imagingdata for facsimile reproduction at distribution points inthe Western Pacific area.

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On b o a r d GMS i s a V i s a b l e I n f r a r e d S p in S canRadiometer ( V I S S R ) , c a p a b l e of m aking h i g h l y a c c u r a t ep i c t u r e s of t h e E a r t h ' s c l ou d c o v er i n d a y l i g h t an di n t o t a l da rkness . The images, which can be t r a n s -m i t t e d t o E a r t h e ve ry 30 m i n u t e s , w i l l e n a b l em e t e o r o l o g i s t s t o i d e n t i f y , m o n i t or and t r a c k s e v e r es t o r m s, heavy r a i n f a l l o r c l o u d b u r s t s , f l o o d s andtyphoons .

GMS a l s o w i l l c a r r y a Space Envi ronment Moni tor(SEM) t o m o ni to r e n e r g e t i c p a r t i c l e a c t i v i t y e m anatedby t h e Sun. Extreme s o l a r a c t i v i t y can a f f e c t E a r t hcommunicat ions. The SEM m o n i t o r s s o l a r p r o t o n s ,a l p h a p a r t i c l e s a nd s o l a r e l e c t r o n s .

A s o l i d m oto r a t t a c h e d t o t h e GMS s p a c e c r a f tw i l l b e f i r e d a b ou t 27 h ou rs a f t e r l i f t - o f f t o i n j e c tt h e s p a c e c r a f t i n t o i t s f i n a l p o s i t i o n above t h ee q u a t o r .

The N A S D A ground s t a t i o n a t Okinawa and N A S A ' sSpace Track ing and Data N e t w o r k ( S T D N ) s t a t i o n a tRosman, N . C . , w i l l p r o v i de ne a r- c on t in u o us t r a n s f e ro r b i t m o n i to r in g o f t h e s p a c e c r a f t .

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The NASDA ground station at Masuda, Japan, plusother stations in the NASA S T D N network (Orroral Valley,Australia and Santiago, Chile) provide backup capabilityin monitoring the transfer orbit.

After GMS goes into its preliminary orbit fromCape Canaveral, all control and monitoring functionswill be performed from the GMS Mission Control Centerat Hughes Aircraft Company, El Segundo, Calif.

The cylindrically-shaped weather satellite isthe first of several "weather watchers" to be launchedby several countries in an attempt to improve weatherpredictions for extended periods on a global basis.This international weather satellite program is amajor part of the Global Atmospheric Research Project(GARP). :;ARP is sponsored by the InternationalCouncil of Scientific Unions and the World MeteorologicalOrganization.

Other countries contribgting weather satellitesto the GARP Program include the European Space Agency(ESA), the Soviet Union and the U . 2 .

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In addition to those countries participating inthe satellite portion of GARP, 3pproximately 145countries also will make contributions to the world-wide weather effort by taking daily surface andatmospheric measurements in their respective areas.

All of the data will be sent to Central DataCenters in Moscow and Washington, D.C. Current planningcalls for the program to be in full operation byDecember of 1978.

The Delta rocket is managed for NASA's Officeof Space Flight by the Goddard Space Flight Center.NASA's Kennedy Space Center, Fla., Expen8ableLaunch Vehicles Division is responsible to Goddard f o rmanagement of launch operations. GMS is a meteorologicalsatellite program of the National Space DevelopmentAgency of Japan (NASDA). NASDA is responsible for thesatellite's procurement, launch and initial checkout.

Later, NASDA will share joint responsibilitywith the Japanses Meteorological Agency for control anduse of the GMS during its planned five-year missionlifetime.

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GMS has been designed, developed and manufacturedby Hughes Aircraft Co. under subcontract to the NipponElectric Co., Ltd. of Japan. Xughes also developed thesatellite's camera system. The SEM was designed andbuilt by Nippon Electric C o . Prime contractor f o r theDelta launch vehicle is McDonnell Douglas AstronauticsCo. Huntington Beach, Calif.

The U.S. is reimbursed by the Japanese Governmentf o r costs associated with providing Delta launchsupport.

(END O F GENERAL RELEASE. BACKGROUND INFORMATION FOLLOWS.)

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SPACECRAFT ( G M S ) CHARACTERISTICS

GMS i s c y l i n d r i c a l i n s h a pe , 3 meter s ( 9 f e e t )t a l l , w e i g h s 2 8 0 k i l o g r a m s ( 6 2 q p o un d s) i n s y n c h r o n ou so r b i t a nd h as a d e s ig n e d l i f e t i m e o f m ore t h a n f i v e y e a r s .L i f e t i m e i s l i m i t e d p r i m a r i l y by t h e amount o f h y d r a z i n ef u e l t h a t c an be c a r r i e d a bo ar d t o p ro v i de c o n t r o l i n o r b i t .F u l l r e d un d an c y o f a l l m i s s i o n - c r i t i c a l f u n c t i o n s i s pro -v i d e d t o e n su r e e l e c t r o n i c s l i f e t i m e s s i g n i f i c a n t l y i ne x c e s s o f f i v e y e a r s . The s o l a r p a n e l p ow er o f 2 2 5 w a t t si n c l u d e s a p p ro x i m at e ly 30 w a t t s m a r g i n a t t h e e nd of f i v ey e a r s .D o m i n a n t f e a t u r e s of t h e sD a c e c r a f t a r e a l a r g es un sh ad e f o r t h e V I S S R camera a p e r t u r e , a 216-cm (7 .1 f t . )d i a m e t e r c y l i n d r i c a l s o l a r a r r a y an d a n S band/UHF despuna n t e n n a .Image c a p a b i l i t y of t h e s a t e l l i t e i s p r o v i d e d b yt h e VISSR, wh ich i s d e r i v e d f r om t h e s p ac e -p r ov e d U n i t e dS t a t e s S y n c h r o n o u s M e t e o r o l o g i c a l S a t e l l i t e i n s t r u m e n ta l r e a d y i n o r b i t . The VISSR p r o v i d e s s i m u l t a n e o u so p e r a t i o n o f f o u r v i s i b l e l i g h t d e t e c t o r s and o ne i n f r a r e dd e t e c t o r .T he SEM i n s t r u m e n t , d e s i g n e d a n d c o n s t r u c t e d b yNippon E l e c t r i c C o . , i s a new d e s i g n c o n t a i n i n g f i v ed e t e c t o r s f o r m ult i- mo de s o l a r p a r t i c l e c ou n t in g .M i c r om i n ia t u r i za t io n o f e l e c t r o n i c s f o r t h ec om m un ic at io ns s u b- s ys te m r e p e a t e r d e s i g n f o r S band andUHF o p e r a t i o n i s a c h i e v e d by u s i n g t h e l a t e s t microwavei n t e g r a t e d c i r c u i t d e s i g n t e c h n i qu e s .A u n i q u e t h r e e c h an n el n o n co n t ac t in g r o t a r y j o i n tc o up l e s s i g n a l s f o r t h e s p i n n i n g s p a c e c r a f t e l e c t r o n i c st o t h e E a r t h - p o i n t e d ( d e s pu n ) a n t e n n a s . T he U H F h e l i xa n t e n n a co mb in es h i g h g a i n a nd l i g h t w e i g h t c o n s t r u c t i o n .The S-band p a r a b o l i c r e f l e c t o r a n te n n a f e a t u r e s a s p e c i a l l yd e s i g n e d r i m a nd d e f o c u s e d f e e d t o m ax im iz e p e r f o r m a n c e .

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Design of the VHF communication subsystem for tele-metry and command monitoring is compatible with the GoddardRange and Range Rate (GRARR) system, which allows use ofNA SA ' s STDN (worldwide tracking n e t w o r k ) telemetry, t r a c k i n gand command stations during launch and transfer orbit.

The control subsystem is similar to the flight-proven Intelsat-IV control subsystem but with very lowjitter, to achieve precision images for the VISSR mission.

In addition, flight-proven space qualified designapproaches have been used throughout the various othersubsystems to enhance system reliability and assure con-fidence in meeting the satellite objectives.

VISSR MISSION

The Visible Infrared Spin Scan Radiometer (VISSR)aboard the GMS is used to image the Earth in both visibleand infrared spectra. Visible spectrum information con-sists of reflected sunlight measurements obtained whenthe Earth's surface visible to the VISSR is illuminated bythe Sun. This information is valuable for determiningcloud cover, wind velocity and other information deducedfrom these parameters.

The infrared spectrum is scanned in the long waveinfrared region (10 to 12 microns), where the informationobtained from the Earth is the amount of heat radiationbelow the principal energy spectrum of the Sun. Since itcontains very little reflected radiation, the infraredinformation is available day and night. The infraredresponse to various Earth atmospheric conditions differssignificantly from the visible response an? thus is avaluable tool for meteorological analysis.

Extremely sensitive infrared detectors are providedwhich operate at temperatures about 95 degrees K ( - 1 7 8degrees C). A unique radiation cooler cools the detectorsby radiating heat into cold space.

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The GM S VISSR g e n e r a t e s an E a r t h i m ag e by u s i n g t h es p i n n i n g m o t i o n of t h e s a t e l l i t e f o r s c a n n in g f rom w e s t t oe a s t a nd u s i n g m o t o r - a c t u a t e d m i r r o r s t e p p i n g f o r s c a nn i ngn o r t h t o s o u t h . S i n c e e a c h n o r t h -s o u t h s c a n s t e p i s 140m i c r o r a d i a n s , 2 , 5 0 0 s t e p s a r e r e q u i r e d t o s c a n a r e g i o n20 d e g r e e s i n e l e v a t i o n . A 20-degree window of az imuth ande l e v a t i o n ( t h e E a r t h s u b te n d s a n a n g l e o f a p p r o x i m a t e l y1 7 . 5 d e g r e e s ) c a n b e s c an n e d i n a p p r o x i m a t e l y 2 5 m i n u t e s .R e s o l u t i o n t o 5 km (1 6 ,0 00 f t . ) s p r o v i d ed by a n o p t i c a l t e l e -s c o p e w i t h a p p r o x i m a t e l y 1 4 0 m i c r o r ad i a n s i n s t a n t a n e o u sf i e l d o f v i ew ( I F O V ) . The f o u r v i s i b l e c h a nn e ls a r e s c a n n e ds i m u l t a n e o u s l y w i t h e ac h i n f r a r e d s c a n , w h i c h p r o v i d e s1 .2 5 km ( 4 , 1 0 0 f t . ) r e s o l u t i o n i n t h e v i s i b l e ch an ne ls .

A s t h e s a t e l l i t e s p i n s , b o t h i n f r a r e d d e t e c t o r sa n d t h e t wo s e t s of v i s i b l e d e t e c t o r s a r e s wep t o v er t h es a m e E a r t h t r a c k , p r o v i d i n g re d un d an t s i g n a l s , i n c r e a s i n gr e l i a b i l i t y and p e r m i t t i n g c o r r e l a t i o n o f i n f r a r e d andv i s i b l e im age d a t a . The r e l a t i v e a r ra n ge m en t o f t h e i n -f r a r e d and v i s i b l e s pe ct r um d e t e c t o r s i n t h e VISSR f o c a lp l a n e , w he re t h e im ag e o f t h e E a r t h i s fo rm ed , i s showni n t h e f i g u r e s .

D e t e c to r s i g n a l s p a s s t h ro u gh t h e f u l l re d un d an tVISSR e l e c t r o n i c s t o t h e t wo VISSR m u l t i p l e x e r m o d u l a t o r s .E i t h e r r e du n d an t VI SSR mu l t i p l ex er mo du la to r may be commandedt o enc od e e i t h e r o f t h e VISSR e l e c t r o n i c s r e du nd an t s i g n a l sfor t r a n s m i s s i o n t o E a r t h by way of t h e r e d u n d a n t c o mm u n ic a ti onc h a n n e l s . Ground p r o c e s s i n g of t h e d a t a p ro v id e d t h ew e at he r p i c t u r e .

GM S L A U N C H P R O F I L E

The f i r s t two s t a g e s of t h e D e l t a 2 9 1 4 p l a c e t h es p a c e c r a f t i n a low a l t i t u d e p a r k in g o r b i t 1 7 4 km ( 1 0 8 m i . )a t 2 7 . 2 d e g re e s i n c l i n a t i o n near t h e f i r s t e q u a t o r i a lc r o s s i n g . S pi nu p t o 5 0 rpm, f o l lo w e d by i n j e c t i o n i n t oa t r a n s f e r o r b i t u s in g t h e D e l t a t h i r d s t a g e , o c cu r s a f t e ra few m in u te s i n p a r k i ng o r b i t .I f s p a c e c r a f t o p e r a t i o n i s n o r m a l , t h e GMS w i l l b e

b o o s t ed i n t o s yn ch ro no us o r b i t when t h e s p a c e c r a f t a p og eemotor i s f i r e d a t t h e t h i r d ap og ee ( a p pr o x im a t el y 2 7 h o u r sa f t e r l i f t - o f f ) . F o r a nom ina l t r a n s f e r o r b i t , t h es u b s a t e l l i t e l o n g i t u d e a t t h i s t i m e i s 1 4 1 d e g r e e s E , t h a ti s , o n l y 1 d eg re e from t h e f i n a l o r b i t a l s t a t i o n .

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Following burnout of the Delta third stage andspacecraft separation, the G MS will be in transfer orbit.Transfer orbit is a highly elliptical, inclined ( 2 7 . 2degrees) orbit, with a perigee altitude of 174 km (108mi.) and an apogee of 8 7 0 km (540 mi.) above synchronousaltitude. When the spacecraft motor is fired at apogee,the orbit will be circularized and the launch inclinationremoved. The transfer orbit third apogee occurs nearestthe spacecraft's final orbit position of 140 degrees Elongitude (north of Australia) and, for this reason, isthe optimum time for aporjee motor firing, to minimizetime and expenditure of hydrazine (S2H4) propellantnecessary to arrive on final station.

During transfer orbit the spacecraft with apogeemotor attached i s ufistable about its principal (spin)axis. To minimize nutation buildup about this spin axis,an active nutation control system is turned on when thespacecraft separates frcm the Delta third stage. Precisecontrol of thruster firings by this active nutation controlsystem maintains spacecraft stability about the spin axis.

Before apogee motor firing, the spacecraft spinaxis must be reoriented to the correct attitude. Re-orientation will be started as soon as possible afterdetermination of injection attitude and subsequent apogeemotor firing attitude. Apogee motor firing attitude willbe aligned to inject the spacecraft into near-synchronousdrift orbit for arrival on station in less than two weeks.

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DELTA LAUNCH VEHICLE

F i r s t S t a g eThe f i r s t s t a g e i s a McDonnel l Dou glas mod i f i ed Thorb o o s t e r i n c o r p o r a t i n g n in e C a s t o r I1 s t r a p - o n T h io k o l s o l i df u e l r o c k e t motors. T h e b o o s t e r i s powered by a Rocketdynee n g i n e u s i n g l i q u i d ox yg en an d l i q u i d h y d ro ca rb o n p r o p e l l a n t s .The main e n g i n e i s gimbal-mounted t o p r o v i d e p i t c h a nd yawc o n t r o l f rom l i f t o f f t o main e n g i ne c u t o f f

S e c o n d S t a g e( M E C O ) .

The s e c o n d s t a g e i s powered by a TRW l i q u i d - f u e l ,p r e s s u r e -f e d e n g i ne t h a t a l s o i s g im ba l- mo un te d t o p r o v i d ep i t c h a n d yaw c o n t r o l t h r o u gh t h e s ec on d s t a g e bu rn .n i t r o g e n g a s s y st em u s es e i g h t f i x e d n o z z l e s f o r r o l l c o n t r o ld u r i n g powered a nd c o a s t f l i g h t , a s w e l l a s p i t c h a n d yawc o n t r o l d u r in g c o a s t a nd a f t e r s ec on d s t a g e c u t o f f s . Twof i x e d n o z z l e s , f e d by t h e p r o p e l l a n t t a n k , h e l iu m p r e s s u r i z a -t i o n s ys te m , p r o v i d e r e t r o t h r u s t a f t e r t h i r d s t a g e s e p a ra t io n .F i f t y - f o u r m i n u t es a f t e r s p a c e c r a f t s e p a r a t i o n , t h e s eco nds t a g e w i l l be r e i g n i t e d f o r a 10-second burn .b u r n w i l l b e c o l l e c t e d f o r s t u d i e s r e l a t e d t o f u t u r e D e l t am i s s i o n s .

A

Data on t h i s

T h i r d S t a q eThe t h i r d s t a g e i s t h e TE-3-64-4 s p i n - s t a b i l i z e d , s o l i d

The f i r i n g of e i g h t s o l i d pr o-p r o p e l l a n t T h i ok o l mo to r.mounted t o t h e s ec on d s t a g e .p e l l a n t r o c k e t s f i x e d t o t h e s p i n t a b l e a c co m pl is he s sp i nu po f t h e t h i r d s t a g e s p a c e c r a f t a sse mb ly .I n j e c t i o n I n t o S yn ch ro no us O r b i t

I t i s s ec ur ed i n t h e s p i n t a b l e

The D e l t a v e h i c l e w i l l i n j e c t GM S i n t o a t r a n s f e r o r b i th a v i n g a n a p o g e e of 36 ,65 5 km ( 2 2 , 7 7 6 m i . ) , a p e r i g e e o f 1 7 4km (108 m i . ) and i n c l i n a t i o n of 27 .2 de g re es . NASA's Space-f l i g h t T ra ck in g an d D a t a N e t w o r k w i l l p r o v i d e t e l e m e t r y ,t r a c k i n g and r a n gi n g s u p p o r t u n t i l t h e s p a c e c r a f t i s p l a c e di n i t s f i n a l s yn ch ro no us o r b i t a t 1 4 0 d e g r e e s E.c o n t r o l , t r a c k i n g and d a t a a n a l y s i s a r e t h e r e s p o n s i b i l i t i e so f NASDA an d Hu qh es A i r c r a f t C o .

Command,

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STRAIGHT EIGHT DELTA FACTS AND FIGURES

Height: 35.4 m (116 ft.) including shroudMaximum Diameter: 2.4 m (8 ft.) without attachedsolidsLiftoff Weight: 131,895 kg (293,100 I b . )Liftoff Thrust: 1,765,315 newtons (396,700 lb.)including strap-on solids

First Stage(Liquid Only) consists of an extended long-tank Thor,

Theproduced by McDonnell Douglas.by the Rocketdyne Division of Rockwell International.stage has the following characteristics:

The RS-27 engines are produced

Diameter: 2 .4 m ( 8 ft.)Height: 21.3 m (70 ft.)Propellants: R J - 1 kerosene as the fuel and liquidoxygen (LOX) as the oxidizerThrust: 912,000 N (205,000 lb.)Burning Time: About 3.48 minutesWeight: About 84,600 kg (185,000 lb.) excludingstrap-on solidsStrap-on solids consist of nine TMX-354-5/Castor I1solid-propellant rockets produced by the Thiokol Chemical

Corp., with the following features:Diameter: 0.8 m (31 in.)Height: 7 m (23.5 ft.)Total Weight: 40,300 kg (88,650 1b. I for nine4 , 4 7 5 kg ( 9,850 lb.) for eachThrust: 2,083,000 N (468,000 1h.I for nine231,400 N ( 52,000 lb.) for eachBurning Time: 3 8 seconds

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Second StageProduced by McDonnell Douglas Astronautics Co., using

a TRW TR-201 rocket engine. Major contractors for the vehicleinertial guidance system located on the second stage areHamilton Standard, Teledyne and Delco.

Propellants: Liquid, consists of Aerozene 5 0 for thefuel and nitrogen tetroxide (N 0 ) forthe oxidizer. 2 4Diameter: 1.5 m (5 ft.) plus 2.4 m (8 ft.) attachedringHeight: 6.4 m (21 ft.)Weight: 6,118 kg (13,596 lb.)Thrust: About 42,943 N (9,650 l b . )Total Burning Time: 335 seconds

Third Stage. Thiokol Chemical Corp. TE-364-4 motor.Propellant: SolidHeight: 1.4 m (4.5 ft.)Diameter: 1 m (3 ft.)Weight: 1,152 kg (2,560 lb.)Thrust: 61,855 N (13,900 1b.IBurning Time: 44 seconds

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LAUNCH OPERATIONSThe Kennedy Space C en te r s Expendable Veh ic le s Direc-

t o r a t e p l a y s a key r o l e i n t h e p r e p a r a t i o n and l a u nc h oft h e t h r u s t - a u g m e n t e d Del ta r o c k e t c a r r y i n g GMS.D e l t a 1 3 2 w i l l be l aunched f r o m Pad B , s o u t h e r n m o s t oft h e t w o l a u n c h p a d s a t Complex 1 7 , Cape Canavera l A i r ForceS t a t i o n , F l a .The D e l t a f i r s t s t a g e and i n t e r s t a q e a re s c h e d u le d t ob e e r e c t e d on Pad B J u n e 1 8. The n i n e s o l i d s t r a p - o n r o c k e tm o t o r s w i l l b e mo un te d i n p l a c e a r ou n d t h e b a s e of t h e f i r s ts t a g e J u ne 20. The second s t a ge w i l l b e e r e c t e d J u ne 21.The GMS s p a c e c r a f t w a s r e c e i v e d by K SC J u n e 7 and under-went i n i t i a l p r o ce s s i n g i n B u i l di n g A E.moved t o t h e Del ta S p i n T e s t F a c i l i t y and mated w i t h t h eD e l t a t h i r d s t a g e J u l y 1.w i l l be moved t o Pad B and mated wi th Del t a 1 3 2 J u l y 6 . Thep a yl oa d f a i r i n g , t o p r o t e c t t h e s p a c e c r a f t on i t s f l i g h tt h r o u g h t h e a t m o s p h e r e , i s t o b e p u t i n p l a c e J u l y 11.

L a t e r it w i l l beThe t h i r d s t a g e / s p a c e c r a f t a s se mb ly

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TYPICAL LAUNCH SEQUENCE FOR GMS/DELTA 132Altitude Velocity

Event Time Kilometers/Miles Km/Hr MPhLiftoffSix Solid Motor BurnoutThree Solid Motor IgnitionThree Solid Motor BurnoutNine Solid Motor JettisonMain Engine Cutoff (MECO)First/Second StageSeparationSecond Stage IgnitionFairing JettisonSecond Stage Cutoff (SECO-1)Restart Second Stage

Second Stage Cutoff (SECO-11)Third Stage SpinupSecond/Third Stage SeparationThird Ctage IgnitionThird Stage BurnoutThird Stage/SpacecraftSeparation

0 sec.38 sec.39 sec.1 min. 17 sec.1 min. 27 sec.3 min. 48 sec.3 min. 56 sec.

4 min. 1 sec.4 min. 45 sec.8 min. 57 sec.21 min. 17 sec.21 min. 24 sec.22 min. 14 sec.22 min. 16 sec.22 min. 58 sec.23 min. 42 sec.24 min. 55 sec.

06621269298

101125160169169171171173174197

04413165761

637899105105106106107108122

01,3801,3802,8883 6617 7117 97

17 7318 1226 75326,73127 10327 9527 9527,08535 8135,405

08578571 7951,96811,10411 20

11 10611 6516 2416 1016 4116 3616 , 3616,83022 4722,000


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DELTA 132/GMS TEAM

NASA H e a d q u a r t e r sJohn F. Y a r d l e y

J o s e p h B. Mahon

Pe te r T. E a t o nGoddard SDace Flicrht C e n t e r

Assoc ia te A d m i n i s t r a t o rf o r S pace F l i g h t

Di r e c t o r of Expendab leLaunch Vehicle ProgramsManager, Del ta Program

D r . R o b e r t S. CooperD r . W i l l i a m C . S c h n e i d e r

C h a r l e s R. GunnW i l l i a m R. R u s s e l l

R o b e r t G o s s

W i l l i a m R. Burrowbr idge

Edward L o w eJohn WalkerKennedy Space C e n t e rL e e R. S c h e r e rD r . Walter J . Kapryan

D i r e c t o rDirec to r o f P r o j e c tManagementD e1 a P r o j e c t ManagerDeputy D e l t a P r o j e c tManager , Techn ica lC h i e f , Miss ion Ana lys i sa nd I n t e g r a t i o n B r an ch ,D e l t a P r o j e c t O f f i ce --NASA Manager fo r GM S

D e l t a Miss ion I n t e g r a t i o nManagerNetwork S up po rt ManagerNetwork Opera t ions Manager

D i r e c t o rD i r e c t o r , S p a c e V e h i c l e sO p e r a t i o n s

George F. Page D i r e c t o r , E x p e n d a b l e V e h ic l e sHugh A. Weston, J r. C h i e f , De l t a O p e r a t i o n s

B e r t L. G r e n v i l l e Complex 1 7 Opera t ions ManagerEdmund Chaffin S p a c e c r a f t C o o r d i n a t or

D i v i s i o n

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NASDAHideo ShimaA k i y o s h i MatsuuraD r . Yashi ro Kuroda

Masayosh i N o j i m aAkira KubozonoYoshitaha KuriharaKazuo Watanabe

P r e s i d e n tV i c e P r e s i d e n tS p e c i a l A s s i s t a n t t ot h e P r e s i d e n tE x e c u t i v e Di r e c t o rS y s t e m P l a n n in g D e p a r tm e n tApplications SatelliteDesign GroupGMS P r o j e c t Manager

McDonnell DouglasA s t r o n a u t i c s C o .H u n t i n g t o n B e ac h, C a l i f .

CONTRACTORS

Nippon E l e c t r i c Co. , L td .Yokohama, JapanH u g h e s A i r c r a f t C o .L o s A n g e l e s , C a l i f .

D e l t a l a u n c h v e h i c l e

S p a c e c r a f t a nd SEM

S p a c e c r a f t a nd cameras y s t e m s

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Documents

GMS Press Kit