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NASA NewsNational Aeronautlcs andSpace Administration
Washington.D C 20546AC 202 755 -8370
For Release I M M E D I A T E
PressKit Project OTSIESA
R E L E A S E N O : 77-168
Contents
G E N E R A L R E L E A S E . . .................................. 1-5
D E L T A L A U N C H V E H I C L E ( 3 9 1 4 ) ........................ 6
D E L T A 3 9 1 4 F A C T S AND F I G U R E S . . . . . . . . . . . . . . . . . . . . . . . 7- 8
L A U N C H O P E R A T I O N S . . ................................ 9
L A U N C H S E Q U E N C E F O R O T S . . .......................... 10
D E L T A / O T S L A U NC H T E A M . .. ........................... 1 1 - 1 2
C O N T R A C T O R S ........................................ 12
Mailed:
August 10, 1977
. . .
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c
N,ition,tl Aeronautics and
S p m ?Admlnistratlon
Washington DC 20546AC, 202 755 8370
Dav id G a r r e t t
Headquarters, Washington, D.C.
(Phone: 2 0 2 / 7 5 5 - 3 0 9 0 )
Joseph McRoberts
Goddard Space Flight Center, Greenbelt, Md.
(Phone: 3 0 1 / 9 8 2 - 4 9 5 5 )
RELEASE NO: 77-168
NASA TO LAUNCH TEST SATELLITE FOR EUROPEAN COMMUNICATIONS
The forerunner of a European operational communications
satellite network of the 1 9 8 0 s is scheduled to be launched
by NASA for the European Space Agency (ESA) no earlier than
Sept. 9 from Cape Canaveral, Fla., on a Delta 3 9 1 4 launch
vehicle.
This new type of communications spacecraft is one of two
experimental models built by ESA to test the satellite's per-
formance in orbit. Its operational descendents are expected
to provide satellite links in the 1980s for routing portions
of the intra-European telephone, telegraph and telex traffic
as well as television relay for Western Europe.
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August 10, 1 9 7 7
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Called Orbital Test Satellite ( O T S ) , the new spacecraft
is built on a modular concept for easy adaptability, thus
reducing costs as new requirements or technological advances
appear.
Initially, O T S will provide experimental and pre-operational
traffic capability for one or two television channels and two
to five thousand telephone circuits. Coverage from its on-
station position at 10 degrees E. longitude above the equator
over West Africa will include the whole of Western Europe,
the Middle East, North Africa, the Azores, Canary Islands,
Madeira and Iceland.
The OTS satellite is expected to be valuable for such
difficult communications tasks as establishing communications
links with areas of difficult access such as off shore oil
rigs. Oil exploration in Europe is now limited mainly to
work in the North Sea, but is expected to extend throughout
the European continental shelf. Other potential applications
are educational television, teleconferencing and radio
broadcasting.
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The operational system calls for satellite transmission
of from a third to half of the telephone traffic between
West European capitals located more than 800 kilometers
(496 miles) apart during the 1980s. The system is planned
to carry 5,000 phone circuits in 1980, increasing to 20,000
in 1990.
There will be at least one large Earth station handling
telephone traffic and television transmissions in each country
requiring satellite services. ESA eventually plans to have
a number of Earth stations to handle television transmissions
exclusively in North Africa and the Middle East.
OTS components include a payload module, a service module
and an antenna assembly. The solar array folds out from the
sides. By arranging components of the spacecraft in separate
compartments alternate payloads can be put in place easily
and economically.
In keeping with the modular concept, the spacecraft's
appearance is box-like, with oblique ends. It weighs 865
kilograms (1,845 pounds),including Apogee Boost MotorCABM)
at launch, is 1.62 meters (7.2 feet) wide, 2.39 m (6.9 ft.)
high and 9.26 m (28.2 ft.) across with deployed solar array.
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I t w i l l be i n j e c t e d i n t o a s yn ch ro no us t r a n s f e r o r b i t
of ab o ut 38,275 km (22 ,54 0 m i . ) ap og ee , 185 km (11 5 m i . )
p e r i g e e a n d 2 7 . 4 d e g re e i n c l i n a t i o n . On t h e f i f t h ap oge e
r o u g h l y 4 0 h o u rs a f t e r l au n c h, when t h e s p a c e c r a f t i s o v e r
t h e m i d - A t la n t i c, t h e s p a c e c r a f t a po ge e k i c k mo to r w i l l be
f i r e d t o c i r c u l a r i z e t h e o r b i t . F r o m t h e re i t w i l l be
a l lowed t o d r i f t s e v e r a l de gr ee s p e r d ay u n t i l it a r r i v e s
a t i t s o n - s ta t i on p o s i t i o n a t 1 0 d e g r e e s E . l o n g i t u d e a b o v e
t h e equa tor .
T h e apogee k i c k m o t o r f i r i n g w i l l be c o n t r o l l e d f r o m
t h e E u ro pe an S p a c e O p e r a t i o n s C e n t e r ( E S O C ) , Darmstadt ,
W e s t Germany, which i s r e s p o n s i b l e f o r a l l t r a c k i n g a n d
d a t a re co ve ry a c t i v i t i e s a f t e r t h e s p a c e c r a f t r ea c h es t r a n s f e r
o r b i t . Launch v e h i c l e t r a c k i n g as well a s e a r l y o r b i t sp ace -
c r a f t t r a c k i n g w i l l b e p r o v i d e d b y N A S A ' s Space Tracking and
Data Network (STDN) w i t h a l l s p a c e c r a f t d a t a s e n t s im ul-
t a n e o u s l y t o ESOC.
T h e s p a c e c r a f t w a s b u i l t u nd er t h e s u p e r vi s i on of th e
E ur op ea n S p a ce A gency b y i n d u s t r i e s i n 1 0 E u r o p e a n c o u n t r i e s :
Belg ium, Denmark , Fran ce , Germany, I t a l y , Ne th er l an ds , Sweden,
Sw i t z e r l an d , t h e Un i t ed Kingeom and Spa in.
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ESA gave direct responsibility for building the satellite
to Hawker Siddeley Dynamics, Britain, as prime contractor.
They were supported by a team of co and subcontractors from
the other countries mentioned above.
NASA's Goddard Space Flight Center, Greenbelt, Md.,
provides technical direction of the Delta project for the
Office of Space Flight. McDonnell Douglas Astronautics Co.,
Huntington Beach, Calif., is the prime contractor. All
reasonable costs for the Delta, launch support including
launch services and tracking support, are reimbursable by
ESA. Such costs are expected to total about $16.1 million.
(END OF GENERAL RELEASE. BACKGROUND INFORMATION FOLLOWS.)
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D E L T A LAUNCH V E H I C L E (3914)
F i r s t S t a g e
The f i r s t s t a g e i s a McDonnell Douglas modified Thorb o o s t e r i n c o r p o r a t i n g n i n e s t ra p - o n T h io k ol s o l i d - f u e lr o c k e t motors. The booster i s powered by a Rocketdynee n g i n e u s i n g l i q u i d o xy gen and l i q u i d h yd ro ca rb on p r o p e l -l a n t s . The main engine i s g im ba l-m ou nte d t o p r o v i d e p i t c hand yaw c o n t r o l from l i f t o f f t o main e n g i n e c u t o f f (MECO) .
Second Stage
The second s t age is 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 n e t h a t a l s o i s g im ba l-m ou nte d t o p r o v i d e p i t c h andyaw c o n t r o l t h r o u g h t h e s ec o nd s t a g e b ur n . A n i t r o g e n g a ss ys te m u s e s e i g h t f i x e d n oz z l e s f o r r o l l c o n t r o l d u r i n g
pow ered and 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 nd yaw c o n t r o ld u r i n g c o a s t and a f t e r s eco nd s t a g e c u t o f f s . Two f i x e dn 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 , hel ium p r e s s u r i z a t i o ns ys tem , p r o vi de 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 ar a t i on .
T h i r d S t a g e
The t h i r d s t a g e i s t h e TE-364-4 s p i n - s t a b i l i z e d , s o l i dp r o p e l l a n t T h i o k o l m o t o r . I t i s s e c u r e d i n t h e s p in t a b l emounted t o t h e s e c o n d s t a g e . The f i r i n g of e i g h t s o l i d pro-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 c om p l is h e s sp i n- upof 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
The D e l ta v e h i c l e \.rill i n j e c t OTS i n t o a t r a n s f e r o r b i t .NASA t r a c k i n g and da t a a c q u i s i t i o n r e s p o n s i b i l i t i e s w i l lc on t i nu e u n t i l a f t e r ABM f i r i n g when o r b i t d e f i n i t i o n i s
agreed be tween NASA and E S A . Command, c o n t ro l , t r a c k in g andd a t a a n a l y s i s t h e n b ecome t h e r e s p o n s i b i l i t y of t h e EuropeanS p ac e O p e r a t i o n s C e n t e r , D a r m s ta d t , W e s t Germany.
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DELTA 3 9 1 4 FACTS A N D FIGURES
Height : 35 .4 m ( 1 1 6 f t . ) i n c l u d i n g s h r o ud
M a x i m u m D i a m e t e r : 2 . 4 m ( 8 f t . ) w i t h o u t
a t ta c h e d s o l i d s
L i f t o f f Weight : 190 ,742 kg (420,5 15 lb.)
L i f to f f Thr us t : 2 ,464 ,200 newtons (555 ,000 lb.)i n c l u d i n g s t ra p -o n s o l i d s
F i r s t S t a ge
( L i q u id o n l y ) c o n s i s t s o f a n e x te n d e d lo n g -t a nk T h or ,pro duc ed by McDonnell Dou glas. The RS-27 e n g in e s a re pro-duced by t h e Rocke tdyne Div i s i on of R o c k w e l l I n t e r n a t i o n a l .The s t a g e h a s t h e f o ll o w in g c h a r a c t e r i s t i c s :
D i a m e t e r : 2 . 4 m ( 8 f t . )
Height : 21 .3 m (70 f t . )
P r o p e l l a n t s : R J - 1 k e r o s e n e a s t h e f u e l and l i q u i doxygen ( L O X ) a s t h e o x i d i z e r
T h r u s t : 912,000 N (205,000 lb.)
Burning T i m e : About 3.48 mi nu tes
Weight: About 84,600 k g (186,500 l b . ) e x c l u d i n g
s t r a p - o n solids
C a s to r I V s tr ap -o n s o l i d s c o n s i s t of n i n e TX 526 ao l i d -p r o p e l l a n t r o c k e t s p ro du ce d by t he Th ioko l Chemica l Corp . ,w i t h t h e f o ll o w in g f e a t u r e s :
D i ame t e r : 0.8 m ( 3 1 in.)
Heigh t : 7 m (23 f t . )
T o t a l W e igh t : 9,798 kg (21,600 l b . ) f o r n i n e1 ,088 kg ( 2,400 lb.) f o r e a c h
Thrus t : 3 ,413 ,700 N (74 ,432 lb.) f o r n i ne379,299 N ( 8,315 lb.) f o r e a ch
Burning T i m e : 58 seconds
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Second Stacre
Produced by McDonnell Douglas A s t ro na u t i cs Co., u s i n ga TRW TR-201 r o c k e t e ng i n e ; m ajo r c o n t r a c t o r s f o r t h ev e h i c l e i n e r t i a l g uid an ce s ys te m l o c a t e d o n t h e se co nd
s t ag e a re Hami l ton S t anda rd , Te l edyne and Delco.
P r o p e l l a n t s : L i q u id , c o n s i s t s o f A er oz en e 50 f o r
t h e f u e l and n i t r o g e n t e t r o x i d e ( N 2 0 4 )f o r t h e o x i d iz e r .
D i a m e t e r : 1.5 m ( 5 f t . ) p l u s 2 . 4 m (8 f t . )
a t t a c h e d r i n g
He igh t : 6 . 4 m ( 2 1 ft.)
Weight : 6 ,118 kg (13,596 l b . )
Th ru s t : About 42 ,943 N ( 9 , 6 5 0 lb.)
To t a l Burning T ime : 335 seconds
T h i r d S t a g e
Th ioko l Chemica l Co. TE-364-4 motor.
P r o p e l l a n t : S o l i d
D i a m e t e r : 1 m ( 3 f t . )
Weight : 1 ,152 kg ( 2 , 5 6 0 l b . )
T h r u s t : 6 1 , 8 5 5 N (13 ,900 1b.I
Burning T i m e : 4 4 s e c o n d s
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LAUNCH OPERATIONS
The Kennedy Space C en te r ' s Expendable Ve hic les D i r e c -
t o r a t e p l a y s a k e y r o l e i n t h e p r e p a r a t i o n a nd l a u n ch oft h e t h r u s t - a u g m e n t e d D e l t a r o c k e t c a r r y i n g O T S .
D el t a 134 w i l l be l aunched f r o m Pad A , n o r t h e r n m o s tof t h e t w o l aunch pads a t Complex 1 7 , Cape Canavera l A i r
Force S t a t i o n .
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 g e w e r e e r e c t e d onPad A July 1 2 . The second s t a g e was e r e c t e d J u l y 1 5 andt h e n i n e s o l i d s t r a p - o n r o c k e t motors w e r e mounted i np l a c e a r ou nd t h e b a s e of t h e f i r s t s t a g e J u ly 25, 2 6 and 2 7 .
The OTS s p a c e c r a f t a r r i v e d a t Kennedy Center May 9
and underwent i t s i n i t i a l c heckou t a t Hangar F a t CapeC a n a v e r a l A i r Force S t a t i o n . I t w i l l be moved t o t h e D e l t a
Spin T e s t F a c i l i t y A u g . 2 2 and w i l l b e m a t e d w i t h t h e D el t at h i r d s t a g e Aug; 30.
The t h i r d s t a g e / s p a c e c r a f t a ss em bl y w i l l be moved t o t h epad and mated wi th D e l t a 134 Sep t ; 1. T h e p a y l o a d f a i r i n gwhich i s 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 t th ro ug hthe a tm osphere i s t o b e p u t i n p l a c e S ep t. 6.
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LAUNCH SEQUENCE FOR OTS
Altitude
Event Time Kilometers/Miles
Liftoff 0 sec. 0 0
Five Solid Motor Burnout 5 7 sec. 10 6
Four Solid Motor Ignition 1 min. 4 sec. 11 7
Three Solid Motor Jettison 1 min. 4 sec. 11 7
Two Solid Motor Jettison 1 min. 5 sec. 13 8
Four S o l i d Motor Burnout 2 min. 2 sec. 41 26
Four Solid Motor Jettison 2 min. 7 sec. 4 6 24
Main Engine Cutoff (MECO) 3 min. 48 sec. 1 0 9 68
First/Second Stage
Separation
113 7 0min. 5 6 sec.
Second Stage Ignition 4 min. 1 sec. 116 7 2
Fairing Jettison 4 min. 22 sec. 126 7 9
Second Stage Cutoff (SECO) 8 min. 21 sec. * 158 99
Second Stage Restart 20 min. 40 sec. 1 7 7 111
SECO 2 21 min. 1 7 sec. 1 7 9 1 1 2
Third Stage Spinup
Second/Third Stage
Separation
22 min. 7 sec. 180 113
22 min. 8 sec. 1 7 9 112
Third Stage Ignition 22 min. 50 sec. 184 115
Third Stage Burnout 23 min. 33 sec. 190 119
Third Stage/Spacecraft 24 min. 46 sec. 2 3 0 144
Separation
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DELTA/OTS LAUNCH TEAM
European Space Agency
Roy Gibson
Wal te r Luksch
D r . Rene C. L. C O l l e t t e
B r i a n S t o c k w e l l
G. W. D u r l i n g
NASA H e a d a u a r t e r s
John F. Yard l ey
Joseph B. Mahon
Pe t e r T. E a t o n
Goddard Space F l i gh t C e n t e r
D r . R o b e r t S. Cooper
Rober t E. Smylie
D 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. Gunn
W i l l i a m R. R u s s e l l
Rober t G o s s
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Direc tor Genera l
Dire c to r o f Corrmunications
Manager of F ixed Serv ice
Communications Programs
OTS Pro j ec t Manage r
OTS Sp a c e c r a ft Manager
Assoc ia t e A d m i n i s t r a t o rf o r S pace F l i g h t
D i r e c t o r o f E x pe n da b leLaunch Vehicle Programs
Manager, D el ta Program
D i r e c t o r
Deputy D i r e c t o r
D i r e c t o r o f P r o j e c t s
Management
Del ta P r o j e c t Manager
Deputy De l t a P r o j e c t Manager,T e c h n i c a l
C h i e f , M i s s io n A n a l y s i sa nd I n t e g r a t i o n B r an ch ,
D e l ta P r o j e c t O f f i c e
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Goddard Ce nte r (Cont 'd . 1Frank Lawrence
Jack Yudd
Raymond Mazur
Kennedy Space Center
L e e R. S c h e r e r
G e r a l d D. G r i f f i n
D r . Walter J . Kapryan
George F. Page
Hugh A. Weston, J r .
B e r t L. G r e n v i l l e
John Dunn
D e l t a M i ss io n I n t e g r a t i o nManager
M i s s i o n O p e r a t i o n s a n d
Network Su pp or t Manager
Miss ion Suppor t
D i r e c t o r
D e p u t y D i r e c t o r
D i r e c t o r , S p a c e Vehic les
O p e r a t i o n s
D i r e c t o r , E x p e n d a b l e V e h i c l e s
C h i e f , D e l t a O p e r a t i o n sD i v i s i o n
Complex 1 7 Opera t ions Manager
S p a c e c r a f t C o o r d i n a t o r
CONTRACTORS
Hawker Si dd e le y Dynamics S pa ce cr af t (pr im e)
United Kingdom
AEG-Telef unkenGermany
A e r i t a l i a , I t a l y
Communicat ions payload(p r ime)
S p a c e c r a f t c o - c o n t r a c t o r
ERNO, Germany Sp ac ec ra f t co -co n t r ac t o r
M a t ra , F r an c e S p a c e c r a f t c o - c o n t r a c t o r
SAAB, Sw eden S p a c e c r a f t c o - c o n t r a c t o r
McDonnell DouglasA s t r o n a u t i c s C o .
Hunt ing ton Beach, C a l i f .
D e l t a l a u n c h v e h i c l e
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