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8/7/2019 Galaxy-A Press Kit
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National Aeronautics andSpace Administration
Washington. D.C20546AC 202 755-8370 ID I I
IMAEDIATEFor Release
Gal axy-APress Kit Project
RELEASE NO: 83-101
Contents
GENERAL RELEASE 2.......................................... . 2
DELTA LAUNCH VEHICLE ..................................... . 6
FLIGHTSEQUENCE OF EVENTS . .............................................. . 8
LAUNCH OPERATIONS ........................ .10
NASA/IN.DUSTRY LAMNC AEA'T ......................... ll
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. .. .. , .. .
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NA SAeNational Aeronautics and
Space Administration25th Anniversaty
Washington DC 20546 W58-1983
AC 202 755-8370
For Release
David Garrett
Headquarters, Washington, D. C. IM'iEDIATE
(Phone: 202/755-3090)
Weida G. TuckerKennedy Space Center, Fla.
(Phone: 305/867-2468)
Charles Recknagel
Goddard Space Flight Center, Greenbelt, Md.
(Phone: 301/344-5566)
RELEASE NO: 83-101
NASA TO LAUNCH GALAXY-A SATELLITE
NASA will launch the Galaxy-A communications spacecraft on
Delta 170 from Launch Complex 17B, Eastern Space and Missile
Center, Cape Canaveral Air Force Station, Fla., no earlier than
June 28. There are three "windows" for launch on that date:
from 6:36 to 7:10 p.m. EDT; from 7:33 to 7:57 p.m. EDT; and from
8:20 to 9:57 p.m. EDT.
June 22, 1983
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3
The Galaxy-A satellite, owned by Hughes Communications,
Inc., a group of wholly owned subsidiaries of Hughes Aircraft
Co., will relay television programming to cable systems in the
continental United States, Alaska, and Hawaii. The satellite
carries a total of 24 operating transponders. The 18 primary
transponders have been sold to six cable prograrmying companies.
One of the remaining six standard transponders has been corrrnitted
to another major programmer and the rest are in various stages of
negoti ation.
Galaxy-A will be positioned in a stationary orbit 35,890
kilometers (22,300 statute miles) above the equator at 134
degrees west longitude, roughly due south of Juneau, Alaska. It
will operate in the 6/4 Ghz C-band and has a design lifetime of
at least nine years.
The Galaxy-A, built for Hughes Communications, Inc., by the
Hughes Aircraft Company's Space and Co-mmunications Group, is the
first in a series of three Galaxy satellites.
The second and third Galaxy satellites, to be launched in
September 1983 and June 1984 respectively, will relay video,
voice, data, and facsimile communicationsin the continental U.S.
for large corporations, long haul carriers, and broadcasters.
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4
The Operations Control Center for the Galaxy satellites is
located at Hughes Conmunications' headquarters in El Segundo,
Calif., with telemetry and command terminals in Fillmore, Calif.,
and Brooklyn, N.\.
The Delta 170 rocket, a 3920/PAM! version of the launch
vehicle, consists of an Extended Long Tank First Stage, the
thrust of its Rocketdyne RS-27 engine augmented by nine Castor IV
strap-on solid motors; the new improved Aerojet AJIO-118W second
stage; and a Payload Assist Module (PAM), which functions as the
final stage.
The entire vehicle is a uniform 2.4 meters (8 feet) in
diameter (excluding the strap-on solid motors) and 35.35 m (116
ft.) in height. McDonnell Douglas Astronautics Corp., Huntington
Beach, Calif., is the prime contractor for production and launch
of the Delta vehicle.
Following launch by the first two stages of the Delta 3920,
G7alaxy-A will be inserted into an elliptical transfer orbit by
the PAM, rather than a conventional third stage. The PAM, built
by McDonnell Douglas, is attached to the satellite.
To produce a near-stationary orbit, an apogee kick motor
(Thiokol Corporation's Star 30 solid propellant rocket) mounted
in the satellite itself will be fired.
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5
Positioning of the spacecraft will follow, using the
satellite's on-board attitude-positioning gas system.
The Hughes Operations Control Center will direct Galaxy-A
(Galaxy-i after achieving orbit) through transfer orbit to its
final position in stationary orbit. Once the satellite reaches
its assigned position, subsystem testing and station-keeping
activities will be carried out by Hughes.
Galaxy-A has a diameter of 216 cm (85 in.) and is 277 cm
(109 in.) high when stowed aboard its Delta launch vehicle. In
orbit, the aft solar panel deploys and the antenna reflector
erects for a combined height of 683 cm (269 in.), or the
equivalent of a two-story building. With its full load of 136 kg
(300 lb.) of station keeping fuel, Galaxy- A weighs 519 kg (1,141
lb.).
Nominal orbit characteristics are:
Transfer Orbit:
Apogee Altitude 36,408 km 22,624 statute miles
Perigee Altitude 185 km 115 statute miles
Inclination 23.51 degrees
Argument of Perigee 178 degrees
Operational Orbit: 35,890 km 22,300 statute miles
Stataon Longitude 134 degrees (W)
(END OF GENERAL RELEASE; BACKGROUND INFORYLATION FOLLOWS.)
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6
I1!E DELTA 3920 VEHICLE/PAM-D
Delta vehiclesare built by the McDonnell Douglas
Corporation, and launched by a combined NASA/McDonnell Douglas
team. The Delta is used to launch a wide variety of scientific
and applications spacecraft, from both Cape Canaveral Air Force
Station in Florida and Vandenberg Air Force Base in California.
Some applications satellites are the TIROS, NIMBUS and ITOS
weather observers, usually launched from Vandenberg into north-
south polar orbits; the LANDSATs, earth resources technology
satellites, also from Vandenberg; many types of communications
satellites from Cape Canaveral; and SMS and GOES synchronous-
orbit weather observers, from the Cape. The scientific
spacecraft, launched from both launch sites, include planetarymagnetic field mapping satellites, solar activity observers,
atmospheric data gatherers,and the diversified Explorer
series. More medium-weight payloads have been launched on Delta
vehicles than all other launch systems in its class combined.
First-Stage
The first stage of the Delta, built by McDonnell Douglas, is
22.6 m (74 ft.) in length and 2,4 m (8 ft.) in diameter. The
main engine, built by Rocketdyne, burns RP-1, a highly refined
kerosene, and liquid oxygen. It produces 912,000 Newtons(205,000 lb.) of thrust at sea level, and burns for about 228
seconds.
Nine CastorIV strap-on solid rocket boosters, built by
Thiokol greatly increase the power of the Delta first stage.Each solid produces 284,672 Newtons (64,000 lb.) thrust at
liftoff. This increases to 418,112 Newtons (94,000 lb.) atmaximum; the average thrust for the 58-second burn time is
379,280 Newtons (85,270 lb.). Six of the solids ignite at
liftoff, and three after the first six burn out. The average
first stage thrust while the six solids, the main engine, and two
4450-Newton (1,000-lb.) thrust verniers are burning is 3,196,333
Newtons (718,600 lb.). Gross vehicle weight will be about
191,728 kilograms (422,700 lb.) at liftoff.
The second stage, built by Aerojet, is approximately six m
(20 ft.) long and 175 cm (69 in.) in diameter through the mainbody. The primary structure consists of two propellant tanks,
mounted one above the other and sharing a central dividingbulkhead. One tank contains the Aerozine-50 fuel and the other
the nitrogen tetroxide oxidizer.
The single engine, called the Aerojet ITIP (Improved
Transtage Injector Program) produces 44,000 Newtons (9,900 lb.)
of thrust and can burn for about 430 seconds.
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7
The Aerojet stage replaces a smaller one that produced
almost as much thrust but had a total burn time of only 300
seconds. The 130 seconds of increased burn time makes the
Aerojet stage much more powerful overall.
Like the older second stage, the Aerojet ITIP can be
restarted in space, providing mission flexibility. This stagealso contains the Delta Redundant Inertial Measurement System(DRIMS), which controls the flight of both the first and secondstages.
The second stage has a 2.4-m (8-ft.)-wide and 28-cm (11-
in.)-high structural assembly called the miniskirt attached 1.07
m (3.5 ft.) from its top. This miniskirt rests on a-2.4-m (8-
ft.)-diameter interstage barrel, 4.7 m (15.5 ft.) high, whichextends upward from the top of the first stage. A 7.9-m (26-
ft.)-high fairing sits on top of the miniskirt, completing the
exterior view of the vehicle. The second stage hangs down inside
the interstage and extends up into the fairing, protected fromcontact with the dense lower atmosphere during first stagef i ht.
Payload Assist Module
This version of the Delta vehicle does not have a third
stage. Instead, a Payload Assist Module (PAM) solid propellantstage is attached to the spacecraft, and provides the final
increment of velocity required to reach the transfer orbit. TwoPAM. stages are available, a -D for Delta vehicles and a larger -A
or Atlas-Centaur class payloads. Both are also designed to beused as added stages on spacecraft released into low Earth orbit
from the Space Shuttle orbiter.
The PAM-D is mounted to the top of the second stage via a
spin table, in a manner similar to that of the original Delta
solid propellant third stage. The miniskirt supports the weight
of the second stage, the PAM-D, and the spacecraft. Small
rockets around the perimeter of the spin table are fired prior to
second and final stage separation, to spin the PAA'-D and the
spacecraft up to about 50 rpm. This spinning motion stabilizes
the stage throughout its burn, ensuring an accurate trajectory.
No other guidance system is required.
The PAAI-D, built by McDonnell Douglas, uses a STAR-48 solid
propellant motor. This stage uses 1,996 kg (4,400 lb.) of
propellant and burns for 85 seconds, while providing an average
thrust of 84,500 Newtons (19,000 lb.).
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10
LAUNCH OPERATIONS
NASA's John F. Kennedy Space Center is responsible for the
preparationand launch of Delta 170 which will carry the Galaxy-A
satellite into orbit.
On April 15 the Delta first stage and interstage were
erected on Pad B of Complex 17 at Cape Canaveral Air Force
Station. On April 16-19, the nine solid strap-on rocket motors
were mounted in place around the base of the first stage. The
first stage was mated with the second stage on April 20.
Flectrical and mechanical qualifications tests were performed on
May 12. A simulated flight was conducted on June 3, *and a flight
sequence test was performed on June 9.
The Gnlaxy-A spacecraft arrived at the Cape Canaveral Air
Force Station on March 22 , and underwent initial checkout. On
May 17 , the reaction control system ordnance was installed. Atelemetry tracking and control test and a spacecraft functional
test were performed on May 18. On May 19, the reflector ordnance
was installed. Mating of the solar array panels with the
spacecraft was completed on May 20. On May 23, critical
clearance checks were performed on the spacecraft, and the apogee
kick motor was checked for leaks. The solar array panels were
deployed on May 24 and solar panel functional checks were
performed. A practice countdown was conducted on May 26.
The spacecraft was moved to the Delta Spin Test Facility on
May 31, and the spacecraft mated with its apogee kick motor. The
safe and arm device and the inner aft thermal barrier were
installed on June 1. The spacecraft was serviced with
propellants on June 2, and a spacecraft functional test was
performed on June 3. The spacecraft was to be moved to the pad
on June 20 and mated with it s booster stage, and a spacecraft
functional test was to be run on that same day. On June 21, a
launch rehearsal and a safe and arm rotation test were scheduled
to take place. The fairing, which will protect the spacecraft on
its flight through the atmosphere, was to be installed on June
23.
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NASA/INDUSTRY LAUNCH TEAM
NASA HEADQUARTERS
Lt.Gen. J. A. Abrahamson Associate Administrator for
Space Flight
Robert E. Smylie Associate Administrator forSpace Tracking and Data Systems
Joseph B. Mahon Director, Special Programs
Peter Eaton Chief, Expendable Launch VehiclePrograms
Henry Clarks Delta Program Manager.
GODDARD SPACE FLIGHT CENTER
Dr. Noel IV. inners Director
John.J. Quann Deputy Director
William C. Keathley Director, Project Management
Robert C. Baumann Acting Delta Project Manager
William A. Russell, Jr. Deputy Delta Project Manager
J. Donald Kraft Manager, Delta Mission Analysis
and Integration
Philip B. Frustace Galaxy-1 Mission IntegrationManager
Robert 1. Seiders Network Support Manager
Ralph Banning Network Director
KENNEDY SPACE CENTER
Richard G. Smith Director
Thomas S. Walton Director, Cargo Operations
Charles D. Gay Director, Expendable VehiclesOperations
Wayne L. McCall Chief, Delta OperationsDivision
Jim Weir Head, Cargo Support Branch
Barry Olton Spacecraft Coordinator
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12
ONTRACES
McDonnell Douglas Delta Launch Vehicle
Astronautics Co.Huntington Beach, Calif.
Rocketdyne Division First Stage Engine (RS-27)
Rockwell International
Canoga Park, Calif.
Thiokol Corp. Castor IV Strap-on Solid
Huntsville, Ala. Fuel Motors
Aerojet Liquid Rocket AJ10-118K (ITIP) Second Stage
Sacramento, Calif. Engine
General Motors Corp. Guidance ComputerDelco DivisionSanta Barbara, Calif.
McDonnell Douglas Payload Assist Module (PAM)
Astronautics Co. Third StageHuntington Beach, Calif.
-end-