| Newsgroups: sci.space
Subject: NASA to launch Navy communications satellite (Forwarded)
Date: 18 Sep 89 17:41:52 GMT
Reply-To: yee@trident.arc.nasa.gov (Peter E. Yee)
Organization: NASA Ames Research Center, Moffett Field, CA
Jim Cast
Headquarters, Washington, D.C.
Mary Ann Peto
Lewis Research Center, Cleveland
Lisa Malone
Kennedy Space Center, Fla.
1st Lt. John Kennedy
Air Force Space Systems Division, Los Angeles
Jack Isabel
General Dynamics, San Diego, Calif.
RELEASE: 89-145
NASA TO LAUNCH NAVY COMMUNICATIONS SATELLITE
Agency officials today announced a target date of no earlier than
September 22 for the 68th and final launch of a NASA Atlas/Centaur
vehicle. Atlas/Centaur-68 is scheduled to place the last in a series
of Navy FLTSATCOM communications spacecraft into a geosynchronous
Earth orbit. Launch will take place from Complex 36B, Cape Canaveral
Air Force Station, Fla. The 30- minute launch window opens at 4:15
a.m., EDT.
This final chapter in NASA's Atlas/Centaur history has roots
dating back to May 1962, when the first launch took place. Since
then, the program has earned its place in history with missions
such as Ranger and Surveyor probes to the Moon; Mariner flights
to Mars, Venus and Mercury; and several series of communications
satellite launches including FLTSATCOM, Intelsat and Comstar.
FLTSATCOM satellites -- five have been sucessfully placed
into orbit -- are the spaceborne portion of a worldwide Navy, Air
Force and Department of Defense system to enable communications
between naval aircraft, ships, submarines, ground stations,
Strategic Air Command elements and Presidential Command Network.
The FLTSATCOM program is managed by the Space and Naval
Warfare Systems Command. The Air Force Space Systems Division,
Los Angeles, is responsible for production, launch
vehicle/spacecraft integration and tracking and data
acquisition. FLTSATCOM spacecraft are built in Redondo Beach,
Calif., by the Defense and Space Systems Group of TRW, Inc.
Atlas/Centaur is built for NASA by General Dynamics Space
Systems Division, San Diego, Calif. General Dynamics, under an
agreement signed with NASA in 1988, has assumed operation and
control of Launch Complex 36 and in the future, will provide
commercial Atlas launch transportation services for both the
Government and the private sector from that site. With NASA
oversight, General Dynamics will serve in the capacity of Launch
Director for the upcoming mission.
NOTE TO EDITORS
Events and logistics associated with the upcoming launch of
Atlas/Centaur-68 follow:
NEWS CONFERENCES: An L-2 day prelaunch conference is presently
scheduled for 2 p.m., EDT, on Wednesday, September 20. The
conference will be held in the E&O Building Conference Room, Cape
Canaveral Air Force Station (CCAFS). If sufficient on-site press
interest exists, a postlaunch conference also may be held at the
same location at approximately T+1 hour. Conference participants
will include NASA, DoD and General Dynamics program officials.
Local press questions only will be accommodated.
PRESS VIEWING: Press viewing of the launch will be from Press Site 1, CCAFS.
ACCREDITATION AND BADGING: Requests for accreditation and
badging for the launch should be directed to the Kennedy Space
Center Public Information Branch, Phone: XXX/YYY-ZZZ. Special
audio-visual requirements (remote camera setups will be
accommodated) should be directed to the KSC audio visual office,
Phone: XXX/YYY-ZZZZ.
NASA SELECT COVERAGE: Audio and video of the prelaunch and
postlaunch (if held) news conferences will be carried via NASA
SELECT television. Launch commentary and video also will be
carried via NASA SELECT beginning at 3 a.m. EDT, launch
morning. NASA Select is available via GE Satcom F2R, Transponder
13, 72 degrees W. Longitude, 3960 MHz, vertical polarization.
ATLAS/CENTAUR LAUNCH VEHICLE
The Atlas/Centaur is NASA's standard launch vehicle for
intermediate weight payloads. It is used to launch payloads into
low-Earth orbit, geosynchronous-Earth orbit and on interplanetary
trajectories.
Centaur was the nation's first high-energy, liquid
hydrogen/liquid oxygen propelled rocket. Developed and launched
under the direction of NASA's Lewis Research Center, Cleveland,
it became operational in 1966 with the launch of Surveyor 1, the
first U.S. spacecraft to soft-land on the lunar surface.
Since that time, both the Atlas booster and Centaur second
stage have undergone many improvements. At present, the vehicle
combination can place 13,500 pounds in low-Earth orbit, 5,100
pounds in a synchronous transfer orbit and 2,180 pounds on an
interplanetary trajectory.
The Atlas/Centaur, approximately 137 feet high, consists of
an Atlas SLV-3G booster and Centaur D-1AR second stage. The
Atlas booster develops 438,922 pounds of thrust at liftoff using
two 188,750 thrust booster engines, one 60,500 pound thrust
sustainer engine and two vernier engines developing 461 pounds
thrust each. The two RL-10 engines on Centaur produce a total of
33,000 pounds of thrust. Both the Atlas and Centaur are 10-feet
in diameter.
Until early 1974, Centaur was used exclusively in
combination with the Atlas booster. It was subsequently used
with a Titan III booster to launch heavier payloads into Earth
orbit and interplanetary trajectories.
The Atlas and the Centaur vehicles have been updated over
the years. Thrust of the Atlas engines has been increased about
50,000 pounds since their first use in the space program in the
early 1960's.
The Centaur D-1AR has an integrated electronic system that
performs a major role in checking itself and other vehicle
systems before launch and also maintains control of major events
after liftoff. The new Centaur system handles navigation and
guidance tasks, controls, pressurization and venting, propellant
management, telemetry formats and transmission and initiates
vehicle events. Most operational needs can be met by changing
the computer software.
ATLAS/CENTAUR-68 LAUNCH VEHICLE CHARACTERISTICS
A/C-68 liftoff weight including spacecraft is 360,917
pounds. Liftoff height is 137 feet. Launch Complex 36 (Pad B)
is used for the launch operation.
ATLAS BOOSTER CENTAUR STAGE
Fueled Weight 320,701 lbs. 38,824 lbs.
Height: 76 feet 61 feet
with payload fairing
Thrust: 438,922 lbs 33,000 lbs
at sea level in vacuum
Propellants: Liquid oxygen Liquid oxygen/
and RP-1 liquid hydrogen
Propulsion: MA-5 system two Two 16,500 pound
188,750 lb thrust thrust RL-10
booster engines, one engines, 12 small
60,500 lb thrust hydrazine thrusters
sustainer engine, two
461 lb thrust vernier
engines
Velocity: 6,584 mph at booster 22,513 mph
engine cutoff (BECO), at spacecraft
9,486 mph at sustainer separation
engine cutoff (SECO)
Guidance: Preprogrammed profile Inertial guidance
through BECO. Switch
to inertial guidance
for sustainer phase
FLEET SATELLITE COMMUNICATIONS SYSTEM
The Fleet Satellite Communications System, managed by the
U.S. Navy, provides near global satellite communications for high
priority requirements of the Navy, Air Force and other Department
of Defense communications needs.
Five satellites presently comprise the FLTSATCOM
constellation. Two satellites in the planned eight-satellite
series were lost -- the Flight 4 spacecraft was damaged during
launch in 1981 and did not operate and the Flight 6 spacecraft
and launch vehicle were destroyed by an apparent lightning strike
during launch in 1987.
Each FLTSATCOM spacecraft has 23 communications channels in
the ultra-high and super-high frequency bands. Ten of the
channels are used by the Navy for worldwide communications among
its land, sea and air forces. Twelve of the channels are used by
the Air Force as part of the Air Force Satellite Communications
System for command and control nuclear capable forces. A 500
kilohertz channel on the satellite is allotted to National
Command Authority.
The ground segment of the fleet satellite system consists of
links among designated and mobile users, including most U.S. Navy
ships and selected Air Force and Navy aircraft, submarines,
global ground stations and presidential command networks. These
terminals are being managed and acquired by the individual services.
FLTSATCOM FLIGHT-8 CHARACTERISTICS (A/C-68)
WEIGHT: The final FLTSATCOM spacecraft (designated Flight-8)
along with its apogee kick motor, with solid propellant, weighs
approximately 5,100 pounds going into transfer orbit.
SIZE: The Flight-8 spacecraft body is 8 feet in diameter and
22.8 feet high. Main parabolic antenna is 16 feet in diameter
with an 80-inch solid center surrounded by a wire mesh screen.
Once in orbit, the folded screen is deployed by ground command.
A 13.5 foot helical receive antenna, 13-inches in diameter at the
base, is mounted outside the edge of the transmit antenna dish.
The receive antenna also is folded within the Centaur fairing
during launch and deployed by separate ground commands.
POWER: Primary electrical power for the Flight-8 spacecraft is
provided by two deployable solar array paddles which supply
approximately 1,200 watts of power. In addition, three nickel-
cadmium batteries, each having 24-sealed, 34-amp-hour cells,
provide power during eclipse operations.
DESIGN LIFE: 5 years
ORBIT: The satellites are three-axis stabilized in geosynchronous
orbit, 22,250 nautical miles above Earth's equator.
MAJOR CONTRACTOR: TRW Space and Defense Systems Group, Redondo Beach, Calif.
ATLAS/CENTAUR-68 LAUNCH VEHICLE PREPARATIONS
Kennedy Space Center is responsible for pre-launch
processing and testing of the Atlas Centaur-68 vehicle. Most of
this activity occurred at Launch Complex 36 on the Cape Canaveral
Air Force Station (CCAFS).
The launch of AC-68 originally was planned for 1987, but was
postponed after a leak was discovered during a terminal countdown
demonstration test in June of that year. The leak, near the
Centaur number one engine gimbal assembly, resulted in a decision
to demate the Centaur stage.
During the disassembly process, a workstand was dislodged,
fell and struck the Centaur liquid hydrogen tank, causing the
rupture and loss of the tank. An investigation board concluded
that the tank was ruptured when a leg of the falling workstand
penetrated the tank skin.
A new Centaur stage had to be fabricated and both the Atlas
booster and Centaur upper stage were shipped back to the General
Dynamics plant in San Diego.
The current Atlas/Centaur vehicle arrived by C5A transport
plane at the Skid Strip on CCAFS on May 24. The Atlas first
stage was erected in the gantry of Pad B on Launch Complex 36 on
June 6 and the interstage adapter was attached the next day. The
Centaur stage was hoisted into the gantry and mated to the Atlas
stage on June 8. The vehicle was powered up for integrated
testing on June 20.
A terminal countdown demonstration, which includes loading
the vehicle with propellants, was conducted Aug. 22. This test
served as a launch team certification and is designed to simulate
as closely as possible all pre-liftoff events on launch day,
including the loading of propellants.
A flight events demonstration, an electrical test which
simulates post-liftoff events and exercises all components aboard
the vehicle used during powered flight, was conducted on Sept. 7.
All launch vehicle and pad operations during the countdown
are conducted from the blockhouse at Complex 36 by a joint NASA-
General Dynamics Space Systems launch team.
FLTSATCOM F-8 SATELLITE PRELAUNCH PROCESSING
The FLTSATCOM F-8 spacecraft was shipped from the TRW plant
in Redondo Beach, Calif., and arrived at Hangar AM on Cape
Canaveral Air Force Station on July 31.
The satellite was removed from its environmentally
controlled storage canister and testing was resumed. The systems
tests were completed on Aug. 11.
The satellite was transported to the Explosive Safe Area
(ESA-60) on Aug. 21. The apogee kick motor, the solid propellant
rocket used to circularize the orbit at geosynchronous altitude,
was installed on Aug. 21 and 22 at this facility.
Encapsulation of the spacecraft in the nose fairing, which
protects the spacecraft during the portion of flight within the
Earth's atmosphere, was accomplished on Sept. 11.
The satellite was scheduled to be transferred to Pad B at
Launch Complex 36 on Sept. 12, where it was hoisted into position
atop the Atlas Centaur rocket. A composite electrical readiness
test was completed on Sept. 14, to demonstrate the operation of
all airborne electrical systems and components used in-flight.
Spacecraft prelaunch processing, testing and launch vehicle
integration are managed and conducted by a joint Air Force/TRW
test team at CCAFS.
DOWNRANGE LAUNCH SUPPORT
Launch vehicle telemetry and data will be established
through the NASA Spaceflight Tracking and Data Network and the
Air Force Eastern Test Range. Initial launch coverage will come
from the Merritt Island Launch Area station located at Kennedy
Space Center and the USAF's Tel-4 station located on south KSC,
followed by the NASA station on Bermuda. As the vehicle moves
downrange, tracking support will be provided by other NASA
stations at Ascension Island and Canberra, Australia.
The Eastern Test Range also will supply telemetry and data
from its stations at Tel-4, Jupiter Inlet, Fla., and from its
downrange tracking station on the island of Antigua. A pair of
Advanced Range Instrumentation Aircraft stationed over the
Atlantic Ocean between Ascension Island and Africa will cover the
time interval of the second main engine burn on the Centaur stage
and the subsequent spacecraft separation.
NASA and Department of Defense radars will provide downrange
trajectory information to range safety personnel and computers.
The radars are located at Cape Canaveral, Tel-4 Patrick Air Force
Base, Jupiter Inlet, Bermuda and Antigua.
FLIGHT EVENTS SEQUENCE: ATLAS/CENTAUR-68, FLTSATCOM F-8
EVENT TIME AFTER ALTITUDE DISTANCE SPEED
LIFTOFF (miles) DOWNRANGE (mph)
(miles)
Liftoff T-0 ------ ------- -------
Atlas Booster 2 min 35 sec 37 55 5,703
Engine Cutoff
Jettison Atlas 2 min 38 sec 39 60 5,704
Booster Engine
Jettison Centaur 3 min 0 sec 51 93 6,124
Insulation Panels
Jettison Nose 3 min 43 sec 71 169 7,055
Fairing
Atlas Sustainer/ 4 min 30 sec 89 266 8,466
Vernier Engines Cutoff
Atlas/Centaur 4 min 32 sec 89 271 8,469
Separation
First Centaur 4 min 43 sec 97 295 8,441
Main Engines Start
Centaur Main 9 min 55 sec 102 1,294 16,652
Engines Cutoff
Second Centaur 23 min 56 sec 101 5,013 16,686
Main Engines Start
Second Centaur 25 min 32 sec 110 5,600 22,013
Main Engines Cutoff
Centaur/Payload 27 min 47 sec 179 6,391 21,791
Separation
(These numbers may vary, depending on exact launch date, launch
time and spacecraft weight)
GENERAL DYNAMICS/LAUNCH COMPLEX 36: A NEW ERA
General Dynamics, under an agreement signed with NASA in
1988, has assumed operation and control of Launch Complex 36,
CCAFS. Following the upcoming Atlas/Centaur-68 mission, the
company plans to provide commercial Atlas launch services from
that site for both NASA and private customers.
General Dynamics' first commercial launch of its Atlas I
vehicle is scheduled for 1990 with a launch rate capability of
four launches per year from Complex 36B. The Atlas I
configuration accommodates an 11-foot-diameter as well as a 14-
foot-diameter fairing enabling the vehicle to perform a broader
range of missions. General Dynamics also is developing a
commercial derivative of its military Atlas II vehicle. The
commercial configuration is called Atlas IIA, which will offer 25
percent higher performance than Atlas I. Atlas II class vehicles
begin launch operations in 1992.
To date, General Dynamics has contracted for commercial
launch services with four users. A EUTELSAT II spacecraft is
scheduled for a 1990 launch with options for two additional
launches. NASA, on behalf of the National Oceanic and
Atmospheric Administration, has contracted for commercial launch
services for up to five Geostationary Operational Environmental
Satellites (GOES). The first GOES launch is scheduled for
1990. In addition, NASA has awarded the 1990 launch of its
Combined Release and Radiation Effects Satellite to General
Dynamics for a commercial Atlas launch.
General Dynamics also is under contract from Hughes to
launch 10 of the new generation UHF Follow-On communications
satellites, and Intelsat has contracted for two launches on Atlas
IIAs.
PREVIOUS ATLAS CENTAUR VEHICLE FLIGHTS
PROGRAM INITIATION DATE: 1958 FIRST FLIGHT: May 8, 1962
LAUNCHES TO DATE: 67 LAUNCH VEHICLE SUCCESSES: 57
LAST 20 FLIGHTS
LAUNCH LAUNCH FINAL PAYLOAD
DATE VEHICLE SPACECRAFT ORBIT ACHIEVED S/F*
AUG 8,1978 AC-51 PIONEER VENUS-2 HELIO S
NOV 13,1978 AC-52 HEAO B LEO S
MAY 4, 1979 AC-47 FLTSATCOM-2 GSO S
SEP 20, 1979 AC-53 HEAO 3 LEO S
JAN 17, 1980 AC-49 FLTSATCOM-3 GSO S
OCT 30, 1980 AC-57 FLTSATCOM-4 GSO S
DEC 6, 1980 AC-54 INTELSAT V GSO S
FEB 21, 1981 AC-42 COMSTAR D-4 GSO S
MAY 23, 1981 AC-56 INTELSAT V GSO S
AUG 6, 1981 AC-59 FLTSATCOM-5 GSO F
DEC 15, 1981 AC-55 INTELSAT V GSO S
MAR 4, 1982 AC-58 INTELSAT V GSO S
SEP 28, 1982 AC-60 INTELSAT V GSO S
MAY 19, 1983 AC-61 INTELSAT V GSO S
JUN 9, 1984 AC-62 INTELSAT V F
MAR 22, 1985 AC-63 INTELSAT VA GSO S
JUN 29, 1985 AC-64 INTELSAT VA GSO S
SEP 28, 1985 AC-65 INTELSAT VA GSO S
DEC 4, 1986 AC-66 FLTSATCOM-7 GSO S
MAR 26, 1987 AC-67 FLTSATCOM-6 F
(S/Successful F/Failure)*
ATLAS/CENTAUR-68, FLTSATCOM F-8 LAUNCH TEAM
NASA Headquarters
J.B. Mahon Deputy Associate Administrator for
Space Flight (Flight Systems)
C.R. Gunn Director of Unmanned Launch Vehicles
and Upper Stages
J.P. Castellano Chief, Intermediate and Large Launch
Vehicles
Kennedy Space Center
Gen. F.S. McCartney, Director
John T. Conway Director, Payload Management and
Operations
James L. Womack Director, Expendable Vehicle Operations
James E. Weir Chief, Payload Support Management Branch
S. M. Francois Chief, Launch Operations Division
David C. Bragdon Spacecraft Coordinator
Lewis Research Center
Dr. J.M. Klineberg Director
V.J. Weyers Director of Space Flight System
S.V. Szabo Director of Engineering
J.W. Gibb Manager, Launch Vehicle Project Office
R.E. Orzechowski FLTSATCOM Mission Manager
E. Procasky A/C-68 Chief Engineer
FLTSATCOM
Col. S.P. Purdy FLTSATCOM Program Director
Cmdr. J.O. Hall Asst. Dep. Director for FLTSATCOM
Capt. B.J. Sapp FLTSATCOM Program Manager
Capt. T.R. Newman FLTSATCOM Launch Operations Manager
General Dynamics
D.R. Dunbar GDCLS/Atlas/Centaur Vice President and
Technical Director
B.J. Sherwood GDCLS/Program Manager FLTSATCOM
F.E. Watkins GDSS-CCAFS Director Base Operations
S.K. Baker GDSS-CCAFS Engr. Managerm Atlas I/II
Launch Operations
R.J. Moberly GDSS/Atlas/Centaur Program Manager
W.F. Sauer GDSS/A/C-68 Chief Engineer
TRW
B. Beckham Program Manager FLTSATCOM
F. Wohrman Launch Operations Director
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