First Satellite Designed for Space Shuttle Launch
Diameter:
4.26 m (14 ft)
Overall Height
6.17 m (20 ft 3 in.)
Weight
7,711 kg (17,000 lb)
aboard shuttle
1,388 kg (3,060 lb)
beginning of life
In September 1978, the United States Navy announced a contract award to Hughes Communication Services, Inc., a Hughes Aircraft Company subsidiary, now Boeing, to provide worldwide communications satellite service to the Department of Defense for at least five years at each of four orbital locations. The Navy would act as executive agent on behalf of the Department of Defense. The new satellite, known as Leasat, began service in 1984. Users include mobile air, surface, subsurface, and fixed earth stations of the Navy, Marine Corps, Air Force, and Army. Hughes Space and Communications Company, now Boeing, built the satellites.
The agreement called for Boeing to design, build, launch, and operate a complete communications satellite system. Included were five satellites, one of which was a spare, as well as associated ground facilities -- an operational control center, a network of four fixed ground stations, and two movable stations. The satellites occupied geosynchronous positions over the United States and over the Atlantic, Pacific, and Indian oceans.
The Leasat spacecraft were designed exclusively for launch on NASA's space shuttle. Leasat F1 was scheduled for launch in June 1984, but the shuttle mission was aborted only seconds before liftoff. Leasat F2 became the first in the series to be launched, on 30 August 1984. Leasat F1 followed on an 8 November 1984 launch. Leasat F3 was launched on the shuttle on 12 April 1985, but did not achieve orbit when the satellite failed to start. Four months later, NASA and Boeing mounted a salvage attempt during the 27 August 1985 shuttle mission on which Leasat F4 was launched. After attaching special electronics assemblies to Leasat 3 during two days of space walks, astronauts manually launched the satellite again. The electronics allowed ground controllers to turn on the satellite and, at the end of October, fire its perigee rocket and send Leasat 3 into orbit. Leasat 4 successfully obtained orbit and was undergoing tests about a week after launch when its UHF downlink failed. The satellite was declared a loss. The fifth and last Leasat, which was built as a spare, was successfully launched in January 1990.
SATELLITES
Leasat is 14 feet (4.26 meters) in diameter and 20 feet, 3 inches (6.17 meters) high with its UHF and omnidirectional antennas deployed. With its antennas stowed in the launch configuration, Leasat is 14 feet, 1 inch (4.29 meters) high. Total payload weight (including launch cradle) in the shuttle is 17,000 pounds (7711 kg). Weight after separation from the shuttle is 15,200 pounds (6895 kg), and the satellite's weight on station at the beginning of life is 3,060 pounds (1388 kg).
The satellites are spin-stabilized, with the spun portion containing the solar array and sun and Earth sensors for attitude determination and Earth pointing reference, batteries for eclipse operation, and all propulsion and attitude control hardware. The despun platform contains Earth-pointing reference, batteries for eclipse operation, and all propulsion and attitude control hardware. The despun platform contains Earth-pointing communication antennas, communication repeaters, and the majority of the telemetry, tracking, and command (TT&C) equipment.
Mechanical interface with the shuttle is achieved through a reusable cradle, with five contact points between the spacecraft and the cradle, and five contact points between the cradle and the shuttle.
Power Sources
Solar panel output is 1238 watts after seven years in orbit. Three 25 A-hr nickel-cadmium batteries for eclipse operation are designed for a nominal maximum 45 percent discharge. Redundancy resulting from the three-battery system permits full load support with loss of one of the batteries.
Communications Payload
Two large helical UHF antennas provide receive and transmit capability in the UHF band (240 to 400 MHz). Telemetry, command, and the Fleet Broadcast uplink and beacon are in the "exclusive" portions of the SHF band (7250 to 7500 MHz, and 7975 to 8025 MHz). Twelve UHF repeaters provide the main communications capability.
The principal Navy Fleet Broadcast function includes an SHF uplink, and both SHF and UHF downlinks. The additional antennas for this channel are the SHF uplink and downlink earth coverage horns, which support the uplink and acquisition/timing function, respectively. The UHF downlink for Fleet broadcast is multiplexed onto the UHF transmit helix.
Launch Sequence
Mounting the antennas on deployable structures allows them to be stowed for launch, resulting in considerable savings in the cost of launching the satellite from the space shuttle. (Shuttle launch costs are based on a formula which takes into account the ratio of either weight or length of satellite cargo, whichever is greater, to the shuttle's total capacity.)
The space shuttle places Leasat in a circular parking orbit at approximately 180 miles (296 km) altitude with 28.6 degrees inclination. Ejection of the spacecraft from the shuttle is initiated when locking pins at the contact points are retracted. An explosive device then releases a spring that ejects the spacecraft in a "Frisbee" motion. This gives the satellite its separation velocity and gyroscopic stability.
Two further sets of maneuvers are required to place the satellite in its circular orbit 22,300 miles (35,744 km) over the equator within a 5 degree inclination. The first set boosts the satellite into an elliptical transfer orbit where apogee and perigee are equatorial, with apogee at synchronous altitude. The second maneuvers circularize the orbit and remove all but 5 degrees of inclination, yielding the final synchronous orbit. Because of high satellite velocity in the parking orbit, a solid fuel perigee motor is used to accomplish rapid firing. Two liquid fuel motors are used to augment the velocity on successive perigee transits, to circularize the orbit, and to remove inclination.
| Channel Type | No. | Bandwidth, kHz | EIRP*, dBw | G/T*, dB/K |
|---|---|---|---|---|
| Relay | 6 | 25 | 26 | -18 |
| Wideband | 1 | 500 | 28 | -18 |
| Narrowband | 5 | 5 | 16.5 | -18 |
| Fleet Broadcast | 1 | Onboard Processing | 26 | -20 |
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*Specified minimum values over the coverage areas for the full service period. |
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GROUND SEGMENT
The Leasat ground segment consists of the contractor's operational control center (COCC), two movable ground stations (MGSs), and four contractor satellite control sites (CSCSs) as well as interconnecting leased lines. The ground segment also includes communication equipment and a leased line to the Naval Telecommunications Command Operational Center (NTCOC) in Washington, DC, for coordination of all Leasat operations.
Operational Control Center
THE COCC is located in El Segundo, CA, and houses the computing hardware/software and communication equipment that interfaces with the CSCSs in Guam, Hawaii, Stockton, CA, and Norfolk, VA.
COCC hardware includes two PDP 11/70 computers, either of which can perform the required orbit, attitude, and SHAPE (spacecraft health and performance evaluation) software tasks. In addition, four smaller PDP 11/34 computers, each having a full complement of signal processing hardware, are included to provide the real time software tasks for the four spacecraft. A fifth PDP 11/34 computer serves three purposes--backup, launch support, and training.
Each of the four real time PDP 11/34 computers is connected to an individual spacecraft control console consisting of two cathode ray tube (CRT) keyboard/displays and a hardware spacecraft status panel. In addition, an 11/34 is connected to both of the 11/70s so that either 11/70 can serve the batch processing functions. Through the operator interface, each PDP 11/70 is served by a plotter, printer, and a variety of CRTs and graphic displays for orbit, attitude, and maneuver tasks.
Satellite Control Site
CSCSs acquire telemetry and range data from, and transmit commands to individual satellites via the Navy AN/FSC-79 SHF terminals. CSCS hardware allows either manual or computer control of spacecraft command routing logic in the command modulator, and routing of the telemetry receiver outputs to the telemetry demodulators and/or ranging equipment.
Movable Ground Stations
Two autonomous SHF movable ground stations provide all TT&C functions during the transfer orbit phase of the Leasat mission. These stations also supply backup support, if needed, to operational CSCSs. The MGSs are located at Norfolk and Guam. The Atlantic and continental United States satellites can be controlled from the Norfolk MGS, and the Pacific and Indian Ocean satellites can be controlled from the MGS on Guam.
MGSs are operational throughout the launch phase and then are placed in a standby (nonoperational) mode. Both stations can be reactivated in less than a day if required. Both can be moved in C-130 aircraft and restored to operational status at a new site within two weeks.