International Designator 1963-031

International Designator: 1963-031A

Satellite Name: Syncom 2

Other Names:

Launch Date: 1963-07-26

Launch Time: 14:38:00 UTC

Launch Site/Country: Cape Canaveral, United States

Launch Vehicle: Thor-Delta

On-orbit Dry Mass: 39 kg

Description:

Syncom 2 was the first geosynchronous satellite. Although the period was 24 hours and the spacecraft remained at a nearly constant longitude, the orbit was inclined at 33 degrees so it was not truly geostationary but moved in an elongated figure-eight pattern 33 degrees north and south of the equator. Syncom 2 was an experimental communications satellite placed over the Atlantic Ocean and Brazil at 55 degrees W longitude. It began regular service on August 16. It demonstrated the feasibility of geosynchronous satellite communications. Voice, teletype, facsimile, and data transmission tests were successfully conducted between the Lakehurst, New Jersey ground station and the USNS Kingsport while the ship was at sea off the coast of Africa and television transmissions were relayed from Lakehurst to the Telstar ground station at Andover, Maine. The Syncoms were the forerunners of the Intelsat series of satellites.

Mission Profile

Syncom 2 was launched into a high-altitude orbit from Cape Canaveral on 1963 July 26. Six hours after launch, the apogee motor was fired to place the spacecraft in an orbit ranging from 34,100 to 36,440 km with a drift rate of 7.5 degrees per day eastward. The apogee was then raised and the drift rate changed to 4.5 degrees per day westward toward the desired position over 55 degrees W longitude. After two weeks of drifting, the nitrogen jets were pulsed in a series of four firings to slow the spacecraft to near-zero drift on August 16, followed by an alignment maneuver. The final orbit was geosynchronous with an inclination of 33 degrees. Operations were turned over to the Department of Defense on 1965 January 1.

Spacecraft and Subsystems

The Syncom satellites were 71 cm diameter, 39 cm high cylinders. The fully fueled mass of the spacecraft was 68 kg. The nozzle of the solid-propellant apogee motor (1,000-lb-thrust designed to impart a velocity increase of 1,431 meters/sec) extended from the bottom of the cylinder and a co-axial slotted array communications antenna from the top. The total height including the nozzle was 64 cm. The radial exterior was covered with 3,840 P-on-n silicon solar cells which provided direct power of 29 watts the 99 percent of the time the spacecraft was in sunlight. Nickle-cadmium rechargeable batteries provided power when the spacecraft was in the Earth's shadow. No active thermal control was required. Most of the central interior of the spacecraft consisted of the tanks and combustion chamber for the apogee motor, around this were arranged two hydrogen peroxide and two nitrogen tanks and the electronics. Attitude and velocity control was provided by nitrogen jets to align the spin axis and hydrogen peroxide jets to position the satellite. Each system had two jets, one parallel and one perpendicular to the spin axis.

Syncom employed a redundant, frequency-translation, active repeater communication system designed to handle one two-way telephone or 16 one-way teletype channels. The dual transponders utilized 2-watt traveling wave tubes. Selection of receiver and transmitter was made by ground command. One receiver had a 13-megacycle bandwidth for TV transmission, the other a 5-megacycle bandwidth. The receiving gain was 2 dB through the slotted dipole antenna. Signals were received on two frequencies near 7360 megacycles and retransmitted on 1815 megacycles. The slotted dipole transmitting antenna radiated a pancake-shaped beam 25 degrees wide with its plane perpendicular to the spacecraft spin axis. There were also four whip antennas oriented normal to the spin axis for telemetry and command.

Mission(s):

Sponsoring Agency/Country:

Source: NSSDC Master Catalog


Dr. T.S. Kelso [TS.Kelso@celestrak.org]
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