JCSAT-2
| Mission type | Communication |
|---|---|
| Operator | JSAT Corporation |
| COSPAR ID | 1990-001B |
| SATCAT no. | 20402 |
| Spacecraft properties | |
| Spacecraft | JCSAT-2 |
| Bus | HS-393 |
| Manufacturer | Hughes |
| Launch mass | 2,280 kg (5,030 lb) |
| BOL mass | 1,364 kg (3,007 lb) |
| Dimensions | 3.7 m × 10 m × 2.3 m (12.1 ft × 32.8 ft × 7.5 ft) with solar panels and antennas deployed. |
| Power | 2.2 kW |
| Start of mission | |
| Launch date | 00:07:00, January 1, 1990 |
| Rocket | Commercial Titan III |
| Launch site | Cape Canaveral LC-40 |
| Contractor | Martin Marietta |
| End of mission | |
| Disposal | placed in a graveyard orbit |
| Deactivated | 2002 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Inclined geosynchronous |
| Semi-major axis | 42657 km |
| Perigee | 36,021.0 km |
| Apogee | 36,552.2 km |
| Inclination | 12.7° |
| Period | 1,461.3 minutes |
| Epoch | 00:00:00 2016-08-16 |
| Transponders | |
| Band | Ku band: 32 × 27 Mhz |
| Bandwidth | 864 MHz |
| TWTA power | 20 Watts |
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JCSAT-2 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-393 platform. It was originally ordered by Japan Communications Satellite Company (JCSAT), which later merged into the JSAT Corporation. It had a Ku band payload and operated on the 154°E longitude until it was replaced by JCSAT-2A.
The spacecraft was designed and manufactured by Hughes on the HS-393 satellite bus. It had a launch mass of 2,280 kg (5,030 lb), a mass of 1,364 kg (3,007 lb) after reaching geostationary orbit and an 8-year design life. When stowed for launch, its dimensions were 3.4 m (11 ft) long and 3.7 m (12 ft) in diameter. With its solar panels fully extended it spanned 10 m (33 ft). Its power system generated approximately 2,350 Watts of power thanks to two cylindrical solar panels. It also had a two 38Ah NiH2 batteries. It would serve as the main satellite on the 150°E longitude position of the JSAT fleet.
Its propulsion system was composed of two R-4D LAE with a thrust of 490 N (110 lbf). It also used two axial and four radial 22 N (4.9 lbf) bipropellant thrusters for station keeping and attitude control. It included enough propellant for orbit circularization and 8 years of operation.
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