JCSAT-3
| Mission type | Communication |
|---|---|
| Operator | Intelsat |
| COSPAR ID | 1995-043A |
| SATCAT no. | 23649 |
| Spacecraft properties | |
| Spacecraft | JCSAT-3 |
| Bus | HS-601 |
| Manufacturer | Hughes |
| Launch mass | 3,105 kg (6,845 lb) |
| Dry mass | 1,841 kg (4,059 lb) |
| Dimensions | 26.2 m × 7.5 m (86 ft × 25 ft) with solar panels and antennas deployed. |
| Power | 5 kW |
| Start of mission | |
| Launch date | 00:53:00, August 29, 1995 |
| Rocket | Atlas IIAS |
| Launch site | Cape Canaveral LC-36B |
| Contractor | International Launch Services |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Inclined geosynchronous |
| Transponders | |
| Band |
Ku band: 12 × 36 Mhz + 16 × 27 Mhz C band: 12 x 36 MHz |
| Bandwidth | 1,296 MHz |
| TWTA power |
Ku band: 63 Watts C band: 34 Watts |
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JCSAT-3 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-601 platform. It was originally ordered by JSAT Corporation, which later merged into the SKY Perfect JSAT Group. It has a mixed Ku band and C band payload and operated on the 128°E longitude until it was replaced by JCSAT-3A.
The spacecraft was designed and manufactured by Hughes on the HS-601 satellite bus. It had a launch mass of 3,105 kg (6,845 lb), a dry mass of 1,841 kg (4,059 lb) and a 12 year design life. When stowed for launch, its dimensions were 2.8 m × 4.9 m × 3.8 m (9 ft 2 in × 16 ft 1 in × 12 ft 6 in). With its solar panels fully extended it spanned 26.2 m (86 ft), and its width when its antennas were fully deployed was 7.5 m (25 ft). Its power system generated approximately 5 kW of power thanks to two wings with four solar panels each. It also had a single NiH2 battery composed of 30 cells and a 200Ah charge. It would serve as the main satellite on the 128°E longitude position of the JSAT fleet.
Its propulsion system was composed of an R-4D-11-300 LAE with a thrust of 490 N (110 lbf). It also used had 12 22 N (4.9 lbf) bipropellant thrusters for station keeping and attitude control. It included enough propellant for orbit circularization and 12 years of operation.
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