Superbird-C
| Mission type | Communication |
|---|---|
| Operator | SKY Perfect JSAT Group |
| COSPAR ID | 1997-036A |
| SATCAT № | 24880 |
| Spacecraft properties | |
| Spacecraft | Superbird-C |
| Bus | HS-601 |
| Manufacturer | Hughes |
| Launch mass | 3,130 kg (6,900 lb) |
| Dimensions | 26.2 m × 7.5 m × 4.9 m (86 ft × 25 ft × 16 ft) with solar panels and antennas deployed. |
| Power | 4.5 kW |
| Start of mission | |
| Launch date | 01:15:00, July 28, 1997 |
| Rocket | Atlas IIAS |
| Launch site | Cape Canaveral LC-36B |
| Contractor | International Launch Services |
| End of mission | |
| Disposal | Graveyard orbit |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Graveyard orbit |
| Semi-major axis | 42,505 km |
| Perigee | 36,122.8 km |
| Apogee | 36,145.3 km |
| Inclination | 6.2° |
| Period | 1,453.5 minutes |
| Epoch | 00:00:00UTC 2016-08-26 |
| Transponders | |
| Band | Ku band: 4 × 54 Mhz, 4 × 36 Mhz and 16 × 27 Mhz |
| TWTA power | 90 Watts |
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Superbird-C, was a geostationary communications satellite ordered and operated by Space Communications Corporation (SCC) that was designed and manufactured by Hughes (now Boeing) on the HS-601 platform. It has a pure Ku band payload and was used fill the position at 144°East longitude. It provided television signals and business communications services throughout Japan, southern and eastern Asia, and Hawaii.
The spacecraft was designed and manufactured by then Hughes (now Boeing) on the HSS-601 satellite bus. It had a launch mass of 3,150 kg (6,940 lb) and a 13-year design life. When stowed for launch, it measured 4 m × 3.8 m × 2.4 m (13.1 ft × 12.5 ft × 7.9 ft). It had two wings with four solar panels each, that generated 4.5 kW at the end of its design life. When fully deployed, the solar panels spanned 26.2 m (86 ft), with its antennas in fully extended configuration it was 7.5 m (25 ft) wide. It had a 29-cell NiH2 battery with a power charge of 200Ah.
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 13 years of operation.
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