BSAT-2c
| Mission type | Communication |
|---|---|
| Operator | B-SAT |
| COSPAR ID | 2003-028A |
| SATCAT no. | 27830 |
| Spacecraft properties | |
| Spacecraft | BSAT-2c |
| Bus | STAR-1 |
| Manufacturer | Orbital Sciences Corporation |
| Launch mass | 1,275 kg (2,811 lb) |
| Dry mass | 535 kg (1,179 lb) |
| Dimensions | 3.7 m × 2.5 m × 2 m (12.1 ft × 8.2 ft × 6.6 ft) |
| Power | 2.6 kW |
| Start of mission | |
| Launch date | 22:38, June 11, 2003 |
| Rocket | Ariane 5G V-161 |
| Launch site | Guiana Space Center ELA-3 |
| Contractor | Arianespace |
| Entered service | July 15, 2003 |
| End of mission | |
| Disposal | Placed in a graveyard orbit |
| Deactivated | August 2013 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Graveyard orbit |
| Semi-major axis | 42,467 km |
| Perigee | 36,065.2 km |
| Apogee | 36,128.7 km |
| Inclination | 2.5° |
| Period | 1,451.6 minutes |
| Epoch | 00:00:00 UTC 2016-09-09 |
| Transponders | |
| Band | 4 (plus 4 spares) Ku band |
| TWTA power | 130 Watts |
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BSAT-2c, was a geostationary communications satellite operated by B-SAT and was designed and manufactured by Orbital Sciences Corporation on the STAR-1 platform. It was stationed on the 110° East orbital slot along its companion BSAT-2a from where they provided redundant high definition direct television broadcastin across Japan.
The original companion for BSAT-2a was BSAT-2b, but a launch failure during its launch during July 2001, meant that it was not possible to commission it into service. Thus, during October of the same year BSAT-2c was ordered and launched in June 2003. It was retired in August 2013.
BSAT-2c was designed and manufactured by Orbital Sciences Corporation on the STAR-1 satellite bus for B-SAT. It had a launch mass of 1,275 kg (2,811 lb), a dry mass of 535 kg (1,179 lb), and a 10-year design life. As all four STAR-1 satellites, it had a solid rocket Star 30CBP apogee kick motor for orbit raising, plus 200 kg (440 lb) of propellant for its liquid propellant station keeping thrusters.
It measured 3.7 m × 2.5 m × 2 m (12.1 ft × 8.2 ft × 6.6 ft) when stowed for launch. Its dual wing solar panels could generate 2.6 kW of power at the beginning of its design life, and it span was 11.5 m (38 ft) when fully deployed.
It had a single Ku band payload with four active transponders plus four spares with a TWTA output power of 130 Watts.
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