N-STAR c
| Mission type | Communication |
|---|---|
| Operator | SKY Perfect JSAT Group |
| COSPAR ID | 2002-035B |
| SATCAT no. | 27461 |
| Spacecraft properties | |
| Spacecraft | N-STAR c |
| Bus | GEOStar-2 |
| Manufacturer | Lockheed Martin/Orbital Sciences Corporation |
| Launch mass | 1,625 kg (3,583 lb) |
| Dimensions | 3.3 m × 1.9 m × 1.5 m (10.8 ft × 6.2 ft × 4.9 ft) |
| Power | 2.6 kW |
| Start of mission | |
| Launch date | 23:22:00, July 5, 2002 |
| Rocket | Ariane 5G V-153 |
| Launch site | Kourou ELA-3 |
| Contractor | Arianespace |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Geosynchronous orbit |
| Longitude | 136°E |
| Epoch | 2016-08-22 00:00:00 UTC |
| Transponders | |
| Band |
C band: 1 S band: 20 |
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N-STAR c, is a geostationary communications satellite originally ordered by NTT DoCoMo and later fully acquired by SKY Perfect JSAT Group. It was designed and manufactured by Lockheed Martin, which acted as prime, developed the payload and did the final integration and testing, and Orbital Sciences Corporation, which supplied the satellite bus on the GEOStar-2 platform and procured the launch services. It had a launch weight of approximately 1,625 kg (3,583 lb), and a 10-year design life. Its payload is composed of 1 C band, and 20 S band transponders and its stationed in the 136°East longitude.
N-STAR c is a 3 axis stabilized geostationary communications satellite based on the GEOStar-2 satellite bus. While its payload was developed by Lockheed Martin, who also did final integration, the satellite bus was supplied by Orbital Sciences Corporation (now Orbital ATK). N-STAR c was the first order for the GEOStar-2 (then called STAR-2) platform, and Orbital supplied it fully integrated and tested to LM.
It weighted 1,625 kg (3,583 lb) at launch, and while the design life was of 10 years. Stowed for launch it measured 3.3 m × 1.9 m × 1.5 m (10.8 ft × 6.2 ft × 4.9 ft). It had a power availability dedicated to the payload of 1.4 kW, thanks to its Multi-junction GaAs solar cells that produced 2.6 kW at the beginning of its operative life and spanned 12.6 m (41 ft) when deployed. The satellite used a bipropellant propulsion system for orbit circularization, station keeping and attitude control, with enough propellant for 12 years.
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