The spacecraft was designed and manufactured by then Hughes Space and Communications Company (now Boeing Satellite Development Center) on the HS-601 satellite bus. It had a launch mass of 3,150 kg (6,940 lb), a dry mass of 1,416 kg (3,122 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.[6][7] It had a 29-cell NiH2 battery with a power charge of 200 Ah.[7]
Its payload is composed of two 2.2 m (7 ft 3 in) dual-gridded reflectors and twenty four Ku-bandtransponders powered by a traveling-wave-tube amplifier (TWTA) with and output power of 90 watts. It can configure two 54 MHz transponders into one 114 MHz with an effective 180 watts.[6][7]
The Ku-band footprint covered Japan, southern and eastern Asia, and Hawaii.[7]
History
Space Communications Corporation (SCC) was founded in 1985, the same year as the original companies that later formed JSAT.[8] SCC switched satellite suppliers and on 1995 ordered a satellite from Boeing, Superbird-C.[6]
Payloads are separated by bullets ( · ), launches by pipes ( | ). Crewed flights are indicated in underline. Uncatalogued launch failures are listed in italics. Payloads deployed from other spacecraft are denoted in (brackets).