Superbird-A2
| Names |
Superbird 6 (Sep-2001 to Apr-2004) Superbird-A2 (Apr-2004 onward) |
|---|---|
| Mission type | Communication |
| Operator | SKY Perfect JSAT Group |
| COSPAR ID | 2004-011A |
| SATCAT № | 28218 |
| Website | Archived official page |
| Spacecraft properties | |
| Spacecraft | Superbird-A2 |
| Bus | Boeing 601 |
| Manufacturer | Boeing |
| Launch mass | 3,100 kg (6,800 lb) |
| BOL mass | 1,528 kg (3,369 lb) |
| Dry mass | 1,477 kg (3,256 lb) |
| Dimensions | 26.2 m × 7.5 m × 4.5 m (86 ft × 25 ft × 15 ft) with solar panels and antennas deployed. |
| Power | 4378 W |
| Start of mission | |
| Launch date | 00:45:00, April 16, 2004 |
| 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 | 42,394 km |
| Perigee | 35,923.2 km |
| Apogee | 36,123.7 km |
| Inclination | 9.6° |
| Period | 1,447.8 minutes |
| Epoch | 00:00:00UTC 2016-08-26 |
| Transponders | |
| Band |
Ku band: 23 × 36 MHz Ka band: 4 × 100 MHz |
| Bandwidth | 1,228 MHz |
| Coverage area |
Ku band: Japan wide beam Ka band: Japan wide beam + steerable spot |
| TWTA power |
Ku band: 85 Watts Ka band: 70 Watts |
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Superbird 6 (Sep-2001 to Apr-2004)
Superbird-A2, known as Superbird-6 before launch, 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 had a mixed Ku band and Ka band payload and was expected replace Superbird-A at the position at 158°East longitude. It was expected to provided television signals and business communications services throughout Japan, southern and eastern Asia, and Hawaii.
While the launch was within the margins specified by the satellite manufacturer, the trajectory analysis had been inexact and the satellite suffered sever life and power degradation. It tried to use a supersynchronous transfer strategy, but Boeing had failed to take into consideration the effect of the Moon. Thus, the lowest part of the orbit dropped too fast and much propellant had to be spent on a fast transit to geosynchronous orbit. Additionally, the solar panels suffered damage from the extreme contact with the atmosphere. Given the damage to the spacecraft, it was never put into service.
The spacecraft was designed and manufactured by Boeing on the BSS-601 satellite bus. It had a launch mass of 3,100 kg (6,800 lb), a begging of life mass of 1,528 kg (3,369 lb) and an end of life mass of 1,477 kg (3,256 lb). It was designed for a 13 year life. When stowed for launch, it measured 4.5 m × 3.5 m × 3.5 m (15 ft × 11 ft × 11 ft). It had two wings with four solar panels each, that generated 4378 W 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.
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