HS-393
| Manufacturer | Boeing Satellite Development Center | ||
|---|---|---|---|
| Country of origin | United States | ||
| Applications | Communications satellite | ||
| Specifications | |||
| Spacecraft type | Spin-stabilized | ||
| Design life | 8 years | ||
| Launch mass | 2.2 to 2.5 t (2.4 to 2.8 tons) | ||
| Dimensions |
Diameter: 3.7 m (12 ft) Height (stowed): 3.4 m (11 ft) Height (deployed): 10 m (33 ft) | ||
| Power | 2 to 2.2 kWatts | ||
| Batteries | 2 × 38Ah NiH2 batteries | ||
| Regime | Geostationary orbit | ||
| Production | |||
| Status | Retired | ||
| Built | 3 | ||
| On order | 3 | ||
| Launched | 3 | ||
| Retired | 3 | ||
| First launch | JCSAT-1 March 6, 1989 | ||
| Last launch | SBS 6, October 12, 1990 | ||
| Related spacecraft | |||
| Derived from | HS-376 | ||
| |||
The Hughes 393 (sometimes referred to as the HS-393 is a communications satellite bus introduced in 1985 by Hughes Space and Communications Company. It was a spin-stabilized bus that had twice as much power as the HS-376 platform.[1][2]
Design
The satellite bus was designed and manufactured by Hughes. It had a launch mass of 2.2 to 2.5 t (2.4 to 2.8 tons), a mass of 1.35 to 1.5 t (1.49 to 1.65 tons) after reaching geostationary orbit and an 8-year design life. When stowed for launch, its dimensions were 3.4 m (11 ft) in height and 3.7 m (12 ft) in diameter.[1][3] With its solar panels fully extended its height was 10 m (33 ft).[4][5]
Its power system generated approximately 2,350 Watts of power at BOL and 2,200 at end of life, thanks to two cylindrical solar panels. These panels used K7 and K4-3/4 solar cells and were more than twice the number than on the HS-376[1] The bottom panel was retracted around the body and top panel for launch, and extended downwards for operation.[1] It also had a two 38Ah NiH2 batteries.[4]
Its propulsion system was composed of two R-4D LAE with a thrust of 490 N (110 lbf). It also had two axial and four radial 22 N (4.9 lbf) bipropellant thrusters for station keeping and attitude control.[1] It included enough propellant for orbit circularization and 8 years of operation.[4]
Its payload was composed of a 2.4 m (7 ft 10 in) antenna fed Ku band transponders.[1][3]
Satellites
The HS-393 was a powerful platform than the HS-376 platform, being able to supply 2,200kW of power versus 1,400 of the HS-376HP. But only three were ever built.[2]
| Satellite | Other Names | Operator | Model | Ordered | Launch | Launch Vehicle | Launch Result | Mass at launch (kg) | Mass at BOL (kg) | Remarks |
|---|---|---|---|---|---|---|---|---|---|---|
| JCSAT-1 | JSAT Corporation | HS-393 | 1985 | 1989-03-06 | Ariane 44LP | Success | 2,280 kg (5,030 lb) | 1,346 kg (2,967 lb) | First Japanese commercial satellite.[4][1] | |
| JCSAT-2 | JSAT Corporation | HS-393 | 1985 | 1990-01-01 | Commercial Titan III | Success | 2,280 kg (5,030 lb) | 1,346 kg (2,967 lb) | [4][1] | |
| SBS 6 | Satellite Business Systems | HS-393 | 1985 | 1990-10-12 | Ariane 44L | Success | 2,478 kg (5,463 lb) | 1,500 kg (3,300 lb) | Launched along Galaxy 6.[5][3] | |
See also
References
- 1 2 3 4 5 6 7 8 "JCSAT 1,2". Boeing Satellite Development Center. Retrieved 2016-08-17.
- 1 2 Krebs, Gunter Dirk (2016-04-21). "Hughes: HS-393". Gunter's Space Page. Retrieved 2016-08-17.
- 1 2 3 "SBS 6". Boeing Satellite Development Center. Retrieved 2016-08-17.
- 1 2 3 4 5 Krebs, Gunter Dirk (2016-08-17). "JCSat 1, 2". Gunter's Space Page. Retrieved 2016-07-20.
- 1 2 Krebs, Gunter Dirk (2016-08-17). "SBS 6". Gunter's Space Page. Retrieved 2016-07-20.