Manufacturer | Boeing Satellite Development Center | ||
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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) |
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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 | ||
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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.
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. With its solar panels fully extended its height was 10 m (33 ft).
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 These panels used K7 and K4-3/4 solar cells and were more than twice the number than on the HS-376 The bottom panel was retracted around the body and top panel for launch, and extended downwards for operation. It also had a two 38Ah NiH2 batteries.
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. It included enough propellant for orbit circularization and 8 years of operation.