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JCSAT-2 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-393 satellite bus. It was originally ordered by Japan Communications Satellite Company (JCSAT), which later merged into the JSAT Corporation. It had a Ku-band payload and operated on the 154° East longitude until it was replaced by JCSAT-2A.[5]

JCSAT-2

Mission type	Communications
Operator	JSAT Corporation
COSPAR ID	1990-001B [1]
SATCAT no.	20402
Mission duration	8 years (planned)
Spacecraft properties
Spacecraft	JCSAT-2
Spacecraft type	JCSAT
Bus	HS-393
Manufacturer	Hughes
Launch mass	2,280 kg (5,030 lb)
BOL mass	1,364 kg (3,007 lb)
Dimensions	3.7 m × 10 m × 2.3 m (12.1 ft × 32.8 ft × 7.5 ft) with solar panels and antennas deployed.
Power	2.350 kW
Start of mission
Launch date	1 January 1990, 00:07 UTC[2]
Rocket	Commercial Titan III (s/n CT-1) (maiden launch)
Launch site	Cape Canaveral, SLC-40
Contractor	Martin Marietta
End of mission
Disposal	Graveyard orbit
Deactivated	2002 [3]
Orbital parameters
Reference system	Geocentric orbit[4]
Regime	Geostationary orbit
Longitude	154° East
Transponders
Band	32 Ku-band × 27 Mhz[5]
Bandwidth	864 MHz
Coverage area	Japan
TWTA power	20 watts
JSAT constellation ← JCSAT-1 JCSAT-3 →

Satellite description

The spacecraft was designed and manufactured by Hughes Space and Communications Company on the HS-393 satellite bus. It had a launch mass of 2,280 kg (5,030 lb), a mass of 1,364 kg (3,007 lb) after reaching geostationary orbit and an 8-year design life. When stowed for launch, its dimensions were 3.4 m (11 ft) long and 3.7 m (12 ft) in diameter.[6] With its solar panels fully extended it spanned 10 m (33 ft).[5] Its power system generated approximately 2350 watts of power thanks to two cylindrical solar panels.[5] It also had a two 38 Ah NiH₂ batteries.[5] It would serve as the main satellite on the 150° East longitude position of the JSAT fleet.[5]

Its propulsion system was composed of two R-4d-12 liquid apogee engine (LAE) with a thrust of 490 N (110 lb_f). It also used two axial and four radial 22 N (4.9 lb_f) bipropellant thrusters for station keeping and attitude control.[6] It included enough propellant for orbit circularization and 8 years of operation.[5] Its payload was composed of a 2.4 m (7 ft 10 in) antenna fed by thirty-two 27 MHz Ku-band transponders for a total bandwidth of 864 MHz.[5] The Ku-band transponders had a Traveling-wave tube#Traveling-wave-tube amplifier (TWTA) output power of 20 watts.[5]

History

With the opening of the Japanese satellite communications market to private investment, Japan Communications Satellite Company (JCSAT) was founded in 1985.[7][8] In June of the same year, JCSAT awarded an order to Hughes Space and Communications for two identical satellites, JCSAT-1 and JCSAT-2, based on the spin-stabilized HS-393 satellite bus.[5] JCSAT-2 was successfully launched aboard a Commercial Titan III (maiden launch) along Skynet 4A on 1 January 1990 at 00:07 UTC.[1][5] Originally expected to be retired in 2000, it was finally sent to a graveyard orbit on 2002.[3]

References

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