JCSAT-1

JCSAT-1 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-393 platform. 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 150°E longitude until it was replaced by JCSAT-1B.[5]

JCSAT-1
Mission typeCommunication
OperatorJSAT Corporation
COSPAR ID1989-020A[1]
SATCAT no.19874
Spacecraft properties
SpacecraftJCSAT-1
BusHS-393
ManufacturerHughes
Launch mass2,280 kg (5,030 lb)
BOL mass1,364 kg (3,007 lb)
Dimensions3.7 m × 10 m × 2.3 m (12.1 ft × 32.8 ft × 7.5 ft) with solar panels and antennas deployed.
Power2.2 kW
Start of mission
Launch date23:29:00, March 6, 1989 (UTC) (1989-03-06T23:29:00Z)[2]
RocketAriane 44LP
Launch siteKourou ELA-2
ContractorArianespace
End of mission
Disposalplaced in a graveyard orbit
Deactivated1998[3]
Orbital parameters
Reference systemGeocentric
RegimeInclined geosynchronous
Semi-major axis42,373  km
Perigee altitude35,987.0 km
Apogee altitude36,018.1 km
Inclination14.5°
Period1,446.8 minutes
Epoch00:00:00 2016-08-16[4]
Transponders
BandKu band: 32 × 27 Mhz[5]
Bandwidth864 MHz
TWTA power20 Watts
 

Satellite description

The spacecraft was designed and manufactured by Hughes 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 2,350 Watts of power thanks to two cylindrical solar panels.[5] It also had a two 38Ah NiH2 batteries.[5] It would serve as the main satellite on the 150°E longitude position of the JSAT fleet.[5]

Its propulsion system was composed of two R-4D LAE with a thrust of 490 N (110 lbf). It also used two axial and four radial 22 N (4.9 lbf) bipropellant thrusters for station keeping and attitude control.[6] It included enough propellant for orbit circularization and 8 years of operation.[5]

Its payload is 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 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] On 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-1 would become the first commercial Japanese communications satellite. It was successfully launched aboard an Ariane-44LP on March 6, 1989 at 23:29:00 UTC.[5]

Originally expected to be retired in 1997, it was finally sent to a graveyard orbit on 1998.[3]

References
  1. "JCSAT 1". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
  2. "JCSAT 1". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
  3. Yanagisawa, Toshifumi (2016-03-09). "Lightcurve observations of LEO objects in JAXA" (PDF). JAXA. Retrieved 2016-08-16.
  4. "JCSAT 1". n2yo.com. Retrieved 2016-08-16.
  5. Krebs, Gunter Dirk (2016-04-21). "JCSat 1, 2". Gunter's Space Page. Retrieved 2016-07-20.
  6. "JCSAT 1,2". Boeing Satellite Development Center. Archived from the original on 2010-02-07. Retrieved 2016-08-16.
  7. "History". SKY Perfect JSAT Holdings Inc. Retrieved 2016-07-28.
  8. "JCSAT". Global Security. Retrieved 2016-08-04.
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