JCSAT-2

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 typeCommunications
OperatorJSAT Corporation
COSPAR ID1990-001B [1]
SATCAT no.20402
Mission duration8 years (planned)
Spacecraft properties
SpacecraftJCSAT-2
Spacecraft typeJCSAT
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.
Power2.350 kW
Start of mission
Launch date1 January 1990, 00:07 UTC[2]
RocketCommercial Titan III (s/n CT-1) (maiden launch)
Launch siteCape Canaveral, SLC-40
ContractorMartin Marietta
End of mission
DisposalGraveyard orbit
Deactivated2002 [3]
Orbital parameters
Reference systemGeocentric orbit[4]
RegimeGeostationary orbit
Longitude154° East
Transponders
Band32 Ku-band × 27 Mhz[5]
Bandwidth864 MHz
Coverage areaJapan
TWTA power20 watts
 

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 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 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
  1. "Display: JCSAT 2 1990-001B". NASA. 10 February 2021. Retrieved 20 March 2021. Public Domain This article incorporates text from this source, which is in the public domain.
  2. "Trajectory: JCSAT 2 1990-001B". NASA. 10 February 2021. Retrieved 20 March 2021. Public Domain This article incorporates text from this source, which is in the public domain.
  3. Yanagisawa, Toshifumi (9 March 2016). "Lightcurve observations of LEO objects in JAXA" (PDF). JAXA. Archived from the original (PDF) on 26 August 2016. Retrieved 16 August 2016.
  4. "JCSAT 2". N2YO.com. Retrieved 16 August 2016.
  5. Krebs, Gunter (21 April 2016). "JCSat 1, 2". Gunter's Space Page. Retrieved 20 July 2016.
  6. "JCSAT 1, 2". Boeing. Archived from the original on 7 February 2010. Retrieved 16 August 2016.
  7. "History". SKY Perfect JSAT. Retrieved 28 July 2016.
  8. "JCSAT". Global Security. Retrieved 4 August 2016.
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