JCSAT-2
| Mission type | Communications |
|---|---|
| Operator | JSAT Corporation |
| COSPAR ID | 1990-001B[1] |
| SATCATno. | 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) withsolar panelsand antennas deployed. |
| Power | 2.350kW |
| Start of mission | |
| Launch date | 1 January 1990, 00:07UTC[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 | 32Ku-band× 27Mhz[5] |
| Bandwidth | 864 MHz |
| Coverage area | Japan |
| TWTA power | 20 watts |
JCSAT-2was ageostationarycommunications satellitedesigned and manufactured byHughes(nowBoeing) on theHS-393satellite bus.It was originally ordered byJapan Communications Satellite Company(JCSAT), which later merged into theJSAT Corporation.It had aKu-bandpayload and operated on the 154° Eastlongitudeuntil it was replaced byJCSAT-2A.[5]
Satellite description[edit]
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 reachinggeostationary orbitand 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 itssolar panelsfully 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 38AhNiH2batteries.[5]It would serve as the main satellite on the 150° East longitude position of theJSAT fleet.[5]
Its propulsion system was composed of twoR-4d-12liquid apogee engine(LAE) with a thrust of 490 N (110 lbf). It also used two axial and four radial 22 N (4.9 lbf)bipropellantthrustersforstation keepingandattitude control.[6]It included enough propellant fororbit circularizationand 8 years of operation.[5]Its payload was composed of a 2.4 m (7 ft 10 in) antenna fed by thirty-two 27MHzKu-bandtranspondersfor a total bandwidth of 864 MHz.[5]The Ku-band transponders had aTraveling-wave tube#Traveling-wave-tube amplifier(TWTA) output power of 20 watts.[5]
History[edit]
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 toHughes Space and Communicationsfor two identical satellites,JCSAT-1andJCSAT-2,based on thespin-stabilizedHS-393 satellite bus.[5]JCSAT-2 was successfully launched aboard aCommercial Titan III(maiden launch) alongSkynet 4Aon 1 January 1990 at 00:07UTC.[1][5]Originally expected to be retired in 2000, it was finally sent to agraveyard orbiton 2002.[3]
References[edit]
- ^ab"Display: JCSAT 2 1990-001B".NASA. 10 February 2021.Retrieved20 March2021.
This article incorporates text from this source, which is in thepublic domain.
- ^"Trajectory: JCSAT 2 1990-001B".NASA. 10 February 2021.Retrieved20 March2021.This article incorporates text from this source, which is in thepublic domain.
- ^abYanagisawa, Toshifumi (9 March 2016)."Lightcurve observations of LEO objects in JAXA"(PDF).JAXA. Archived fromthe original(PDF)on 26 August 2016.Retrieved16 August2016.
- ^"JCSAT 2".N2YO.com.Retrieved16 August2016.
- ^abcdefghijkKrebs, Gunter (21 April 2016)."JCSat 1, 2".Gunter's Space Page.Retrieved20 July2016.
- ^ab"JCSAT 1, 2".Boeing. Archived fromthe originalon 7 February 2010.Retrieved16 August2016.
- ^"History".SKY Perfect JSAT.Retrieved28 July2016.
- ^"JCSAT".Global Security.Retrieved4 August2016.
