JCSAT-2
| Mission type | Communication |
|---|---|
| Operator | JSAT Corporation |
| COSPAR ID | 1990-001B[1] |
| SATCAT no. | 20402 |
| Spacecraft properties | |
| Spacecraft | JCSAT-2 |
| 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 | 2.2 kW |
| Start of mission | |
| Launch date | 00:07:00, January 1, 1990 (UTC)[2] |
| Rocket | Commercial Titan III |
| Launch site | Cape Canaveral LC-40 |
| Contractor | Martin Marietta |
| End of mission | |
| Disposal | placed in a graveyard orbit |
| Deactivated | 2002[3] |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Inclined geosynchronous |
| Semi-major axis | 42657 km |
| Perigee altitude | 36,021.0 km |
| Apogee altitude | 36,552.2 km |
| Inclination | 12.7° |
| Period | 1,461.3 minutes |
| Epoch | 00:00:00 2016-08-16[4] |
| Transponders | |
| Band | Ku band: 32 × 27 Mhz[5] |
| Bandwidth | 864 MHz |
| TWTA power | 20 Watts |
JCSAT-2 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 154°E longitude until it was replaced by JCSAT-2A.[5]
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 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 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-2 was successfully launched aboard a Commercial Titan III along Skynet 4A on January 1, 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
- ^ a b "JCSAT 2". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- ^ "JCSAT 2". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- ^ a b Yanagisawa, Toshifumi (2016-03-09). "Lightcurve observations of LEO objects in JAXA" (PDF). JAXA. Retrieved 2016-08-16.
- ^ "JCSAT 2". n2yo.com. Retrieved 2016-08-16.
- ^ a b c d e f g h i j k Krebs, Gunter Dirk (2016-04-21). "JCSat 1, 2". Gunter's Space Page. Retrieved 2016-07-20.
- ^ a b "JCSAT 1,2". Boeing Satellite Development Center. Archived from the original on 2010-02-07. Retrieved 2016-08-16.
- ^ "History". SKY Perfect JSAT Holdings Inc. Retrieved 2016-07-28.
- ^ "JCSAT". Global Security. Retrieved 2016-08-04.
