JCSAT-1
| Mission type | Communication | ||||
|---|---|---|---|---|---|
| Operator | JSAT Corporation | ||||
| COSPAR ID | 1989-020A[1] | ||||
| SATCAT № | 19874 | ||||
| Spacecraft properties | |||||
| Spacecraft | JCSAT-1 | ||||
| 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 | 23:29:00, March 6, 1989[2] | ||||
| Rocket | Ariane 44LP | ||||
| Launch site | Kourou ELA-2 | ||||
| Contractor | Arianespace | ||||
| End of mission | |||||
| Disposal | placed in a graveyard orbit | ||||
| Deactivated | 1998[3] | ||||
| Orbital parameters | |||||
| Reference system | Geocentric | ||||
| Regime | Inclined geosynchronous | ||||
| Semi-major axis | 42,373 km | ||||
| Perigee | 35,987.0 km | ||||
| Apogee | 36,018.1 km | ||||
| Inclination | 14.5° | ||||
| Period | 1,446.8 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-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]
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 became 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
- ↑ "JCSAT 1". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- ↑ "JCSAT 1". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- 1 2 Yanagisawa, Toshifumi (2016-03-09). "Lightcurve observations of LEO objects in JAXA" (PDF). JAXA. Retrieved 2016-08-16.
- ↑ "JCSAT 1". n2yo.com. Retrieved 2016-08-16.
- 1 2 3 4 5 6 7 8 9 10 11 Krebs, Gunter Dirk (2016-04-21). "JCSat 1, 2". Gunter's Space Page. Retrieved 2016-07-20.
- 1 2 "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.