JCSAT-3
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JCSAT-3 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-601 satellite bus. It was originally ordered by JSAT Corporation, which later merged into the SKY Perfect JSAT Group. It has a mixed Ku-band and C-band payload and operated on the 128° East longitude until it was replaced by JCSAT-3A.[2]
| Mission type | Communications |
|---|---|
| Operator | JSAT |
| COSPAR ID | 1995-043A [1] |
| SATCAT no. | 23649 |
| Mission duration | 12 years (planned) |
| Spacecraft properties | |
| Spacecraft | JCSAT-3 |
| Spacecraft type | JCSAT |
| Bus | HS-601 |
| Manufacturer | Hughes |
| Launch mass | 3,105 kg (6,845 lb) |
| Dry mass | 1,841 kg (4,059 lb) |
| Dimensions | 26.2 m × 7.5 m (86 ft × 25 ft) with solar panels and antennas deployed. |
| Power | 5 kW |
| Start of mission | |
| Launch date | 29 August 1995, 00:53:02 UTC[1] |
| Rocket | Atlas IIAS |
| Launch site | Cape Canaveral, LC-36B |
| Contractor | International Launch Services (ILS) |
| End of mission | |
| Disposal | Graveyard orbit |
| Deactivated | March 2007 |
| Last contact | March 2007 |
| Orbital parameters | |
| Reference system | Geocentric orbit |
| Regime | Geostationary orbit |
| Longitude | 128° East |
| Transponders | |
| Band | Ku-band: 12 × 36 Mhz + 16 × 27 MHz C-band: 12 x 36 MHz |
| Bandwidth | 1296 MHz |
| Coverage area | Japan |
| TWTA power | Ku-band: 63 watts C-band: 34 watts |
The spacecraft was designed and manufactured by Hughes on the HS-601 satellite bus. It had a launch mass of 3,105 kg (6,845 lb), a dry mass of 1,841 kg (4,059 lb) and a 12-year design life. When stowed for launch, its dimensions were 2.8 m × 4.9 m × 3.8 m (9 ft 2 in × 16 ft 1 in × 12 ft 6 in). With its solar panels fully extended it spanned 26.2 m (86 ft), and its width when its antennas were fully deployed was 7.5 m (25 ft).[2] Its power system generated approximately 5 kW of power thanks to two wings with four solar panels each.[2][3] It also had a single NiH2 battery composed of 30 cells and a 200 Ah charge.[2] It would serve as the main satellite on the 128° East longitude position of the JSAT fleet.[2]
Its propulsion system was composed of an R-4D-11-300 liquid apogee engine (LAE) with a thrust of 490 N (110 lbf). It also used had 12 22 N (4.9 lbf) bipropellant thrusters for station keeping and attitude control. It included enough propellant for orbit circularization and 12 years of operation.[2]
Its payload is composed of four octagonal antenna fed by twelve 36 MHz and sixteen 27 MHz Ku-band plus twelve 27 MHz C-band transponders for a total bandwidth of 1296 MHz.[2] The Ku-band transponders have a TWTA output power of 63 watts while the twelve C-band transponders have 34 watts of power.[2]
In 1993, Japan Communications Satellite Company and Satellite Japan Corporation merged to form Japan Satellite Systems Inc. (JCSAT).[4] That same year, JCSAT ordered JCSAT-3, a third satellite from Hughes, but this time using the HS-601 platform.[2] In 1995, JCSAT obtained a license for international service, and thus became a regional operator.[4]
On 29 August 1995 at 00:53:02 UTC, an Atlas IIAS launching from Cape Canaveral LC-36B successfully launched JCSAT-3 into orbit. It was positioned into the 128° East orbital longitude.[2]
On 20 April 2004, JSAT ordered a second satellite from Lockheed Martin, JCSAT-10. Based on the A2100-AX satellite bus, it would have a C-band and Ku-band payload and was expected to replace JCSAT-3 at the 128° East orbital longitude after its planned 2006 launch.[5] On 11 August 2006, an Ariane 5 ECA launched JCSAT-10 (JCSAT-3A) along Syracuse-3B into a transfer orbit. Upon successful deployment at 128° East longitude, it was renamed JCSAT-3A.[6] In March 2007, JCSAT-3 was retired and decommissioned.[7][8]
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