JCSAT-3
| Mission type | Communication |
|---|---|
| Operator | Intelsat |
| COSPAR ID | 1995-043A[1] |
| SATCAT no. | 23649 |
| Spacecraft properties | |
| Spacecraft | JCSAT-3 |
| 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 | 00:53:00, August 29, 1995[2] |
| Rocket | Atlas IIAS |
| Launch site | Cape Canaveral LC-36B |
| Contractor | International Launch Services |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Inclined geosynchronous |
| Transponders | |
| Band | Ku band: 12 × 36 Mhz + 16 × 27 Mhz C band: 12 x 36 MHz |
| Bandwidth | 1,296 MHz |
| TWTA power | Ku band: 63 Watts C band: 34 Watts |
JCSAT-3 was a geostationary communications satellite designed and manufactured by Hughes (now Boeing) on the HS-601 platform. 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°E longitude until it was replaced by JCSAT-3A.[3]
Satellite description
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).[3] Its power system generated approximately 5 kW of power thanks to two wings with four solar panels each.[3][4] It also had a single NiH2 battery composed of 30 cells and a 200Ah charge.[3] It would serve as the main satellite on the 128°E longitude position of the JSAT fleet.[3]
Its propulsion system was composed of an R-4D-11-300 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.[3]
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 1,296 MHz.[3] The Ku band transponders have a TWTA output power of 63 Watts while the twelve C band transponders have 34 Watts of power.[3]
History
On 1993, Japan Communications Satellite Company and Satellite Japan Corporation merged to form Japan Satellite Systems Inc. (JCSAT).[5] That same year, JCSAT ordered JCSAT-3, a third satellite from Hughes, but this time using the HS-601 platform.[3] In 1995, JCSAT obtained a license for international service, and thus became a regional operator.[5]
On August 29 at 00:53:00 UTC, an Atlas IIAS launching from Cape Canaveral LC-36B successfully launched JCSAT-3 into orbit. It was positioned into the 128° East slot.[3]
On April 20, 2004, JSAT ordered a second satellite from Lockheed, JCSAT-10. Based on the A2100AX platform, it would have a C band and Ku band payload and was expected to replace JCSAT-3 at the 128°East slot after its planned 2006 launch.[6]
On October 11, an Ariane 5 ECA launched JCSAT-10 along Syracuse-3B into a transfer orbit. Upon successful deployment at 128°East longitude, it was renamed JCSAT-3A.[7] On March 2007, JCSAT-3 was retired and decommissioned.[8][9]
References
- ^ "JCSAT 3". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- ^ "JCSAT 3". NASA Space Science Data Coordinated Archive. 27 April 2016. Retrieved 2016-08-04.
- ^ a b c d e f g h i j Krebs, Gunter Dirk (2016-04-21). "JCSat 3, 4 (JCSat R) → Intelsat 26". Gunter's Space Page. Retrieved 2016-07-20.
- ^ "Hughes Built JCSAT-4 To Boost Services In Pacific Rim". warunasat.com. Hughes. February 14, 1997. Retrieved 2016-08-11.
- ^ a b "History". SKY Perfect JSAT Holdings Inc. Retrieved 2016-07-28.
- ^ "JSAT Corporation Awards Lockheed Martin Contract For Second A2100 Satellite". Icaa.eu. Lockheed Martin Space Systems. April 20, 2004. Retrieved 2016-08-05.
- ^ Krebs, Gunter Dirk (2016-04-21). "JCSat 10, 11, 12 (JCSat 3A, RA)". Gunter's Space Page. Retrieved 2016-07-20.
- ^ "Radio Regulatory Council Summary of Minutes (912th Meeting)" (PDF). Secretariat of the Radio Regulatory Council of Japan. December 13, 2006. Retrieved 2016-08-12.
- ^ "JCSAT 3". n2yo.com. Retrieved 2016-08-12.
