Engineering:JCSAT-3
| 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 |
JCSAT constellation | |
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]
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).[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]
History
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]
References
- ↑ 1.0 1.1 "Trajectory: JCSAT 3 1995-043A". NASA. 10 February 2021. https://nssdc.gsfc.nasa.gov/nmc/spacecraft/displayTrajectory.action?id=1995-043A.
This article incorporates text from this source, which is in the public domain.
- ↑ 2.0 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 Krebs, Gunter (2016-04-21). "JCSat 3, 4 (JCSat R) → Intelsat 26". Gunter's Space Page. http://space.skyrocket.de/doc_sdat/jcsat-3.htm.
- ↑ "Hughes Built JCSAT-4 To Boost Services In Pacific Rim". February 14, 1997. http://community.warunasat.com/showthread.php?tid=1580&pid=14307#pid14307.
- ↑ 4.0 4.1 "History". SKY Perfect JSAT. http://www.skyperfectjsat.co.jp/en/about/history.html.
- ↑ "JSAT Corporation Awards Lockheed Martin Contract For Second A2100 Satellite". Lockheed Martin Space Systems. April 20, 2004. http://www.icaa.eu/lockheed-martin/2004/04/20/jsat-corporation-awards-lockheed-martin-contract-second-a2100-satellite/.
- ↑ Krebs, Gunter (2016-04-21). "JCSat 10, 11, 12 (JCSat 3A, RA)". Gunter's Space Page. http://space.skyrocket.de/doc_sdat/jcsat-10.htm.
- ↑ "Radio Regulatory Council Summary of Minutes (912th Meeting)". Secretariat of the Radio Regulatory Council of Japan. December 13, 2006. http://www.soumu.go.jp/main_sosiki/joho_tsusin/eng/councilreport/pdf/061213_1.pdf.
- ↑ "JCSAT 3". N2YO.com. http://www.n2yo.com/?s=23649.
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