Amos-2
| Mission type | Communications |
|---|---|
| Operator | Spacecom |
| COSPAR ID | 2003-059A |
| SATCAT № | 28132 |
| Website | http://www.amos-spacecom.com/content.cfm?page=amos-2 |
| Mission duration | 12 years |
| Spacecraft properties | |
| Bus | AMOS |
| Manufacturer | IAI |
| Launch mass | 1,370 kilograms (3,020 lb) |
| Start of mission | |
| Launch date | 27 December 2003, 21:30:00 UTC[1] |
| Rocket | Soyuz-FG/Fregat |
| Launch site | Baikonur 31/6 |
| Contractor | Starsem |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Geostationary |
| Longitude | 4° west |
| Perigee | 35,778 kilometres (22,231 mi) |
| Apogee | 35,805 kilometres (22,248 mi) |
| Inclination | 0.07 degrees |
| Period | 23.93 hours |
| Epoch | 30 October 2013, 05:29:06 UTC[2] |
| Transponders | |
| Band | 28 Ku-band |
AMOS-2 is an Israeli commercial communication satellite, part of the AMOS series of satellites. The satellite was positioned at 4° W longitude in the geo-stationary orbit. it was launched at December 27, 2003 from Baikonur, Kazakhstan and it serves clients in three service regions: Middle East (including Israel), Europe and eastern coast of USA. Transmission and communication services given by this satellite include: direct distribution of TV and radio translations, TV and radio translations to communication centers, distribution of internet services, data transmissions to communication networks.
AMOS-2 carries 28 Ku-band transponders; 22 active with six as backups.[3]
With a mass of 1370 kg at launch, AMOS-2 incorporated a 400 newton Liquid Apogee Boost Motor (ABM) and fourteen 10 newton Reaction Control Thrusters for raising the satellite's orbit from Geostationary Transfer orbit to its final geostationary orbit as well as for its attitude control. It carried 450 kg of propellant (monomethyl hydrazine and MON-1).
AMOS-2 measures 11.5 m in length in its final in-orbit configuration. It is 3-axis body stabilised using Sun and Earth sensors, momentum and reaction wheels. Its solar array generates 1700W power, backed up by 24 A·h Ni-Cd batteries.
After its launch into Geo-synchronous transfer orbit by Soyuz, AMOS-2 was taken to its final geo-stationary orbit by firing the apogee boost motor in phases. After it reached the geo-stationary orbit, its antenna and solar Panels were deployed and the satellite was finally placed in its allocated slot of 4° W longitude.
Amos 2 and Amos 3 are placed in proximity to create common location, which enables to satellite users to increase user abilities without additional antennas.
See also
References
- ↑ McDowell, Jonathan. "Launch Log". Jonathan's Space Page. Retrieved 30 October 2013.
- ↑ "AMOS 2 Satellite details 2003-059A NORAD 28132". N2YO. 30 October 2013. Retrieved 30 October 2013.
- ↑ "AMOS 2". Gunter's Space Page. Retrieved 30 October 2013.
External links
- Amos by Spacecom
- International Media Switzerland Official provider's site
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