Türksat 1C
| Mission type | Communication |
|---|---|
| Operator | Türksat |
| COSPAR ID | 1996-040B |
| SATCAT № | 23949 |
| Mission duration | 14 years |
| Spacecraft properties | |
| Bus | Spacebus 2000 |
| Manufacturer | Aérospatiale |
| Launch mass | 1,062 kg (2,341 lb) |
| Power | 2,800 watts |
| Start of mission | |
| Launch date | July 9, 1996 |
| Rocket | Ariane 44L H10-3 |
| Launch site | Kourou ELA-2 |
| End of mission | |
| Deactivated | October 3, 2010 |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Geostationary |
| Longitude | 31.3°E |
| Perigee | 35,802.6 kilometres (22,246.7 mi) |
| Apogee | 35,835.7 kilometres (22,267.3 mi) |
| Period | 1,437.4 minutes |
| Transponders | |
| Band | 16 Ku band + 8 backup |
| Bandwidth | 9×36 MHz 2×54 megahertz 5×72 megahertz |
| EIRP | 53 dBW west spot: Europa & Turkey 53 decibel-watts east spot: Asia & Turkey |
Türksat 1C was a Turkish communications satellite as part of a project to form an instant network with two geosynchronous satellites that is supervised by the companies Türksat A.Ş. in Turkey and Aérospatiale of France.
Türksat 1C was launched by Arianespace atop an Ariane-44L H10-3 launch vehicle along with Saudi Arabian satellite Arabsat-2A in a dual-payload launch on July 9, 1996 from ELA-2 at the Guiana Space Centre in Kourou, French Guiana. It was built under the insurance terms of the turnkey system contract to replace the first Turkish satellite Türksat 1A, which was lost following a launch failure on January 24, 1994. The contract was modified so that the coverage area of Türksat 1C was enlarged by two big zones.
Turksat 1C was successfully placed into geostationary transfer orbit and positioned at 31.3°E on July 10, 1996. Completing the orbital tests, the satellite shifted to longitude 42°E. After this process, which took 17 days, the broadcast traffic of the Türksat 1B was transferred to Türksat 1C. Finally, when these processes completed Türksat 1B was positioned at 31.3°E following similar orbital manoeuvres.
Turksat 1C was designed for covering Turkey and Europe on west spot by vertical emission and Turkey and Central Asia on east spot by horizontal emission so as to serve simultaneously between Europe, Turkey and Central Asia, and to provide direct connection between Europe and Central Asia. It is based on the Aerospatiale Spacebus 2000 series having an on-orbit mass of 1,062 kg (2,341 lb). The communications payload consists of 16 Ku band transponders with eight backup, nine with 36Mhz, two with 54Mhz and five 72Mhz bandwidth.
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