 | |
| Mission type | Communications |
|---|---|
| Operator | ISRO |
| COSPAR ID | 2003-018A  |
| SATCAT no. | 27807 |
| Website | www |
| Mission duration | 3-5 years |
| Spacecraft properties | |
| Bus | I-2K |
| Manufacturer | ISRO |
| Launch mass | 1,825 kilograms (4,023 lb) |
| Start of mission | |
| Launch date | 8 May 2003, 11:28 (2003-05-08UTC11:28Z) UTC[1] |
| Rocket | GSLV Mk.I D2 |
| Launch site | Sriharikota FLP |
| Contractor | ISRO |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Geostationary |
| Longitude | 47.95° east |
| Perigee altitude | 35,904 kilometres (22,310 mi) |
| Apogee altitude | 35,920 kilometres (22,320 mi) |
| Inclination | 2.43 degrees |
| Period | 24.03 hours |
| Epoch | 29 October 2013, 19:06:36 UTC[2] |
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← GSAT-1
GSAT-3 →
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GSAT-2 was an experimental communication satellite built by the Indian Space Research Organisation (ISRO) and launched on one of the first GSLVs. The satellite was positioned at 48 deg east longitude in the geo-stationary orbit.
GSAT-2 carried four C-band transponders, two Ku band transponders and a Mobile Satellite Service (MSS) payload operating in S-band forward link and C-band return link. Besides the communication payloads, GSAT-2 carried the following four piggyback experimental payloads:
Weighing 1800 kg at launch, GSAT-2 incorporated a 440 newton Liquid Apogee Motor (LAM) and sixteen 22 newton Reaction Control Thrusters for raising the satellite's orbit from Geo-stationary Transfer orbit to its final geo- stationary orbit as well as for its attitude control. It carried 840 kg of propellant (monomethyl hydrazine and MON-3).
GSAT-2 measures 9.55 m in length in its final in-orbit configuration. It is 3-axis body stabilised using Sun and Earth sensors, momentum and reaction wheels, magnetic torquers and bi-propellant thrusters. Its solar array generates 1380 W power, backed up by two 24 A·h Ni-Cd batteries.
After its launch into Geo-synchronous transfer orbit by GSLV-D2, GSAT-2 it was taken to its final geo-stationary orbit by firing the liquid apogee 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 48° east longitude.
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Launches are separated by dots ( • ), payloads by commas ( , ), multiple names for the same satellite by slashes ( / ). | |
