GSAT-2
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| Mission type | Communications |
|---|---|
| Operator | ISRO |
| COSPAR ID | 2003-018A |
| SATCAT no. | 27807 |
| Website | www |
| Mission duration | 3-5 years |
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| Spacecraft properties | |
| Bus | I-2K |
| Manufacturer | ISRO |
| Launch mass | 1,825 kilograms (4,023 lb) |
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| Start of mission | |
| Launch date | Template:Start-date UTC[1] |
| Rocket | GSLV Mk.I D2 |
| Launch site | Sriharikota FLP |
| Contractor | ISRO |
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| 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] |
| Template:Succession links Template:Succession links | |
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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.
Payloads
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:
- Total Radiation Dose Monitor (TRDM) to compare the estimated radiation doses inside the satellite with the directly measured radiation doses using a Radiation Sensitive Field Effect Transistor (RADFET)
- Surface Charge Monitor (SCM) to indicate the state of the charging environment in the vicinity of the spacecraft
- Solar X-ray Spectrometer (SOXS) to study the solar flare emission in 4 keV - 60 keV[3] energy range using state of the art semiconductor devices and Phoswich Scintillation Detector
- Coherent Radio Beacon Experiment (CRABEX) to investigate the spatial structure, dynamic and temporal variations of Ionosphere and several aspects of equatorial electrodynamics
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).
Measurements
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.
Positioning
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.
See also
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References
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- ^ Page Module:Citation/CS1/styles.css has no content.McDowell, Jonathan. "Launch Log". Jonathan's Space Page. Retrieved 30 October 2013.
- ^ Page Module:Citation/CS1/styles.css has no content."GSAT 2 Satellite details 2003-018A NORAD 27807". N2YO. 29 October 2013. Retrieved 30 October 2013.
- ^ Page Module:Citation/CS1/styles.css has no content."Solar X-Ray Spectrometer (SOXS) Home Page". Archived from the original on 2016-03-04. Retrieved 2010-04-29.
External links
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