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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〔http://www.prl.res.in/~soxs-data〕 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 altitude control. It carried 840 kg of propellant (monomethyl hydrazine and MON-3). 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「GSAT-2」の詳細全文を読む スポンサード リンク
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