GSAT-2

Mission type	Communications
Operator	ISRO
COSPAR ID	2003-018A
SATCATno.	27807
Website	www.isro.org/satellites/gsat-2.aspx
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	SriharikotaFLP
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]
GSAT ← GSAT-1 GSAT-3 →

GSAT-2 was an experimental communication satellite built by theIndian Space Research Organisation (ISRO) and launched on one of the firstGSLVs. The satellite was positioned at48 deg east longitude in thegeo-stationary orbit.

GSAT-2 carried four C-band transponders, two K_u 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 440newton 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 itsattitude control. It carried 840 kg of propellant (monomethyl hydrazine andMON-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 24A·h Ni-Cd batteries.

After its launch into Geo-synchronous transfer orbit byGSLV-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.

• List of Indian satellites

• ISRO: GSAT-2

• Communications satellites in geostationary orbit
• Spacecraft launched in 2003
• GSAT satellites
• 2003 in India
• Spacecraft launched by GSLV rockets

• Articles with short description
• Short description is different from Wikidata