GSAT-2

In this article, we will explore GSAT-2 from different perspectives, analyzing its impact on today's society and its relevance in history. With a critical and objective look, we will address the most important aspects related to GSAT-2, delving into its origins, evolution and development over time. Through a thorough analysis, we will unravel the different concepts and theories that revolve around GSAT-2, with the purpose of providing a comprehensive understanding of its importance in the contemporary context. In addition, we will examine the implications and effects that GSAT-2 has had in various areas, thus allowing a broad and detailed vision of its significance today.

GSAT-2
Mission typeCommunications
OperatorISRO
COSPAR ID2003-018A Edit this at Wikidata
SATCAT no.27807
Websitewww.isro.org/satellites/gsat-2.aspx
Mission duration3-5 years
Spacecraft properties
BusI-2K
ManufacturerISRO
Launch mass1,825 kilograms (4,023 lb)
Start of mission
Launch date8 May 2003, 11:28 (2003-05-08UTC11:28Z) UTC[1]
RocketGSLV Mk.I D2
Launch siteSriharikota FLP
ContractorISRO
Orbital parameters
Reference systemGeocentric
RegimeGeostationary
Longitude47.95° east
Perigee altitude35,904 kilometres (22,310 mi)
Apogee altitude35,920 kilometres (22,320 mi)
Inclination2.43 degrees
Period24.03 hours
Epoch29 October 2013, 19:06:36 UTC[2]
← GSAT-1
GSAT-3 →

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

References

  1. ^ McDowell, Jonathan. "Launch Log". Jonathan's Space Page. Retrieved 30 October 2013.
  2. ^ "GSAT 2 Satellite details 2003-018A NORAD 27807". N2YO. 29 October 2013. Retrieved 30 October 2013.
  3. ^ "Solar X-Ray Spectrometer (SOXS) Home Page". Archived from the original on 2016-03-04. Retrieved 2010-04-29.