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Geosynchronous Satellite Launch Vehicle
Geosynchronous Satellite Launch vehicle is the latest rocket which can be used to launch the Geo satellites, EDUSAT, and other etc, into the outer space of earth (Space). These rockets are designed and manufactured by ISRO in India. This GSLV project was initiated and developed from the year of 1990 by Indian government. The first GSLV rocket was launched for GSAT-1 on 18 April in 2001, but it was failed due to unsuccessfully to reaches the correct orbit.
Totally, Nine (9) GSLV rockets are launched by ISRO for satellite launching. 4 GSLV rockets are failed (3 Mk.I, 1 Mk. II), 4 GSLV rockets are successful (2 Mk.I, 1 Mk.II, MGSLV-III) and 1 GSLV rocket was partial failure of Mk.I
The following are GSLV rockets launched by ISRO in India.
- GSLV-D1 was launched on 18 April 2001 for carrying GSAT-1. (failed)
- GSLV-D2 was launched on 08 May 2003 for carrying GSAT-2. (success)
- GSLV-F01 was launched on 20 September 2004 for carrying GSAT-3. (Success)
- GSLV-F02 was launched on 10 July 2006 for carrying INSAT-4C. (failed)
- GSLV-F04 was launched on 02 September 2007 for carrying INSAT-4CR. (partial failed)
- GSLV-D3 was launched on 15 April 2010 for carrying GSAT-04. (failed)
- GSLV-F06 was launched on 25 December 2010 for carrying GSAT-5P. (failed)
- GSLV-D5 was launched on 05 January 2014 for carrying GSAT-14. (success)
- GSLV-X1 was launched on 18 December 2014 for testing of sub orbital flight and also the simulate the weight and attributes of C-25. (success)
There are two specifications of payload, they are
Payload to GTO:
Its weight upto 2500kgs, GSLV's primary payloads are INSAT class of communication satellites that operate from geostationary orbits and hence are placed in Geosynchronous Transfer Orbits by GSLV.
Payload to LEO:
Its weight upto 5000kgs Further, GSLV's capability of placing up to 5 tonnes in Low Earth Orbits broadens the scope of payloads from heavy satellites to multiple smaller satellites.
GSLV Vehicle Description
GSLV vehicle having dimensions as follows as.
- Height : 49.13 meters (161.21 ft )
- Diameter : 2.8 meters (9 ft 2 inches)
- Mass : 414,750 kilograms (914,370 lb)
These vehicle was empolyed by s-band telemetry and C-band transponders for enable to performance monitoring, tracking, range safety / flight safety and preliminary orbit determination of GSLV.
This vehicle having the three stages to complete the mission while launching the rockets.
- Booster stage
- Core stage
- Upper stage
Booster stage is first stage of GSLV rocket. It can be employed by either solid or liquid booster. It liquid booster are used to launch then the minimum 4 engine’s required to lift-off from the ground. It solid booster are used to launch then the minimum 2 engine’s required to lift-off from the ground. In this GSLV, four L4OH liquid Strap on booster, which in load of 40 tons of hyperbolic propellants (UDMH&N2O5). These propellants are stores in tandem in two independents tanks 2.1 meters diameter. These propellants are pump-fed by the engine and generator 680KN of thrust with a burn time of 149 seconds.
Core stage is the second stage of GSLV. It is employed by vikas engine and it has 2.8m diameters. This core stage was activated after reaches certain height from ground level by separated the boosters from the rocket. The vikas engine was worked by UH25/N2O4 fuel (propellant) with burn time of 200sec which produces by 1598 KN of thrust.
Vikas engine is also called as the liquid fuel rocket engine. Which is built by Indian space research organization (ISRO) in the year of 1970’s. Nimbi narayanan developed the vikas engine with his team. It is mostly used in the pole satellite launch vehicle (PSLV)and geosynchronous satellite launch vehicle(GSLV).
This engine is used in the second stage of the PSLV and GSLV launch vehicle,with four strap-on boosters. The engine is also capable of gambling. It is used upto 40mertic tons of UDMH Fuel. It is similar to Viking engine.
Upper stage is the last stage of GSLV. This launches the satellite from it. This upper stage was employed by the different engines like C-25, KVD, CE-7.5 etc… these engines are activated after reaches particulars height which compatible to satellite from ground. In this stage, LOV/LH2 propellant was used as a fuel in engine with the 720seconds of burn time and produces 186kms of thrust.
© 2015 KALYAN CHAKRAVARTHY THADAKA