Geosynchronous Satellite Launch Vehicle
Artist representation of GSLV Mk II.
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| Function | Medium Lift Launch System |
|---|---|
| Manufacturer | ISRO |
| Country of origin | India |
| Cost per launch | Mk II ₹2.2 billion($36 million) |
| Size | |
| Height | 49.13 metres (161.2 ft) |
| Diameter | 2.8 metres (9 ft 2 in) |
| Mass | 414,750 kilograms (914,370 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | 5,000 kilograms (11,000 lb) |
| Payload to GTO | 2,500 kilograms (5,500 lb) |
| Launch history | |
| Status |
|
| Launch sites | Satish Dhawan |
| Total launches | 10 (6 Mk.I, 4 Mk.II) |
| Successes | 5 (2 Mk.I, 3 Mk.II) |
| Failures | 4 (3 Mk.I, 1 Mk.II) |
| Partial failures | 1 (Mk.I) |
| First flight |
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| Last flight |
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| Boosters | |
| No. boosters | Four |
| Engines | 1 L40H Vikas 2 |
| Thrust | 760 kN (170,000 lbf) |
| Total thrust | 3,040 kN (680,000 lbf) |
| Specific impulse | 262 s (2.57 km/s) |
| Burn time | 160 seconds |
| Fuel | N2O4/UDMH |
| First stage | |
| Engines | 1 S139 |
| Thrust | 4,700 kN (1,100,000 lbf) |
| Specific impulse | 237 s (2.32 km/s) |
| Burn time | 100 seconds |
| Fuel | HTPB (solid) |
| Second stage | |
| Engines | 1 GS2 Vikas 4 |
| Thrust | 800 kN (180,000 lbf) |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 150 seconds |
| Fuel | N2O4/UDMH |
| Third stage (GSLV Mk.II) - CUS12 | |
| Engines | 1 CE-7.5 |
| Thrust | 75 kN (17,000 lbf) |
| Specific impulse | 454 s (4.45 km/s) |
| Burn time | 720 seconds |
| Fuel | LOX/LH2 |
Geosynchronous Satellite Launch Vehicle (Hindi: भूस्थिर उपग्रह प्रक्षेपण यान), abbreviated in English as GSLV, is an expendable launch system operated by the Indian Space Research Organisation (ISRO). GSLV has been used in ten launches to date, since its first launch in 2001 through to its most recent launch on September 8, 2016 of the INSAT-3DR.
The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites. India has depended on the United States and Europe for the launch of INSAT class of satellites.
GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launchers in the form of the S125/S139 solid rocket booster and the liquid-fueled Vikas engine. The third stage was procured from Russian company Glavcosmos based on an agreement signed in 1991. Russia backed out of the deal after US sanctions were imposed in May 1992. ISRO started the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic stage. Russia agreed to sell 7 cryogenic stages and 1 ground mock-up stage instead of 5 cryogenic stages and the technology to build the stages.
The first development flight of GSLV Mk.I (GSLV-D1) was launched on 18 April 2001. The flight carrying GSAT-1 failed to reach the correct orbit. Attempts to save GSAT-1 by using its own propulsion system to maneuver it into the correct orbit were unsuccessful as it ran out of fuel several thousand kilometres below geosynchronous orbit.
The GSLV became operational after a second development flight, which successfully placed GSAT-2 in 2003. In its first operational flight in September 2004, GSLV launched EDUSAT - India's first dedicated satellite for educational services. However, the second operational flight, GSLV F02, conducted on July 10, 2006 did not succeed in placing the satellite INSAT-4C into orbit.
GSLV F04 is the fifth flight of India's Geosynchronous Satellite Launch Vehicle (GSLV), launched INSAT-4CR satellite, into a geosynchronous transfer orbit (GTO) of 170 km perigee and 35,975 km apogee with an orbital inclination of 21.7° with respect to the equator on 2 September 2007. Subsequently, the satellite was maneuvered into geostationary orbit using its own propulsion system.
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