GSLV III
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This article or section documents a scheduled or expected spaceflight. Details may change as the launch date approaches or more information becomes available. |
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| Geosynchronous Satellite Launch Vehicle Mk.III | |
 Geosynchronous Satellite Launch Vehicle III |
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| Fact sheet | |
|---|---|
| Function | Medium-heavy launch vehicle |
| Manufacturer | ISRO |
| Country of origin |  India |
| Size | |
| Height | 42.4 m |
| Diameter | TBC |
| Mass | TBC |
| Stages | 2 |
| Capacity | |
| Payload to LEO | 10,000 kg |
| Payload to GTO |
4,000-6000 kg |
| Launch History | |
| Status | In development |
| Launch sites | Satish Dhawan Space Centre |
| Maiden flight | Scheduled for 2008[citation needed] |
| Boosters (Stage 0) - S-200 | |
| No boosters | 2 |
| Engines | 1 Solid |
| Thrust | 7700 kN (785 tf) |
| Burn time | TBC |
| Fuel | Solid |
| First Stage - L-110 | |
| Engines | 2 Vikas |
| Thrust | 735 kN (785 Tf) |
| Burn time | TBC |
| Fuel | Liquid (TBC) |
| Second Stage - C-25 | |
| Engines | TBC |
| Thrust | 196 kN (20 Tf) |
| Burn time | TBC |
| Fuel | LOX/LH2 |
The GSLV-III or Geosynchronous Satellite Launch Vehicle mark III is a launch vehicle currently under development by the Indian Space Research Organization. It is intended to launch heavy satellites into geostationary orbit, and will allow India to become less dependent on foreign rockets for heavy lifting.
The rocket is the technological successor to the GSLV, however is not derived from its predecessor. There is no GSLV-II - the GSLV-I has a Russian-made cryogenic third stage, which was to be replaced with an identical Indian-built one for the GSLV-II. US objections based on the Missile Technology Control Regime (MTCR) prevented the Russia-India technology transfer that would have enabled this, leading to cancellation of the GSLV-II. The GSLV-III will use an Indian-developed cryogenic engine.[1]
The maiden flight is scheduled for 2008.
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[edit] Stages
[edit] Boosters
The boosters used on the GSLV-III will be the S200, which is also designated Large Solid Booster, or LSB, which is a solid propellant stage with a mass of 200 tonnes. Two boosters will be used. Each has a diameter of 3.4 metres and a length of 25 metres. They are estimated to produce 785 tonnes-force (7.70 MN) of thrust.
[edit] Core stage
The core stage will be the L110 restartable liquid stage which has 110 tonnes of liquid propellant and a diameter of 4-metres. It will be the first Indian liquid engine cluster design, and will use two improved Vikas engines, each producing 75 tonnes (735 kN) of thrust. The improved Vikas engine will use regenerative cooling, providing improved weight and specific impulse, compared to earlier rockets.
[edit] Upper stage
The upper stage will be the C25, which is a restartable cryogenic stage fuelled by 25 tonnes of liquid oxygen and liquid hydrogen. It has a 4-metre diameter and is 8.2 metres long. The stage will produce 20 tonnes (197 kN) of thrust.
[edit] Summary
- Overall length: 42.4 m
- Lift-off mass: 630 t
- Number of stages: 3
- Payload: 10 t to LEO or 4-6 t to GTO (approx)
- Launch Orbit: Geosynchronous Transfer Orbit (GTO) 180 x 36,000 km
[edit] Comparable Rockets
[edit] References
[edit] See also
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