GSLV III

GSLV III

infobox rocket
name = Geosynchronous Satellite Launch Vehicle Mk.III


imsize = 200px
caption = Geosynchronous Satellite Launch Vehicle III
function = Medium-heavy launch vehicle
manufacturer = ISRO
country-origin = IND
height = 42.4 m
diameter = TBC
mass = TBC
stages = 3
LEO-payload = 10,000-20,000 Kg
payload-location = GTO
payload = 4,000-8,000 Kg
status = In Development
sites = Satish Dhawan Space Centre
first=Scheduled for 2008Fact|date=January 2008
boosters = 2
boostername = S-200
boosterengines = 1 Solid
boosterfuel = Solid
boosterthrust = 7700 kN
alt-boosterthrust = 785 tf
boostertime = TBC
stage1name = L-110
stage1engines =2 Vikas
stage1thrust = 735 kN
alt-stage1thrust = 785 Tf
stage1fuel = Liquid (TBC)
stage1time = TBC
stage2name = C-25
stage2engines = TBC
stage2time = TBC
stage2thrust = 196 kN
alt-stage2thrust = 20 Tf
stage2fuel = 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. [ [http://www.hindu.com/thehindu/holnus/008200708050320.htm Cryogenic stage tested on the ground] ]

The maiden flight is scheduled for 2008.

tages

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.

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.

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.

ummary

* Overall length: 42.4 m
* Lift-off mass: 630 t
* Number of stages: 3
* Payload: 10-20 tonnes to LEO or 4-8 tonnes to GTO (approx)
* Launch Orbit: Geosynchronous Transfer Orbit (GTO) 180 x 36,000 km

Comparable Rockets

*Ariane 5
*Delta IV (Heavy)
*Long March 5
*Atlas V
*H-IIB
*Proton
*Angara A5
*Falcon 9

References

ee also

Indian Space Research Organisation(ISRO)

Comparison Of Mid-Heavy Lift Launch Systems

Polar Satellite Launch Vehicle

Geosynchronous Satellite Launch Vehicle

External links

* [http://www.bharat-rakshak.com/SPACE/space-launchers-gslv.html#gslvmk3 Bharat-Rakshak GSLV-III information]
* [http://www.newscientist.com/special/india/mg18524871.000 New Scientist article including GSLV-III diagram]

References


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