Geosynchronous Satellite Launch Vehicle Mk III
Model of Geosynchronous Satellite Launch Vehicle III
|Function||Medium lift launch vehicle|
|Country of origin||India|
|Height||42.4 m (139 ft)|
|Diameter||4.0 m (13.1 ft)|
|Mass||630,000 kg (1,390,000 lb)|
|10,000 kg (22,000 lb)|
|4,000 kg (8,800 lb)-5,000 kg (11,000 lb)|
|Launch sites||Satish Dhawan Space Centre, Andhra Pradesh, India|
|First flight||Scheduled for 2014|
|Booster Stage - S-200|
|Length||21.9 m (72 ft)|
|Diameter||3.2 m (10 ft)|
|Thrust||5,150 kN (525 tf) each|
|Specific impulse||227 (sea level)
|Burn time||130 sec|
|Core Stage - L-110|
|Length||17 m (56 ft)|
|Diameter||4 m (13 ft)|
|Thrust||1,400 kN (140 tf)|
|Specific impulse||281 sec |
|Burn time||200 sec|
|Upper Stage - C-25|
|Thrust||200 kN (20 tf)|
|Specific impulse||450 sec|
|Burn time||580 sec|
The GSLV-III or Geosynchronous Satellite Launch Vehicle Mark III is a launch vehicle under development by the Indian Space Research Organisation. It is intended to launch satellites into geostationary orbit and as a launcher for an Indian crew vehicle. The GSLV MK-3 will feature an Indian cryogenic third stage and a higher payload capacity than the current GSLV.
Development for the GSLV Mk III began in the early 2000s, with the first launch planned for 2009-2010. Several factors have delayed the program, including the 15 April 2010 failure of the ISRO-developed cryogenic upper stage on the GSLV Mk II.
A suborbital flight test of the GSLV Mk3 launcher, without its cryogenic third stage, is planned by end of 2014, and will be used to test a crew module on a suborbital trajectory. The first orbital flight is planned to take place in 2016. The first flight with a crew on board would take place after 2020.
S-200 Static test
The S-200 solid rocket booster was successfully tested on 24 January 2010. The booster fired for 130 seconds and generated a peak thrust of about 500 tonnes. Nearly 600 health parameters were monitored during the test and indicated normal performance. A second successful static test was conducted on 4 September 2011.
L-110 Static test
The Indian Space Research Organisation conducted the first static test of the L110 core stage at its Liquid Propulsion Systems Centre (LPSC) test facility at Mahendragiri, Tamil Nadu on 5 March 2010. Originally targeted for a full 200 second burn, the test was terminated at 150 seconds after a leakage in a control system was detected. On 8 September 2010 ISRO successfully conducted a full 200 second test.
Stage 1 - Solid boosters
The GSLV-III will use two S-200 solid motors, also designated Large Solid Boosters (LSB). Each booster will have a diameter of 3.2 metres, a length of 25 metres, and will contain 200 tonnes of propellant. These boosters burn for 130 seconds and produce a peak thrust of about 5,150 kilonewtons (525 tf) each.
Stage 2 - Liquid motor
The core stage, designated L-110, will be a 4-meter diameter liquid-fueled stage containing 110 tonnes of propellant. It will be the first Indian liquid engine cluster design, and will use two improved Vikas engines, each producing about 700 kilonewtons (70 tf) of thrust and burning UH 25 (75%UDMH, 25% hydrazine) and N2O4. The improved Vikas engine will use regenerative cooling, providing improved weight and specific impulse, compared to earlier rockets. The L-110 core stage will ignite 113 seconds after liftoff and burn for about 200 seconds.
Stage 3 - Cryogenic upper stage
The cryogenic upper stage is designated the C-25 and will be powered by the Indian-developed CE-20 engine burning LOX and LH2, producing 20 tonnes-force (200 kN) of thrust. The C-25 will be 4 metres (13 ft) in diameter and 8.2 metres (27 ft) long, and contain 25 tonnes of propellant.
This engine is slated for completion and testing by 2015, it will then be integrated with the C-25 stage and be put through a series of tests. The first C-25 stage will be used on the GSLV MK-III D-1 mission in early 2017. This mission will put in orbit the GSAT-19E communication satellite. Work on the C-25 stage and CE-20 engine for GSLV Mk-III upper stage was initiated in 2003, the project has been subject to many delays due to problems with ISRO's smaller cryogenic engine, the CE-7.5 for GSLV MK-II upper stage.
The payload fairing will have a diameter of 5 metres (16 ft) and a payload volume of 100 cubic metres (3,500 cu ft).
|Flight||Launch date/time (UTC)||Variant||Launch Pad||Payload||Payload Mass||Note(s)|
|X1||December 2014||Mk III||Second||Crew Module (Boilerplate)||kg||Sub-orbital development test flight|
|E1||Late 2015-Early 2016||Mk III||Second||GSAT-19E||kg||Orbital first operational flight|
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- Geosynchronous Satellite Launch Vehicle
- ISRO Orbital Vehicle
- Indian Space Research Organisation (ISRO)
- Polar Satellite Launch Vehicle
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- Bharat-Rakshak GSLV-III information
- New Scientist article including GSLV-III diagram