Geosynchronous Satellite Launch Vehicle Mk III
GSLV mk-3 sub-orbital experiment test flight from Satish Dhawan Space Centre
|Function||Mid-Heavy lift launch vehicle|
|Manufacturer||Indian Space Research Organisation|
|Country of origin||India|
|Height||43.43 m (142.5 ft)|
|Diameter||4.0 m (13.1 ft)|
|Mass||630,580 kg (1,390,190 lb)|
LEO (600 km)
|8,000 kg (18,000 lb)|
|4,000 kg (8,800 lb)|
|Launch sites||Satish Dhawan Space Centre SLP, Andhra Pradesh, India|
|Total launches||1 (2 stage version)|
|Successes||1 (2 stage version)|
|First flight||18 December 2014 (2 stage version; sub-orbital flight)
2016 (full version)
|Booster Stage - S-200|
|Length||25.75 m (84.5 ft)|
|Diameter||3.2 m (10 ft)|
|Empty mass||31,000 kg (68,000 lb)|
|Gross mass||238,000 kg (525,000 lb)|
|Thrust||5,150 kN (525 tf) each|
|Specific impulse||274.5 (vacuum)|
|Burn time||130 sec|
|Core Stage - L-110|
|Length||21.26 m (69.8 ft)|
|Diameter||4.0 m (13.1 ft)|
|Empty mass||10,600 kg (23,400 lb)|
|Gross mass||125,600 kg (276,900 lb)|
|Thrust||1,598 kN (163.0 tf)|
|Specific impulse||293 sec|
|Burn time||200 sec|
|Upper Stage - C-25|
|Length||13.32 m (43.7 ft)|
|Diameter||4.0 m (13.1 ft)|
|Empty mass||3,300 kg (7,300 lb)|
|Gross mass||18,300 kg (40,300 lb)|
|Thrust||186 kN (19.0 tf)|
|Specific impulse||450 sec|
|Burn time||720 sec|
The GSLV-III or Geosynchronous Satellite Launch Vehicle Mark III (Hindi: भूस्थिर उपग्रह प्रक्षेपण यान एमके-३; also called LVM3) is a launch vehicle developed by the Indian Space Research Organisation (ISRO).
It is intended to launch satellites into geostationary orbit and as a launcher for an Indian crew vehicle. The GSLV-III features an Indian cryogenic third stage and a higher payload capacity than the current GSLV.
- 1 History
- 2 Vehicle description
- 3 Scheduled launches
- 4 Comparable rockets
- 5 See also
- 6 References
- 7 External links
Development for the GSLV-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-III launcher, with a passive cryogenic third stage, was successfully carried out on 18 December 2014, and was 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 ballistic and safety 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.
Suborbital flight test
The GSLV-III lifted off from the second launch pad, Sriharikota, at 9.30 am IST on 18 December 2014. The 630.5 tonne rocket had two active solid and liquid propulsion stages (S 200 and L110 respectively) in addition to its cryogenic engine C 25 X (which was in a passive state). The sole payload was an unmanned Crew Module. GSLV-III has the capability to launch its heavier INSAT class satellites and manned missions to space. The main purpose of this mission, however, is to test the atmospheric flight stability of the rocket with around four tonnes of payload.
Crew module reentry
Just over five minutes into the flight, the rocket ejected the cup-cake shaped 3.7-tonne Crew Module Atmospheric Re-entry Experiment (CARE) at an altitude of 126 km. CARE then descended at high speed. The speed was controlled by remotely manipulating its onboard motors till it reached an altitude of 80 km. From here the ballistic re-entry into the atmosphere began while the onboard thrusters were shut down. CARE’s heat shield was expected to experience a temperature of around 1600 °C. At an altitude of around 15 km, the module’s apex cover separated and the parachutes were deployed. CARE splashed down in the Bay of Bengal near the Andaman and Nicobar Islands
Stage 1 – solid boosters
The GSLV-III uses S-200 solid motors, also designated Large Solid Boosters (LSB). Each booster has a diameter of 3.2 metres, a length of 25 metres, and carries 200 tonnes of propellant. These boosters burn for 130 seconds and produce a peak thrust of about 5,150 kilonewtons (525 tf) each.
A separate facility has been established at Sriharikota to make the S200 boosters. Another major feature is that the S200’s large nozzle has been equipped with a ‘flex seal.’ The nozzle can therefore be swivelled when the rocket’s orientation needs correction.
Stage 2 – liquid motor
The core stage, designated L-110, is a 4-meter-diameter liquid-fueled stage carrying 110 tonnes of propellant. It is the first Indian liquid-engine cluster design, and uses 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 uses regenerative cooling, providing improved weight and specific impulse, compared to earlier rockets. The L-110 core stage ignites 113 seconds after liftoff and burns for about 200 seconds.
In flight, as the thrust from the S200 boosters begins to tail off, the decline in acceleration is sensed by the rocket’s onboard sensors and the twin Vikas engines on the ‘L110’ liquid propellant core stage are then ignited. Before the S200s separate and fall away from the rocket, the solid boosters as well as the Vikas engines operate together for a short period of time.
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-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 has a diameter of 5 metres (16 ft) and a payload volume of 110 cubic metres (3,900 cu ft).
|Flight||Launch date/time (UTC)||Variant||Launch Pad||Payload||Payload Mass||Result||Note(s)|
|X||18 December 2014
|LVM3-X||Second||Crew Module Atmospheric Re-entry Experiment (CARE)||3,775 kg||Success||Sub-orbital development test flight
This flight carries a non functional version of the cryogenic upper stage C-25 to simulate its weight and attributes.
The launch of LVM3 vehicle on 18 December was successful, with both the launch vehicle and the CARE module meeting the parameters of the mission.
|D1||Early 2017||Mk III||Second||GSAT-19E||3,500 kg||For launching new generation GSAT weighing about 3.5MT.
Will have the fully functional cryogenic stage.
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- Geosynchronous Satellite Launch Vehicle
- ISRO Orbital Vehicle
- Polar Satellite Launch Vehicle
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We will be checking the crew capsule for all parameters.
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