Geosynchronous Satellite Launch Vehicle
GSLV D5 lifts off carrying GSAT 14 satellite
|Function||Medium Lift Launch System|
|Country of origin||India|
|Cost per launch (2014)||Mk II ₹2.2 billion($36 million) |
|Height||49 metres (161 ft)|
|Diameter||2.8 metres (9 ft 2 in)|
|Mass||402,000 kilograms (886,000 lb)|
|2,000 to 2,500 kilograms (4,400 to 5,500 lb)|
|Launch sites||Satish Dhawan|
|Total launches||8 (6 Mk.I, 2 Mk.II)|
|Successes||3 (2 Mk.I, 1 Mk.II)|
|Failures||4 (3 Mk.I, 1 Mk.II)|
|Partial failures||1 (Mk.I)|
|First flight||Mk.I: 18 April 2001
Mk.II: 15 April 2010
|Boosters (Stage 0)|
|Engines||1 L40H Vikas 2|
|Thrust||680 kilonewtons (150,000 lbf)|
|Total thrust||2,720 kilonewtons (610,000 lbf)|
|Specific impulse||262 sec|
|Burn time||160 seconds|
|Thrust||4,700 kilonewtons (1,100,000 lbf)|
|Specific impulse||166 sec|
|Burn time||100 seconds|
|Engines||1 GS2 Vikas 4|
|Thrust||720 kilonewtons (160,000 lbf)|
|Specific impulse||295 s (2.89 kN·s/kg)|
|Burn time||150 seconds|
|Third Stage (GSLV Mk.I) - 12KRB|
|Thrust||69 kilonewtons (16,000 lbf)|
|Specific impulse||460 s (4.5 kN·s/kg)|
|Burn time||720 seconds|
|Third Stage (GSLV Mk.II) - CUS12|
|Thrust||73.5 kilonewtons (16,500 lbf)|
|Specific impulse||454 seconds (4.45 km/s)|
|Burn time||720 seconds|
Geosynchronous Satellite Launch Vehicle (abbreviated as GSLV) is an expendable launch system operated by the Indian Space Research Organisation (ISRO). It was developed to enable India to launch its satellites without dependence on foreign rockets and providers. GSLV has attempted eight launches to date, since its first launch in 2001 through its most recent launch in 2014.
The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian government 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 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 manoeuvre 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 September 2, 2007. Subsequently, the satellite was manoeuvred into geostationary orbit using its own propulsion system.
Two launches in 2010 failed; the first, in April 2010, was the first flight of the GSLV Mk.II, with an Indian-developed third stage engine replacing the Russian engine used on earlier flights. The third stage failed to ignite. The next launch, in December 2010, used the Russian engine, however the vehicle went out of control during first stage flight and was destroyed by range safety.
The 49 metres (161 ft) tall GSLV, with a lift-off mass of 415 tonnes (457 tons), is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is 7.8 metres (26 ft) long and 3.4 metres (11 ft) in diameter, protects the vehicle electronics and the spacecraft during its ascent through the atmosphere. It is discarded when the vehicle reaches an altitude of about 115 km.
GSLV employs S-band telemetry and C-band transponders for enabling vehicle performance monitoring, tracking, range safety / flight safety and preliminary orbit determination. The Redundant Strap Down Inertial Navigation System/Inertial Guidance System of GSLV housed in its equipment bay guides the vehicle from lift-off to spacecraft injection. The digital auto-pilot and closed loop guidance scheme ensure the required attitude manoeuvre and guide injection of the spacecraft to the specified orbit.
The GSLV can place approximately 5,000 kg (11,000 lb) into an easterly low Earth orbit. With the GSLV Mk.I, using the Russian 12KRB upper stage, with KVD-1 cryogenic rocket engine, GSLV can place 2,200 kg (4,900 lb) into an 18° geostationary transfer orbit. The GSLV Mk.II uses an indigenous cryogenic engine, the CE-7.5 in the third stage instead of the Russian cryogenic engine.
The first GSLV flight, GSLV-D1 used the L40 engine. Subsequent flights of the GSLV used high pressure engines in the strap-on boosters called the L40H. The GSLV uses four L40H liquid strap-on boosters derived from the L37.5 second stage, which are loaded with 40 tons of hypergolic propellants (UDMH & N2O4). The propellants are stored in tandem in two independent tanks 2.1 m diameter. The engine is pump-fed and generates 680 kN (150,000 lbf) of thrust, with a burn time of 149 seconds.
GSLV-D1 used the S125 stage which contained 125 tonnes of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage. The S139 stage is 2.8 m in diameter and has a nominal burn time of 109 seconds. The stage generates a maximum thrust of 4700 kN. .
The third stage of the GSLV Mk.II is propelled by the CE-7.5, an indigenous cryogenic rocket engine, 2.8 m in diameter and uses liquid hydrogen (LH2) and liquid oxygen (LOX) The indigenous cryogenic engine was built at the Liquid Propulsion Systems Centre in Mahendragiri, Tamil Nadu.
All GSLV launches have been conducted from the Satish Dhawan Space Centre in Sriharikota. The GSLV using the Russian Cryogenic Stage (CS) are designated as the GSLV Mk-I and the GSLV using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mk-II.
GSLV Mk I (a)
GSLV Mk I (b)
This variant had 139 t (S-139) first stage and improved fuel in the strap-on boosters & second stage. This variant can launch 1900 kg into geostationary transfer orbit.
GSLV Mk I (c)
This variant has a 15 tonne propellant loading in the third stage, called the C-15. GSLV-F06 (flight 6) is the only attempted launch of the Mark I(c) version to date.
GSLV Mk II
This variant uses an Indian cryogenic engine, the CE-7.5, and is capable of launching 2500 kg into geostationary transfer orbit. Previous GSLV vehicles (GSLV Mk.I) have used Russian cryogenic engines.
The Geosynchronous Satellite Launch Vehicle Mark III or the GSLV Mk-III is a three stage launch vehicle under development. The GSLV Mk-III is a three stage vehicle with a first stage consisting of two identical large solid boosters strapped onto the second liquid stage. The third stage is a cryogenic stage.
|Flight||Launch date/time (UTC)||Variant||Launch pad||Payload||Payload mass||Result||Notes|
|D1||18 April 2001
|Mk I(a)||First||GSAT-1||1540 kg||Failure||Developmental Flight, payload placed into lower than planned orbit, and did not have sufficient fuel to reach a usable orbit. ISRO claimed the launch to be successful and claims GSAT-1 as failure.|
|D2||8 May 2003
|Mk I(a)||First||GSAT-2||1825 kg||Success||Developmental Flight|
|F01||20 September 2004
|Mk I(b)||First||GSAT-3||1950 kg||Success||First operational flight|
|F02||10 July 2006
|Mk I(b)||Second||INSAT-4C||2168 kg||Failure||Both rocket and satellite had to be destroyed over the Bay of Bengal after the rocket's trajectory veered outside permitted limits.|
|F04||2 September 2007
|Mk I(b)||Second||INSAT-4CR||2160 kg||Partial failure||Apogee lower and inclination higher than expected, due to an error in the guidance subsystem. Eventually the 2160 kg payload reached the designated geostationary transfer orbit. Minor error in orbit inclination corrected by satellite mission operators. Satellite is fully operational and full design life of ten years will be achieved. It completed 6 years in orbit successfully  ISRO claims this GSLV flight to be successful.|
|D3||15 April 2010
|Mk II||Second||GSAT-4||2220 kg||Failure||First flight test of the ISRO designed and built Cryogenic Upper Stage. Failed to reach orbit due to malfunction of the Fuel Booster Turbo Pump (FBTP) of the cryogenic upper stage.|
|F06||25 December 2010
|Mk I(c)||Second||GSAT-5P||2130 kg||Failure||First flight of GSLV Mk.I (c) Destroyed by range safety officer after loss of control of liquid-fueled boosters.|
|D5||5 January 2014
|Mk II||Second||GSAT-14||1980 kg||Success||The flight was scheduled for 19 August 2013, but one hour and 14 minutes before the lift off, a leakage was reported and the launch was halted.
Second flight of GSLV with indigenous cryogenic upper stage (CUS) developed by ISRO's Liquid Propulsion Systems Centre (LPSC) was launched successfully on 5 January 2014. It was a launch with precision of 40 metres (130 ft). All the three stages performed successfully. This was the first successful flight of the cryogenic stage which was developed indigenously in India.
||Mk II||Second||GSAT-6||2100 kg|
||Mk II||Second||Chandrayaan 2||3200 kg (launch)|
||Mk II||Second||GSat 9||2330 kg|
||Mk II||Second||GSAT 10|
- Comparison of orbital launchers families
- Comparison of orbital launch systems
- Geosynchronous Satellite Launch Vehicle Mk III (LVM3)
- ISRO Orbital Vehicle
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