Geosynchronous Satellite Launch Vehicle (GSLV) - Mark I & II, is capable of placing INSAT–II class of satellites (2000 – 2,500 kg) into Geosynchronous Transfer Orbit (GTO). GSLV is a three stage vehicle GSLV is 49 m tall, with 414 t lift off weight. It has a maximum diameter of 3.4 m at the payload fairing. First stage comprises S125 solid booster with four liquid (L40) strap-ons. Second stage (GS2) is liquid engine and the third stage (GS3) is a cryo stage. The vehicle develops a lift off thrust of 6573 kn.
The first flight of GSLV took place from SHAR on April 18, 2001 by launching 1540 kg GSAT-1. It was followed by four more launches , GSLV-D2 on May 8, 2003 (GSAT-2 1825 kg), GSLV-F01 on September 20, 2004 (EDUSAT 1950 kg), GSLV-F02 on July 10, 2006 and GSLV-F04 on September 2, 2007 (INSAT-4CR 2130 kg).
GSLV MK-II
GSLV MK II, earlier referred to as GSLV D3, will carry an Indian developed cryogenic third stage which will eventually be capable of launching 2,500 kg into Geostationary Transfer Orbit (GTO). The cryogenic engines that have powered the GSLV rocket so far were sold to India by Russia. Of the seven cryogenic engines supplied, five have now been used. Eventually, all future GSLV's will use the Indian Cryogenic Upper Stage (CUS) that develops 9 ton of thrust against 7.5 ton of the Russian CUS and carries 15 ton of propellant against 12.5 ton.
A human flight rated version of GSLV MK-II with a capsule escape rocket is proposed to be used initially for India's manned space mission. The GSLV MK-II is expected to be launched in in December 2009 carrying the 2.4 ton GSAT - 4.
Features:
Indigenously developed Cryogenic Upper Stage (CUS) will be flight tested. The GSLV carrying this indigenous CUS is designated as GSLV Mk-2. The GSLV carrying the Russian cryogenic stages are designated as GSLV Mk-1.
- Advanced Telemetry System and Advanced Mission Computers.
- Larger Composite Payload Fairing.
- The Composite Carbon Fibre-Reinforced Plastic Payload Fairing (PLF), which is 8.657 m long and 4 m in diameter. Earlier GSLV flights had a mettalic payload fairing diameter of 3.4 m.
Cryogenic Upper Stage (CUS)
Launching heavy satellites weighing over 2 tons into geostationary orbit requires an upper stage powered by a cryogenic engine. Cryogenic technology involves the use of liquid oxygen at minus 183 degrees Celsius and liquid hydrogen at minus 253 degrees Celsius. The technology is difficult to develop and closely guarded by the five nations who currently have it - USA, Russia, Europe, China and Japan.
-
Initial Cryogenic Engine Development Efforts
ISRO started developing a cryogenic engine shortly after the project to develop the Geostationary Satellite Launch Vehicle (GSLV) was launched in 1986. The GSLV is capable of placing a 2 ton satellite into a geostationary transfer orbit (GTO).
-
Transfer of Technology (TOT) from Russia
In 1991 ISRO entered into a $120 million contract with Glavkosmos of Russia for the supply of two KVD-1 cryogenic engines and the complete transfer of technology for those engines. This engine can be used in cryogenic upper stages designed to put payloads into high-altitude elliptical, geostationary orbits or escape trajectories.
The KVD-1 is the one and only oxygen/hydrogen liquid-propellant rocket engine in Russia known to have passed through full-scale ground testing routine. KVD-1's prototype known as 11D56 was developed between 1965-1972 by the Design Bureau of Chemical Machine-Building ( KB Khimmash) for the fourth stage of a future version of heavy Lunar N-1 launch vehicle. Bench trials of the engine commenced in 1966. The KVD-1 engine is a single-chambered unit with a turbopump system designed to feed propellants; and includes afterburning: a feature characteristic of any powerful Russian liquid-propellant rocket engine design.
-
Russia Reneges on Cryogenic Engine TOT
In July 1993, under US pressure, Russia went back on its agreement to transfer cryogenic technology to India on the grounds that it would violate Missile Technology Control Regime (MTCR). In lieu of cryogenic technology, Russia agreed to sell two additional cryogenic stages to India. Following Russia's refusal, India had to develop cryogenic technology it on its own.
-
Current Cryogenic Engine Inventory
Of the seven cryogenic upper stages supplied by Russia, ISRO has so far used five. The last five GSLV flights from Sriharikota were powered by the Russian cryogenic stages. A cryogenic stage includes the engine, propellant tanks, motor casing and wiring.
Indigenous Cryogenic Engine
ISRO has developed its cryogenic upper stage at the Liquid Propulsion Systems Centre (LPSC), Mahendragiri, Tamil Nadu. ISRO's development efforts benefitted from design drawings and other information obtained under the original contract with Russia, and from the extensive training that ISRO engineers received in Russia. ISRO is believed to have contracted former Russian space technicians to assist in the development effort. The outright supply of two KVD-1 engines provided ISRO a conduit to the source of KVD-1 technology.
ISRO's biggest challenge was to develop the special alloys and high-speed turbines required for use with cryogenic fuels. At very low temperatures of liquid hydrogen and liquid oxygen, metals become brittle. The special alloys developed needed new welding techniques and the cryogenic engine fuel pumps required new types of lubricants. SRO's painstaking development effort soon fell behind schedule, threatening its other space programs.
Because of delays in the production of the KVD-1 derivative, in December 2001, ISRO entered into an agreement with Khrunichev Space Centre for supply of five additional KVD-1 engines. The additional purchase ensured the continuity of the GSLV program.
-
First Test Flight Failure
The first test flight of ISRO developed Cryogenic Upper Stage (CUS) on board the GSLV D-3 failed on Thursday, April 15. Initial indications are that the CUS ignited after the first two stages performed flawlessly, lifting the rocket to a height of 60 km and imparting it a velocity of 4.9 km/sec as designed.
Subsequently, the rocket was seen to tumble indicating a failure of the two vernier engines on the CUS. While the main engine of the CUS provides the thrust necessary to loft the satellite to a GTO orbit, two smaller cryogenic vernier engines help steer the rocket along its programmed trajectory.
The failure initially drove ISRO chairman K Radhakrishnan to tears but he soon gathered himself and promised that ISRO will perform a detailed analysis to determine why the vernier engines did not ignite, and whether the main cryogenic engine did ignite.
Pointing out the ISRO scientists and technicians had worked hard for 18 years to come to this level, Radhakrishnan promised to be ready for another launch within an year. The GSLV D3 launcher was carrying the 2.4 ton GSAT-4.
-
Cryogenic Engine Failure Analysis
On Sunday, April 18, after a two day meeting chaired by ISRO Chief K. Radhakrishnan to analysze GSLV D-3 telemetry data, space scientists announced that the CUS ignited but shut down within a second because the turbo pump supplying fuel to the engine stopped working.
The data clearly shows that combustion [of the cryogenic engine fuel, liquid hydrogen at minus 253 degree Celsius, and the oxidiser, liquid oxygen at minus 183 degree Celsius] had indeed taken place. The rocket's acceleration had increased for a second before it drifted off the designated flight path. Indications are that the turbine that powered the fuel turbo pump had somehow failed. [The propellants are pumped using turbo pumps running around 4,000 rpm.] There could be various reasons for its failure.
A Failure Analysis Committee (FAC) will now attempt to zero in on the exact reason for the failure and submit its report by May-end. Next, the national experts' panel, constituted to review and give clearance to the GSLV-D3 mission, will examine the report.
|
Launch Vehicles