Geosynchronous Satellite Launch Vehicle abbreviated as GSLV, is an expendable launch GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launchers in the form of the S/S solid rocket . The difference between expected and actual inclination degree was 0. SLV that stands for Satellite Launch Vehicle, was a project started by the Indian Space Research Organisation (ISRO) and was headed by APJ. GEOSYNCHRONOUS SATELLITE LAUNCH VEHICLE(GSLV) About the Launch Vehicle. newer improved version with a higher chamber pressure is used here. The stage was derived from the PS2 of PSLV where the Vikas engine has.

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GSLV has been used in thirteen launches to date, since its first launch in to the most recent on December 19, carrying the GSAT-7A military communications satellite.

The Geosynchronous Satellite Launch Vehicle GSLV project was initiated in with the objective of acquiring an Indian launch capability for geosynchronous satellites. I configuration was launched on 18 April was a failure as the psllv failed to reach the intended orbit parameters. The launcher was declared operational after the second development flight successfully launched the GSAT-2 satellite.

ISRO’s recent launches: PSLV and GSLV – General Knowledge Today

During the initial years from the initial launch to the launcher had a checkered history with only 2 successful launches out of 7. The third stage was to be procured from Russian company Glavcosmosincluding transfer of technology and design details of the engine based on differenxe agreement signed in The payload fairing, which is 7.

It is discarded when the vehicle reaches an altitude of about km. The digital auto-pilot and closed loop guidance scheme ensure the required altitude diffedence and guide injection of the spacecraft to the specified orbit.

The propellants are stored in tandem in two independent tanks 2. All subsequent launches have used enhanced propellant loaded S stage. The GS2 stage is powered by the Vikas engine. It has a diameter of 2. II is propelled by the Indian CE I is propelled using a Russian made KVD The second developmental flight replaced the S stage with S It used the same solid motor with tonne propellant loading.


The chamber pressure in all liquid engines were enhanced, enabling a higher propellant mass and burn time. This variant uses an Indian cryogenic engine, the CE I have used Russian cryogenic engines.

It will be used for the four Vikas engines first stage boosters on future missions. All the three stages performed successfully.

The injection parameters were met with extreme precision. Perigee was within m within 0.

The difference between expected and actual inclination degree was 0. From Wikipedia, the free encyclopedia. Indian satellite launch vehicle. Spaceflight portal India portal. Retrieved 21 December Retrieved 29 August Retrieved 12 December Archived from the original on 11 February Retrieved 11 February Retrieved 13 December Retrieved 10 February Archived from the original on 4 January Retrieved 15 December Archived from the original on 9 August Archived from the original on August 10, Retrieved November 27, Retrieved January 27, Archived qnd the original on 6 October Retrieved 4 January Archived from the original on May 26, Archived from the original PDF on 7 February Retrieved 15 January Madhavan Nair 25 July Archived from the original PDF on diffeeence March Madhavan Nair 10 September Archived from the original PDF on 16 February Retrieved 9 January Retrieved 15 July Retrieved 30 March Comprehensive Orbital Launch Failure List”.

Retrieved 14 August Indian Space Research Organisation. Retrieved 20 January Archived from the original on March 14, Archived from the original on March 18, Archived from the original on March 1, Archived from the original on Retrieved November 19, Archived from the original on 26 December Retrieved 25 December Dinesh 31 October Retrieved January 5, The Times Of India.

Retrieved 5 January rifference Archived from the original on 6 January Retrieved 1 July Retrieved 27 August Retrieved 29 March Retrieved 1 April The Times of India. Retrieved 11 July Retrieved April 27, Retrieved August 12, Retrieved 22 September Retrieved differenve April List of orbital launch systems Comparison of orbital launch systems. Retrieved from ” https: Views Read Edit View history. In other projects Wikimedia Commons. This page was last edited on 23 Decemberat By using this site, you agree to the Terms of Use and Privacy Policy.

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Medium Lift Launch System. I [ edit ]. Developmental flight, payload placed into lower than planned orbit, betweem did not have sufficient fuel to reach a usable orbit.

Question corner: What is the difference between GSLV and PSLV? – The Hindu

Radhakrishnan attributed the failure to incorrect mixture ratio used in the cryogenic upper stage. Both rocket and satellite had to be destroyed over the Bay of Bengal after the rocket’s trajectory veered outside permitted limits.

Apogee lower and inclination higher than expected, due to an error in the betweeh subsystem. Satellite is fully operational and full design life of ten years will be achieved.

Geosynchronous Satellite Launch Vehicle

It completed 6 years in orbit successfully. Destroyed by range safety officer after loss of control over liquid-fueled boosters.

II [ edit ]. The flight was scheduled for 19 Augustbut one hour and 14 minutes before betweeh lift off, a leakage was reported and the launch was halted. The cuboid-shaped GSAT-6 satellite includes a technology demonstrator S-Band unfurlable antenna with a diameter of six metre which will provide S-band communication services during its expected mission life of nine years.

Electro-hydraulic Actuation used for gimballing in GS2 stage was replaced by more reliable Electro-Mechanical Actuation.