The first development flight of the GSLV (Mk I configuration) was launched on 18 April 2001 was a failure as the payload failed to reach the intended orbit parameters. The launcher was declared operational after the second development flight successfully launched the GSAT-2 satellite. During the initial years from the initial launch to 2014 the launcher had a checkered history with only 2 successful launches out of 7.
Cryogenic engine controversy
The third stage was to be procured from Russian company Glavkosmos, including transfer of technology and design details of the engine based on an agreement signed in 1991.Russia backed out of the deal after United States objected to the deal as in violation of the Missile Technology Control Regime (MTCR) in May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine. A new agreement was signed with Russia for 7 KVD-1 cryogenic stages and 1 ground mock-up stage with no technology transfer, instead of 5 cryogenic stages along with the technology and design as per the earlier agreement. These engines were used for the initial flights and were named GSLV Mk I.
The 49 m (161 ft) tall GSLV, with a lift-off mass of 415 t (408 long tons; 457 short tons), is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is 7.8 m (26 ft) long and 3.4 m (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 (71 mi).
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 altitude maneuver and guide injection of the spacecraft to the specified orbit.
Strap-on motors of GSLV-F05 being integrated with the core stage
The first GSLV flight, GSLV-D1 used the L40 stage. 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 42.6 tons of hypergolic propellants (UDMH and N2O4). The propellants are stored in tandem in two independent tanks 2.1 m (6 ft 11 in) diameter. The engine is pump-fed and generates 760 kN (170,000 lbf) of thrust, with a burn time of 150 seconds.
GSLV-D1 used the S125 stage which contained 125 t (123 long tons; 138 short tons) 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 100 seconds.
Hoisting of the GSLV-F09 second stage during vehicle integration.
The GS2 stage is powered by the Vikas engine. It has a diameter of 2.8 m (9 ft 2 in).
The third stage of the GSLV Mark II is propelled by the Indian CE-7.5cryogenic rocket engine while the older defunct Mark I is propelled using a Russian made KVD-1. It uses liquid hydrogen (LH2) and liquid oxygen (LOX) The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre The engine has a default thrust of 75 kN (17,000 lbf) but is capable of a maximum thrust of 93.1 kN (20,900 lbf).
GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mark I while versions using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mark II. All GSLV launches have been conducted from the Satish Dhawan Space Centre in Sriharikota.
GSLV Mark I
The first developmental flight of GSLV Mark I had a 129 tonne (S125) first stage and was capable of launching around 1500 kg into geostationary transfer orbit. The second developmental flight replaced the S125 stage with S139. It used the same solid motor with 138 tonne propellant loading. The chamber pressure in all liquid engines were enhanced, enabling a higher propellant mass and burn time. These improvements allowed GSLV to carry an additional 300 kg of payload. The fourth operational flight of GSLV Mark I, GSLV-F06, has a 15 tonne propellant loading in the third stage, called the C-15.
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 Mark I) have used Russian cryogenic engines.
For launches from 2018, a 6% increased thrust version of the Vikas engine was developed. It was demonstrated on 29 March 2018 in the GSAT-6A launch second stage. It was used for the four Vikas engines first stage boosters on future missions.
As of 26 April 2021[update] the GSLV has made 13 launches, with 8 successfully reaching their planned orbits, three outright failures and two partial failure, yielding a success rate for GSLV MK. I at 29% (or 57% including the partial failure) and 86% for Mk. II variant. All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR).
^"GSLV Launched Successfully" (PDF). Current Science. 80 (10): 1256. May 2001. Retrieved 12 December 2013.
^ abSubramanian, T. S. (17–31 March 2001). "The GSLV Quest". Frontline. Retrieved 12 December 2013.
^"GSLV Rocket, Billed 'Naughty Boy'". NDTV. Archived from the original on 11 February 2018. Retrieved 11 February 2018.
^Jacob Aron. "India's hefty "naughty boy" rocket comes in from cold". New Scientist. Archived from the original on 11 February 2018. Retrieved 11 February 2018.
^Raj, N Gopal (21 April 2011). "The long road to cryogenic technology". The Hindu. Chennai, India. Retrieved 12 December 2013.
^Subramanian, T. S. (28 April – 11 May 2001). "The cryogenic quest". Frontline. Retrieved 13 December 2013.
^"Why ISRO's New Engine and Mk III Rocket Are Reasons to Forget 1990 Cryogenic Scandal". The Wire. Retrieved 10 February 2018.
^"GSLV-F04". ISRO. Archived from the original on 4 January 2014. Retrieved 15 December 2013.
^ ab"GSLV-D2". ISRO. Archived from the original on 9 August 2013. Retrieved 15 December 2013.
^ ab"GSLV Launcher". ISRO. Retrieved 17 March 2021.
^"Evolution of Indian launch vehicle technologies" (PDF). Current Science. Retrieved 27 January 2014.
^"GSLV-D5". Archived from the original on 6 October 2014. Retrieved 4 January 2014.
^"ISRO's Cryogenic Stage Fails in Maiden Flight". SpaceNews. Archived from the original on 26 May 2012. Retrieved 27 November 2013.
^"GSLV, PSLV flights put off". The Hindu. Chennai, India. 1 January 2010. Archived from the original on 5 January 2010.
^"GSLV-D3/GSAT-4 Brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014. Retrieved 15 January 2014.
^R. V. Perumal; B. N. Suresh; D. Narayana Moorthi; G. Madhavan Nair (25 July 2001). "First developmental flight of geosynchronous satellite launch vehicle (GSLV-D1)" (PDF). Current Science. 81 (2): 167–174. Archived from the original (PDF) on 5 March 2016.
^R. V. Perumal; D. Narayana Moorthi; N. Vedachalam; G. Madhavan Nair (10 September 2003). "Second developmental flight of Geosynchronous Satellite Launch Vehicle" (PDF). Current Science. 85 (5): 597–601. Archived from the original (PDF) on 16 February 2018.
^"GSLV-F06". ISRO. Archived from the original on 10 August 2013. Retrieved 9 January 2014.
^Clark, Stephen (12 October 2010). "India may seek international help on cryogenic engine". Spaceflight Now. Retrieved 15 July 2011. Besides the new upper stage, the GSLV Mk.2 launched in April was nearly identical to previous versions of the booster
^Clark, Stephen (29 March 2018). "India tests upgraded engine tech in successful communications satellite launch". Spaceflight Now. Retrieved 30 March 2018.
^"List of GSLV launches". isro.org. ISRO. Retrieved 14 December 2020.
^"Polar Satellite Launch Vehicle". Retrieved 29 November 2018.
Wikimedia Commons has media related to Geosynchronous Satellite Launch Vehicle.
ISRO GSLV Page
INDIA in Space – GSLV Page
12KRB (KVD-1) Upper Stage at Khrunichev Space Center
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future
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