The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites.[8][9]
GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launch vehicles in the form of the S125/S139 solid rocket booster and the liquid-fueledVikas engine. Due to the thrust required for injecting the satellite in a geostationary transfer orbit (GTO) the third stage was to be powered by a LOX/LH2 Cryogenic engine which at that time India did not possess or have the technological expertise to build. The aerodynamic characterization research was conducted at the National Aerospace Laboratories' 1.2m Trisonic Wind Tunnel Facility.[10]
Second stage of GSLV (GS2) for the GSLV F16 flightIndigenous Cryogenic Upper Stage CE-7.5 of GSLV
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,resulting in the rocket gaining the nickname "naughty boy".[11][12]
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.[9] 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.[13] 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.[14] These engines were used for the initial flights and were named GSLV Mk I.[15]
Vehicle description
The 49m (161ft) tall GSLV,with a lift-off mass of 415t (408 long tons;457 short tons),is a three-stage vehicle with solid,liquid and cryogenic stages respectively. The payload fairing,which is 7.8m (26ft) long and 3.4m (11ft) 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 115km (71mi).[16][needs update]
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.
The GSLV can place approximately 5,000kg (11,000lb) into an easterly low Earth orbit (LEO) or 2,500kg (5,500lb) (for the Mk II version) into an 18°geostationary transfer orbit.
Strap-on motors of GSLV-F05 being integrated with the core stage
Liquid boosters
L40 boosters during checkout phase
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.[17] 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 2.1m (6ft 11in) diameter. The engine is pump-fed and generates 760kN (170,000lbf) of thrust,with a burn time of 150 seconds.
First stage
GSLV-D1 used the S125 stage which contained 125t (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.[17] The S139 stage is 2.8 m in diameter and has a nominal burn time of 100 seconds.[18][19]
Hoisting of the GSLV-F14 second stage during vehicle integration
Second stage
The GS2 stage is powered by the Vikas engine. It has a diameter of 2.8m (9ft 2in).[18]
Third stage
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)[20] The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre.[21][22] The engine has a default thrust of 75kN (17,000lbf) but is capable of a maximum thrust of 93.1kN (20,900lbf). In GSLV-F14 mission,a new white coloured C15 stage was introduced which has more environmental-friendly manufacturing processes,better insulation properties and the use of lightweight materials.[23]
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.[24][25] 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 1500kg 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 300kg of payload.[26][27] The fourth operational flight of GSLV Mark I,GSLV-F06,had a longer third stage called the C15 with 15 tonne propellant loading and also employed a 4 meter diameter payload fairing.[28][29]
This variant uses an Indian cryogenic engine,the CE-7.5,and is capable of launching 2500kg into geostationary transfer orbit. Previous GSLV vehicles (GSLV Mark I) have used Russian cryogenic engines.[30]
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 will be used for the four Vikas engines on the first stage boosters on future missions.[31]
A 4m diameter Ogive payload fairing was developed and deployed for the first time in the EOS-03 launch on 12 August 2021,although this launch was a failure due to technical anomalies with the Cryogenic Upper Stage. This will allow GSLV vehicles to accommodate larger payloads.[32]
As of October 2024,ISRO has stopped selling GSLV Mk II Rockets. Eight known launches are planned with NVS Missions,IDRSS Missions,NISAR Mission.[33][34]
RLV-OREX
The Reusable Launch Vehicle Technology Demonstration program,is a prototype spaceplane concept created by ISRO. For the Orbital return Flight experiment,a modified version of the GSLV Mk. II launcher,with the upper Cryogenic Stage replaced with the PS-4 stage from the PSLV is currently in development,as the RLV won't need all the excess energy produced by the CUS .[35][36]
↑ 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
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GSLV F05 take off
GSLV F11 vehicle at Second Launch Pad
Indigenous Cryogenic Upper Stage CE-7.5 of GSLV
Fully integrated GSLV-F05 coming out of the Vehicle Assembly Building
Launch of GSLV F11 from Second Launch Pad
Top view of a fully Integrated GSLV-F08 inside the Vehicle Assembly Building
