Geosynchronous Satellite Launch Vehicle

Geosynchronous Satellite Launch Vehicle (GSLV) is an expendable launch system operated by the Indian Space Research Organisation (ISRO). GSLV was used in thirteen launches from 2001 to 2018, with more launches planned. Even though GSLV Mark III shares the name, it is an entirely different launch vehicle.

Not to be confused with GSLV Mark III.
GSLV
GSLV-F05 carrying INSAT-3DR at the Second Launch Pad
FunctionMedium Lift Launch System
ManufacturerISRO
Country of originIndia
Cost per launchUS$47 million[1]
Size
Height49.13 m (161.2 ft)[2]
Diameter2.8 m (9 ft 2 in)
Mass414,750 kg (914,370 lb)
Stages3
Capacity
Payload to LEO
Mass5,000 kg (11,000 lb)[2]
Payload to GTO
Mass2,700 kg (6,000 lb)[2][3]
Launch history
Status
  • Mk I: Retired
  • Mk II: Active
Launch sitesSatish Dhawan
Total launches13 (6 Mk.I, 7 Mk.II)
Success(es)8 (2 Mk.I, 6 Mk.II)
Failure(s)3 (2 Mk.I, 1 Mk.II)
Partial failure(s)2 (Mk.I)
First flight
  • Mk.I: 18 April 2001
  • Mk.II: 15 April 2010
Last flight
  • Mk.I: 25 December 2010
  • Mk.II: 19 December 2018
Notable payloadsSouth Asia Satellite
Boosters
No. boosters4 L40 Hs
Length19.7 m (65 ft)[4]
Diameter2.1 m (6.9 ft)[4]
Propellant mass42,700 kg (94,100 lb) each [4]
Engines1 L40H Vikas 2
Thrust760 kN (170,000 lbf)[5]
Total thrust3,040 kN (680,000 lbf)
Specific impulse262 s (2.57 km/s)
Burn time154 seconds[4]
FuelN2O4/UDMH
First stage
Length20.2 m (66 ft)[4]
Diameter2.8 m (9.2 ft)[4]
Propellant mass138,200 kg (304,700 lb)[4]
Engines1 S139
Thrust4,846.9 kN (1,089,600 lbf)[5]
Specific impulse237 s (2.32 km/s)
Burn time100 seconds
FuelHTPB (solid)
Second stage
Length11.6 m (38 ft)[4]
Diameter2.8 m (9.2 ft)[4]
Propellant mass39,500 kg (87,100 lb)[4]
Engines1 GS2 Vikas 4
Thrust846.8 kN (190,400 lbf)[5]
Specific impulse295 s (2.89 km/s)
Burn time139 seconds[4]
FuelN2O4/UDMH
Second GS2 (GL40) stage
Length11.9 m (39 ft)[6]
Diameter2.8 m (9.2 ft)[6]
Propellant mass42,500 kg (93,700 lb)[6]
Engines1 GS2 Vikas 4
Thrust846.8 kN (190,400 lbf)[5]
Specific impulse295 s (2.89 km/s)
Burn time149 seconds[6]
FuelN2O4/UDMH
Third stage (GSLV Mk II) – CUS12
Length8.7 m (29 ft)[4]
Diameter2.8 m (9.2 ft)[4]
Propellant mass12,800 kg (28,200 lb)[4]
Engines1 CE-7.5
Thrust75 kN (17,000 lbf)
Specific impulse454 s (4.45 km/s)
Burn time718 seconds[4]
FuelLOX/LH2
Third stage (GSLV Mk II) – CUS15
Length9.9 m (32 ft)[6]
Diameter2.8 m (9.2 ft)[6]
Propellant mass15,000 kg (33,000 lb)[6]
Engines1 CE-7.5
Thrust75 kN (17,000 lbf)
Specific impulse454 s (4.45 km/s)
Burn time846 seconds[6]
FuelLOX/LH2

History

The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites.[7][8]

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-fueled Vikas engine. Due to the thrust required for injecting the satellite in a GTO orbit the third stage was to be powered by a LOX/LH2 Cryogenic engine which at that time India did not possess or had the technology know-how to build one.

Indigenous 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.[9][10]

Cryogenic Engine Controversy

The third stage was to be procured from Russian company Glavcosmos, including transfer of technology and design details of the engine based on an agreement signed in 1991.[8] Russia backed out of the deal after US objected to the deal as in violation of the Missile Technology Control Regime (MTCR) May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine.[11] 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.[12] These engines were used for the initial flights and were named GSLV Mk.1.[13]

Vehicle description

The 49 metres (161 ft) tall GSLV, with a lift-off mass of 415 metric tons (915,000 lb), 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.[14]

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 5,000 kg (11,000 lb) into an easterly Low Earth orbit or 2,500 kg (5,500 lb)(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

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.[15] 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 & N2O4). The propellants are stored in tandem in two independent tanks 2.1 metres (6 ft 11 in) diameter. The engine is pump-fed and generates 760 kilonewtons (170,000 lbf) of thrust, with a burn time of 150 seconds.

First stage

GSLV-D1 used the S125 stage which contained 125 metric tons (276,000 lb) of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage.[15] The S139 stage is 2.8 m in diameter and has a nominal burn time of 109 seconds.[16] The stage generates a maximum thrust of 4700 kN.[17]

Hoisting of the GSLV-F09 second stage during vehicle integration

Second stage

The GS2 stage is powered by the Vikas engine. It has a diameter of 2.8 metres (9 ft 2 in).[16]

Third stage

The third stage of the GSLV Mk.II is propelled by the Indian CE-7.5 cryogenic rocket engine while the older defunct Mk.I is propelled using a Russian made KVD-1. It uses liquid hydrogen (LH2) and liquid oxygen (LOX)[18] The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre [19][20] The engine has a default thrust of 75 kilonewtons (17,000 lbf) but is capable of a maximum thrust of 93.1 kilonewtons (20,900 lbf).

Payload Fairing with GSAT-6A being Integrated

Variants

GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mk I while versions using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mk II.[21] 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.[22][23] The fourth operational flight of GSLV Mk I, GSLV-F06, has a 15 tonne propellant loading in the third stage, called the C-15.[24]

Launch of GSLV F11 GSAT-7A from Second Launch Pad of SDSC SHAR

GSLV Mark 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 Mark I) have used Russian cryogenic engines.[25]

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 first stage boosters on future missions.[26]

Launch history
Main article: List of GSLV launches

As of 14 December 2020 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.[27] All launches have occurred from the Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR).

Variant Launches Successes Failures Partial failures
GSLV Mk. I 6 2 2 2
GSLV Mk. II 7 6 1 0
Total as of December 2020[28] 13 8 3 2
  • GSLV F05 take off
  • GSLV F11 vehicle at Second Launch Pad.
  • 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.

See also

References
  1. "GAO".
  2. "Geosynchronous Satellite Launch Vehicle". Archived from the original on 21 October 2015. Retrieved 21 December 2014.
  3. "ISRO developing vehicle to launch small satellites". Retrieved 29 August 2018.
  4. "GSLV F09 Brochure". ISRO.
  5. "GSLV F08 Brochure". ISRO.
  6. "GSLV F11 Brochure". ISRO.
  7. "GSLV Launched Successfully" (PDF). Current Science. 80 (10): 1256. May 2001. Retrieved 12 December 2013.
  8. Subramanian, T S (March 17–31, 2001). "The GSLV Quest". Frontline. Retrieved 12 December 2013.
  9. "GSLV Rocket, Billed 'Naughty Boy'". NDTV. Wayback Machine. Archived from the original on 11 February 2018. Retrieved 11 February 2018.
  10. Jacob Aron. "India's hefty 'naughty boy' rocket comes in from cold". New Scientist. Wayback Machine. Archived from the original on 11 February 2018. Retrieved 11 February 2018.
  11. Raj, N Gopal (21 April 2011). "The long road to cryogenic technology". The Hindu. Chennai, India. Retrieved 12 December 2013.
  12. Subramanian, T S (28 April – 11 May 2001). "The cryogenic quest". Frontline. Retrieved 13 December 2013.
  13. "Why ISRO's New Engine and Mk III Rocket Are Reasons to Forget 1990 Cryogenic Scandal". The Wire. Retrieved 10 February 2018.
  14. "GSLV-F04". ISRO. Archived from the original on 4 January 2014. Retrieved 15 December 2013.
  15. "GSLV-D2". ISRO. Archived from the original on 9 August 2013. Retrieved 15 December 2013.
  16. "GSLV D3". ISRO. Archived from the original on August 10, 2013. Retrieved November 27, 2013.
  17. "Evolution of Indian launch vehicle technologies" (PDF). Current Science. Retrieved January 27, 2014.
  18. "GSLV-D5". Archived from the original on 6 October 2014. Retrieved 4 January 2014.
  19. "ISRO's Cryogenic Stage Fails in Maiden Flight". Space News. Archived from the original on May 26, 2012. Retrieved November 27, 2013.
  20. "GSLV, PSLV flights put off". The Hindu. Chennai, India. 1 January 2010.
  21. "GSLV-D3/GSAT-4 Brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014. Retrieved 15 January 2014.
  22. 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.
  23. 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.
  24. "GSLV-F06". ISRO. Archived from the original on August 10, 2013. Retrieved 9 January 2014.
  25. Clark, Stephen (2010-10-12). "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.
  26. Clark, Stephen (29 March 2018). "India tests upgraded engine tech in successful communications satellite launch". Spaceflight Now. Retrieved 30 March 2018.
  27. "List of GSLV launches". isro.org. Retrieved 14 December 2020.
  28. "Polar Satellite Launch Vehicle". Retrieved 29 November 2018.

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