CE-7.5

CE-7.5
Country of origin India
First flight 15 April 2010 (failure)
5 January 2014 (success)
Designer LPSC, Indian Space Research Organisation
Manufacturer Hindustan Aeronautics Limited
ISRO
Application Upper-stage booster
Status In use
Liquid-fuel engine
Propellant LOX / LH2[1]
Cycle Staged combustion
Configuration
Chamber 1
Performance
Thrust (vac.) 73.5 kN (16,500 lbf)[2]
Chamber pressure 5.8 MPa (58 bar) / 7.5 MPa (75 bar)
Isp (vac.) 454 seconds (4.45 km/s)
Dimensions
Length 2.14 m (7.0 ft)
Diameter 1.56 m (5.1 ft)
Dry weight 435 kg

The CE-7.5 is a cryogenic rocket engine developed by the Indian Space Research Organisation to power the upper stage of its GSLV Mk-2 launch vehicle. The engine was developed as a part of the Cryogenic Upper Stage Project (CUSP). It replaced the KVD-1 (RD-56) Russian cryogenic engine that powered the upper stage of GSLV Mk-1.

Overview

CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.[3][4]

Specifications

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[5]
  • Propellant Combination – LOX / LH2[6]
  • Maximum thrust (Vacuum) – 73.55 kN[7]
  • Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN [2][8]
  • Engine Specific Impulse - 454 ± 3 seconds (4.452 ± 0.029 km/s)[3][5]
  • Engine Burn Duration (Nom) – 720 seconds[7]
  • Propellant Mass – 12800 kg[7]
  • Two independent regulators: thrust control and mixture ratio control[6]
  • Steering during thrust: provided by two gimballed steering engines[6]

Development

ISRO formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[5] and was integrated with propellant tanks, third-stage structures and associated feed lines for the first launch. The first flight attempt took place in April 2010 during the GSLV Mk.II D3/GSAT-3 mission. The engine ignited, but the ignition did not sustain as the Fuel Booster Turbo Pump (FBTP) shut down after reaching a speed of about 34,500 rpm 480 milliseconds after ignition, due to the FBTP being starved of Liquid Hydrogen (LH2).[2] On 27th March 2013 the engine was successfully tested under vacuum conditions. The engine performed as expected and was qualified to power the third stage of the GSLV Mk-2 rocket. On 5 January 2014 the cryogenic engine performed successfully and launched the GSAT-14 satellite in the GSLV-D5/GSAT-14 mission.[10][11]

Applications

CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[12]

See also

References

  1. ↑ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.
  2. 1 2 3 "GSLV-D3". ISRO. Archived from the original on 16 April 2010. Retrieved 8 January 2014.
  3. 1 2 "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on February 7, 2014.
  4. ↑ "GSLV MkIII, the next milestone". Frontline. 2014-02-07.
  5. 1 2 3 "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
  6. 1 2 3 "Indigenous Cryogenic Upper Stage". Archived from the original on 6 August 2014. Retrieved 27 September 2014.
  7. 1 2 3 "GSLV-D5". ISRO. Archived from the original on 6 October 2014. Retrieved 27 September 2014.
  8. ↑ "GSLV-D5 launch video – CE-7.5 thrust was uprated by 9.5% to 82 kN and then brought back to nominal thrust of 73.55 kN". Doordarshan National TV.
  9. ↑ "How ISRO developed the indigenous cryogenic engine". The Economic Times.
  10. ↑ "Archived copy". Archived from the original on 2014-01-04. Retrieved 2014-01-05.
  11. ↑ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Retrieved 6 January 2014.
  12. ↑ http://www.isro.gov.in/launchers/gslv

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