CE-7.5

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.

CE-7.5
Country of originIndia
First flight15 April 2010 (failure)
5 January 2014 (success)
DesignerLPSC, Indian Space Research Organisation
ManufacturerHindustan Aeronautics Limited
ISRO
ApplicationUpper-stage booster
StatusIn use
Liquid-fuel engine
PropellantLOX / LH2[1]
CycleStaged combustion
Configuration
Chamber1
Performance
Thrust (vac.)73.5 kN (16,500 lbf)[2]
Chamber pressure5.8 MPa (58 bar) / 7.5 MPa (75 bar)
Isp (vac.)454 seconds (4.45 km/s)
Dimensions
Length2.14 m (7.0 ft)
Diameter1.56 m (5.1 ft)
Dry weight435 kg
Used in
Upper stage of GSLV Mk.II

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 27 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. "GSLV-D3". ISRO. Archived from the original on 16 April 2010. Retrieved 8 January 2014.
  3. "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014.
  4. "GSLV MkIII, the next milestone". Frontline. 7 February 2014.
  5. "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
  6. "Indigenous Cryogenic Upper Stage". Archived from the original on 6 August 2014. Retrieved 27 September 2014.
  7. "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 4 January 2014. Retrieved 5 January 2014.CS1 maint: archived copy as title (link)
  11. "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Archived from the original on 8 January 2014. Retrieved 6 January 2014.
  12. http://www.isro.gov.in/launchers/gslv

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