CE-7.5

From Wikipedia, the free encyclopedia
Jump to: navigation, search
CE-7.5
Country of origin India
Date 2002
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[edit]

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

Specifications[edit]

The specifications and key characteristics of the engine are:

  • Operating Cycle – Staged combustion[5]
  • Propellant Combination – LOX / LH2[6]
  • Maximum thrust (Vacuum) – 75 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 gimbaled steering engines[6]

Development[edit]

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. First flight attempt took place in April 2010 using GSLV Mk-2 D3 launch vehicle. However the engine failed to ignite.[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 using GSLV D5.[10][11]

Applications[edit]

CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.[12]

See also[edit]

References[edit]

  1. ^ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013. 
  2. ^ a b c "GSLV-D3". ISRO. Retrieved 8 January 2014. 
  3. ^ a b "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. ^ a b c "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014. 
  6. ^ a b c "Indigenous Cryogenic Upper Stage". Retrieved 27 September 2014. 
  7. ^ a b c "GSLV-D5". ISRO. 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. ^ http://www.isro.gov.in/gslv-d5/mission.aspx
  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