Country of origin India
Date 2002
Designer LPSC, , Indian Space Research Organisation
Manufacturer Hindustan Aeronautics Limited
Application Upper-stage booster
Status In use
Liquid-fuel engine
Propellant LOX / LH2[1]
Cycle Staged combustion
Chamber 1
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)
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.


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


The specifications and key characteristics of the engine are:


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]


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

See also


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