CE-7.5
Template:Short description Script error: No such module "Unsubst". Script error: No such module "Infobox".Script error: No such module "Check for unknown parameters". 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.[1]
Overview
CE-7.5 is a regeneratively-cooled, variable-thrust, fuel-rich staged combustion cycle rocket engine.[2][3]
Specifications
The specifications and key characteristics of the engine are:
- Operating Cycle – Staged combustion[4]
- Propellant Combination – LOX / LH2[5]
- Maximum thrust (Vacuum) – 73.55 kN[6]
- Operating Thrust Range (as demonstrated during GSLV Mk2 D5 flight) – 73.55 kN to 82 kN[7][8]
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- Engine Burn Duration (Nom) – 720 seconds[6]
- Propellant Mass – 12,800 kg[6]
- Two independent regulators: thrust control and mixture ratio control[5]
- Steering during thrust: provided by two gimballed steering engines[5]
Development
The Indian Space Research Organisation (ISRO) formally started the Cryogenic Upper Stage Project in 1994.[9] The engine successfully completed the Flight Acceptance Hot Test in 2008,[4] 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).[7] 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]
To aid in the development of NGLV, technologies for multiple restart and development of a spark torch igniter was conducted on the Vernier engine of the GSLV CUS in March 2025.[12]
Applications
CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[13]
See also
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References
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