Template:Infobox rocket engine
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, 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]
- Engine Specific Impulse - Template:Convert[2][4]
- 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
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]
Applications
CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[12]
See also
References
- ↑ Russian route, Ramachandran, R.. Frontline. Retrieved 2021-08-17.
- ↑ 2.0 2.1 GSLV-D3 brochure. ISRO.
- ↑ GSLV MkIII, the next milestone. Frontline(2014-02-07).
- ↑ 4.0 4.1 4.2 Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful. ISRO. Retrieved 8 January 2014.
- ↑ 5.0 5.1 5.2 Indigenous Cryogenic Upper Stage. Retrieved 27 September 2014.
- ↑ 6.0 6.1 6.2 GSLV-D5. ISRO. Retrieved 27 September 2014.
- ↑ 7.0 7.1 Cite error: Invalid
<ref>tag; no text was provided for refs namedgslvd3 - ↑ 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.Template:Cbignore
- ↑ How ISRO developed the indigenous cryogenic engine.
- ↑ Archived copy. Retrieved 2014-01-05.
- ↑ Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5. ISRO. Retrieved 6 January 2014.
- ↑ GSLV - Isro.