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CE-7.5
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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[edit]
CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.[2][3]
Specifications[edit]
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 - 454 ± 3 seconds (4.452 ± 0.029 km/s)[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[edit]
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[edit]
CE-7.5 is being used in the third stage of ISRO's GSLV Mk.II rocket.[12]
See also[edit]
References[edit]
- ↑ Ramachandran, R. "Russian route". Frontline. Archived from the original on 24 October 2020. Retrieved 17 August 2021.
- ↑ 2.0 2.1 "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014.
- ↑ "GSLV MkIII, the next milestone". Frontline. 7 February 2014.
- ↑ 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". Archived from the original on 6 August 2014. Retrieved 27 September 2014.
- ↑ 6.0 6.1 6.2 "GSLV-D5". ISRO. Archived from the original on 6 October 2014. 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. Archived from the original on 21 December 2021.
- ↑ "How ISRO developed the indigenous cryogenic engine". The Economic Times.
- ↑ "Archived copy". Archived from the original on 4 January 2014. Retrieved 5 January 2014.
{{cite web}}: CS1 maint: archived copy as title (link) - ↑ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Archived from the original on 8 January 2014. Retrieved 6 January 2014.
- ↑ "GSLV - Isro".
