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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. | 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. | ||
Revision as of 11:13, 4 January 2022
 The CUS15 upper stage of GSLV-F09 powered by the CE-7.5 engine at Stage Preparation Facility | |
| Country of origin | India |
|---|---|
| First flight | 15 April 2010 (failure) 5 January 2014 (success) |
| 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, vacuum | 73.5 kN (16,500 lbf)[2] |
| Chamber pressure | 5.8 MPa (58 bar) / 7.5 MPa (75 bar) |
| Specific impulse, vacuum | 454 seconds (4.45 km/s) |
| Dimensions | |
| Length | 2.14 m (7.0 ft) |
| Diameter | 1.56 m (5.1 ft) |
| Dry mass | 435 kg |
| Used in | |
| Upper stage of GSLV Mk.II | |
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
CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.[3][4]
Specifications
The specifications and key characteristics of the engine are:
- Operating Cycle – Staged combustion[5]
- Propellant Combination – LOX / LH2[6]
- Maximum thrust (Vacuum) – 73.55 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 – 12,800 kg[7]
- Two independent regulators: thrust control and mixture ratio control[6]
- Steering during thrust: provided by two gimballed steering engines[6]
Development
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. 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).[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 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
- ↑ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.
- ↑ 2.0 2.1 2.2 "GSLV-D3". ISRO. Archived from the original on 16 April 2010. Retrieved 8 January 2014.
- ↑ 3.0 3.1 "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on 7 February 2014.
- ↑ "GSLV MkIII, the next milestone". Frontline. 7 February 2014.
- ↑ 5.0 5.1 5.2 "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
- ↑ 6.0 6.1 6.2 "Indigenous Cryogenic Upper Stage". Archived from the original on 6 August 2014. Retrieved 27 September 2014.
- ↑ 7.0 7.1 7.2 "GSLV-D5". ISRO. Archived from the original on 6 October 2014. Retrieved 27 September 2014.
- ↑ "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.
- ↑ "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.
- ↑ http://www.isro.gov.in/launchers/gslv
