CE-7.5
| Country of origin | India |
|---|---|
| Date | 2002 |
| 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 (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) |
| Dimensions | |
| 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.
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) – 75 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 – 12800 kg[7]
- Two independent regulators: thrust control and mixture ratio control[6]
- Steering during thrust: provided by two gimbaled 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. 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]
Applications
CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.[12]
See also
References
- ↑ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Retrieved 27 December 2013.
- 1 2 3 "GSLV-D3". ISRO. Retrieved 8 January 2014.
- 1 2 "GSLV-D3 brochure" (PDF). ISRO. Archived from the original (PDF) on February 7, 2014.
- ↑ "GSLV MkIII, the next milestone". Frontline. 2014-02-07.
- 1 2 3 "Flight Acceptance Hot Test Of Indigenous Cryogenic Engine Successful". ISRO. Retrieved 8 January 2014.
- 1 2 3 "Indigenous Cryogenic Upper Stage". Retrieved 27 September 2014.
- 1 2 3 "GSLV-D5". ISRO. 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.
- ↑ http://www.isro.gov.in/gslv-d5/mission.aspx
- ↑ "Indigenous Cryogenic Upper Stage Successfully Flight Tested On-board GSLV-D5". ISRO. Retrieved 6 January 2014.
- ↑ http://www.isro.gov.in/launchers/gslv
