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 |
| Cycle | Staged combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 73.5 kN (16,500 lbf) |
| 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.
CE-7.5 is a regeneratively-cooled, variable-thrust, staged combustion cycle rocket engine.
The specifications and key characteristics of the engine are:
ISRO formally started the Cryogenic Upper Stage Project in 1994. The engine successfully completed the Flight Acceptance Hot Test in 2008, 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. 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.
CE-7.5 is being used in the third stage of ISRO's GSLV Mk-2 rocket.
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