Our website is made possible by displaying online advertisements to our visitors.
Please consider supporting us by disabling your ad blocker.
CE-7.5
 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 | Fuel-rich 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.[3]
- ^ "Cryogenic engine test a big success, say ISRO officials". Indian Express. Archived from the original on 1 April 2013. Retrieved 27 December 2013.
- ^ "GSLV-D3". ISRO. Archived from the original on 16 April 2010. Retrieved 8 January 2014.
- ^ Ramachandran, R. (22 January 2014). "Russian route". Frontline. Archived from the original on 24 October 2020. Retrieved 17 August 2021.
Previous Page Next Page
