CE-20
 Model of CE-20 | |
| Country of origin | India |
|---|---|
| Date | 2015 |
| Designer | LPSC, Indian Space Research Organisation |
| Manufacturer | Hindustan Aeronautics Limited,[1] |
| Application | Upper stage booster |
| Status | Under Development |
| Liquid-fuel engine | |
| Propellant | LOX / LH2 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 100 |
| Performance | |
| Thrust, vacuum | 200 kN (45,000 lbf) |
| Specific impulse, vacuum | 443 seconds (4.34 km/s) |
| Dimensions | |
| Dry mass | 588 kg |
The CE-20 is a cryogenic rocket engine being developed by the Liquid Propulsion Systems Centre, a subsidiary of Indian Space Research Organisation. It is being developed to power the upper stage of the Geosynchronous Satellite Launch Vehicle Mk III.[2] It is the first Indian cryogenic engine to feature a gas-generator cycle.[3]
Overview
The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle.[4] The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between them. The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with 5.05 engine mixture ratio. The engine has a thrust-to-weight ratio of 34.7 and a specific impulse of 444 seconds (4.35 km/s) in vacuum. ISRO tested the CE-20 on April 28, 2015 at Mahendragiri test facility and achieved a successful long duration hot test (635 seconds).[5] On July 16, 2015, CE-20 was successfully endurance hot tested for a duration of 800 seconds at ISRO Propulsion Complex, Mahendragiri. This duration is approximately 25% more than the engine burn duration in flight.[6] The CE-20 cryogenic engine was again hot-tested for a duration of 640 seconds at ISRO Propulsion Complex, Mahendragiri on 19 February 2016.[7]
For the upcoming GSLV flight in Jan 2017, it was tested again on December 03 for 25 seconds[8]
Specifications
The specifications of the engine as listed on the LPSC handouts:[9]
- Operating Cycle - Gas Generator
- Propellant Combination - Liquid oxygen / Liquid hydrogen
- Thrust Nominal (Vacuum) - 200 kN
- Operating Thrust Range - 180 kN to 220 kN (To be set at any fix values)
- Chamber Pressure (Nom) - 6 MPa
- Engine Mixture ratio (Oxidizer/Fuel by weight) - 5.05
- Engine Specific Impulse - 443 ± 3 seconds (4.344 ± 0.029 km/s)
- Engine Burn Duration (Nom) - 595 seconds
- Total Flow rate - 462 kg/s
- Nozzle Area ratio - 100
- Mass - 588 kg
See also
References
- ^ http://www.thehindu.com/sci-tech/hal-to-produce-cryogenic-engines-for-isro/article4661042.ece
- ^ Indigenous Cryogenic Engine Tested Successfully ISRO 12 May 2012
- ^ "Space Transportation". GSLV - Mk III - Status of CE-20. Indian Space Research Organization. 2009-07-15. Retrieved 2009-08-29.
- ^ GSLV MkIII, the next milestone Frontline 7 February 2014
- ^ http://timesofindia.indiatimes.com/india/Isros-desi-cryogenic-engine-test-successful/articleshow/47090046.cms
- ^ http://isro.gov.in/update/20-jul-2015/indigenously-developed-high-thrust-cryogenic-rocket-engine-successfully-ground
- ^ story/ISRO upbeat as indigenous cryo engine passes test The Hindu, 19 February 2016
- ^ http://www.thehindu.com/sci-tech/science/GSLV-engine-tested-at-Mahendragiri/article16756493.ece
- ^ "LPSC Handouts at Aer India-2009". Specifications of CE-20. Liquid Propulsion Systems Centre. 2009-03-13. Retrieved 2009-08-29.
External links
- India test-fires indigenous cryo engine for 800 seconds
- LPSC handouts during Aero India-2009 with Ce-20 specifications
- LPSC handouts during Aero India-2009 with specifications of all Liquid-fueled engines of India
- Status of CE-20 in Space Transportation/GSLV - Mk III of ISRO's 2008-09 Annual Report
- http://www.thehindu.com/sci-tech/science/isro-upbeat-as-indigenous-cryo-engine-passes-test/article8258313.ece#
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