YF-75: Difference between revisions
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== References == |
== References == |
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* [http://www.astronautix.com/engines/ |
* [http://www.astronautix.com/engines/yf75.htm Encyclopedia Astronautica] |
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* [http://www.geocities.com/CapeCanaveral/Launchpad/1921/engine.htm Go Taikonauts - An unofficial Chinese Space Website] |
* [http://www.geocities.com/CapeCanaveral/Launchpad/1921/engine.htm Go Taikonauts - An unofficial Chinese Space Website] |
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Revision as of 11:12, 23 August 2007
YF-75 (Rocket Engine)
YF-75 is China second generation of crycogenic gimballed engine, in which use Liquid hydrogen (LH2) as fuel and Liquid oxygen (LOX) as oxidizer. It's developed in 1990s and first flight in 1994.
Specifications
- Vacuum thrust: 78.45 kN
- Vacuum specific impulse: 437 s
- Burn time: 470 s
- Engine weight: 550 kg
- Exit to Throat Area ratio: 80 to 1
- Propellants: LOX & LH2
- Mixture ratio: 5.00
- Design: Gas-generator cycle
- Diameter: 1.50 m
- Chambers: 1
- Chamber Pressure: 37.60 bar
- Thrust to Weight Ratio: 14.26
- Contractor: Beijing Wan Yuan Industry Corp.
- Vehicle Application: Long March / CZ-3A, CZ-3B, CZ-3C - 3rd stage
- Status: in Service & Development