YF-75
From Wikipedia, the free encyclopedia
[edit] YF-75 (Rocket Engine)
The YF-75 is China's second generation of cryogenic gimballed engine, using liquid hydrogen (LH2) fuel and liquid oxygen (LOX) oxidizer. Its development began in the early 1990s and its first flight was in 1994.
[edit] 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
- Height: 2.8 m
- Diameter: 1.50 m
- Chambers: 1
- Chamber Pressure: 37.60 bar
- Thrust to Weight Ratio: 14.26
- Restartable: Yes (1 time)
- Contractor: CALT
- Vehicle Application: Long March / CZ-3A, CZ-3B, CZ-3C - 3rd stage
- Status: in Service & Development