Engine Model: YF-75. Designer: Beijing Wan Yuan. Propellants: Lox/LH2. Thrust(vac): 78.500 kN (17,648 lbf). Isp: 440 sec. Burn time: 470 sec. Diameter: 1.50 m (4.90 ft). Chambers: 1. Chamber Pressure: 37.60 bar. Area Ratio: 80.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 0.00. Country: China. Status: In development. First Flight: 1994. Last Flight: 2006. Flown: 34. Gas-generator turbopump. Gimballed engine.
YF-75 used on Rocket Stages
YF-75 used on Spacecraft