YF-75

Designer: Beijing Wan Yuan Industry Corp. 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

Used on stage: CZ-3A-3. on launch vehicle: CZ-3A.

Used on stage: CZ-3A-3. on launch vehicle: CZ-3B.

Used on stage: CZ-3A-3. on launch vehicle: CZ-3C.

Used on stage: CZ-NGLV-HO. on launch vehicle: CZ-NGLV-320.

Used on stage: CZ-NGLV-HO. on launch vehicle: CZ-NGLV-504/HO.

Used on stage: CZ-NGLV-HO. on launch vehicle: CZ-NGLV-522/HO.

Used on stage: CZ-NGLV-HO. on launch vehicle: CZ-NGLV-540/HO.

YF-75 used on Spacecraft

Used on: CZ-3A-3.

Used on: CZ-NGLV-HO.

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