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Designer: Mitsubishi. Used on stages: H-1-2. Used on launch vehicles: H-1. Propellants: Lox/LH2 Thrust(vac): 10,500 kgf. Thrust(vac): 103.00 kN. Isp: 450 sec. Burn time: 370 sec. Mass Engine: 245 kg. Diameter: 2.5 m. Length: 2.7 m. Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 140.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 50.00. Country: Japan. Status: In Production. First Flight: 1986. Last Flight: 1992. Flown: 9. References: 225 .
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Last update 12 March 2001.
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© Mark Wade, 2001 .