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Designer: Mitsubishi. Used on stages: H-2-1. Used on launch vehicles: H-2, H-2 HIMES. Propellants: Lox/LH2 Thrust(vac): 109,925 kgf. Thrust(vac): 1,078.00 kN. Isp: 446 sec. Isp (sea level): 349 sec. Burn time: 346 sec. Mass Engine: 1,714 kg. Diameter: 4.0 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 127.00 bar. Area Ratio: 52.00. Oxidizer to Fuel Ratio: 5.90. Thrust to Weight Ratio: 64.13. Country: Japan. Status: In Production. First Flight: 1994. Last Flight: 1998. Flown: 6. References: 225 . Comments: Staged combustion turbopump. No throttle capability.
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Last update 12 March 2001.
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© Mark Wade, 2001 .