This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Mitsubishi. Developed in: 1995-2001. Used on stages: H-2A-1. Used on launch vehicles: H-2A 2024, H-2A 212. Propellants: Lox/LH2 Thrust(vac): 112,000 kgf. Thrust(vac): 1,098.00 kN. Isp: 440 sec. Isp (sea level): 338 sec. Burn time: 390 sec. Chambers: 1. Chamber Pressure: 121.00 bar. Area Ratio: 51.90. Oxidizer to Fuel Ratio: 5.90. Country: Japan. Status: In Development. Comments: Simplified, lower cost version of LE-7. Staged combustion turbopump. Can be throttled to 72%.
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Last update 12 March 2001.
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© Mark Wade, 2001 .