This page no longer updated from 31 October 2001.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-1-2. Used on launch vehicles: H-2A 212, H-2A 2024. Propellants: Lox/LH2 Thrust(vac): 14,000 kgf. Thrust(vac): 137.00 kN. Isp: 447 sec. Burn time: 534 sec. Chambers: 1. Chamber Pressure: 36.00 bar. Area Ratio: 110.00. Oxidizer to Fuel Ratio: 5.00. Country: Japan. Status: In Production. First Flight: 1986. Last Flight: 1992. Flown: 9. References: 225 . Comments: Simplified, lower cost version of LE-5A. Expander bleed cycle turbopump. Can be throttled to 5% idle mode.
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Last update 12 March 2001.
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© Mark Wade, 2001 .