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Designer: Mitsubishi. Developed in: 1995-2001. Propellants: Lox/LH2. Thrust(vac): 1,098.000 kN (246,840 lbf). Isp: 438 sec. Isp (sea level): 338 sec. Burn time: 390 sec. Mass Engine: 1,800 kg (3,900 lb). Length: 3.67 m (12.04 ft). Chambers: 1. Chamber Pressure: 121.00 bar. Area Ratio: 51.90. Oxidizer to Fuel Ratio: 5.90. Country: Japan. Status: In production. First Flight: 2001. Last Flight: 2006. Flown: 10. The LE-7A rocket engine, developed for the first stage of the H-II rocket, had a two stage combustion cycle system, and was an improved model of the original LE-7 engine. The improvements were made as a result of the severe competition in the artificial satellite business worldwide, and the resulting need to lower the cost of the H-II vehicle for the H-IIA model. The changes were targeted to increase the reliability, improve the operability, and decrease the cost for the first stage engine for the H-IIA rocket. The result was a simplified, lower cost version of LE-7 with a staged combustion turbopump that could be throttled to 72% of rated thrust.
LE-7A used on Rocket Stages
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