LE-7 (original) (raw)

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LE-7

Part of H-2

LE-7

Mitsubishi LOx/LH2 rocket engine for H-2 upper stages. Staged combustion turbopump. No throttle capability. First flight 1994.

Number: 7 . Thrust: 1,078.00 kN (242,344 lbf). Unfuelled mass: 1,714 kg (3,778 lb). Specific impulse: 446 s. Specific impulse sea level: 349 s. Burn time: 346 s. Height: 3.40 m (11.10 ft). Diameter: 4.00 m (13.10 ft).

Thrust (sl): 843.500 kN (189,626 lbf). Thrust (sl): 86,018 kgf. Engine: 1,714 kg (3,778 lb). Chamber Pressure: 127.00 bar. Area Ratio: 52. Thrust to Weight Ratio: 64.1338435000121. Oxidizer to Fuel Ratio: 5.9. Coefficient of Thrust vacuum: 1.73739021790307. Coefficient of Thrust sea level: 1.32200560251845.

Subtopics

LE-7A Mitsubishi LOx/LH2 rocket engine. In production. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001.

Country: Japan. Launch Vehicles: H-II, H-II HIMES. Propellants: Lox/LH2. Stages: H-2-1. Agency: Mitsubishi. Bibliography: 225.

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