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LE-5B engine


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LE-5B Mitsubishi LOx/LH2 rocket engine. In production. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001.

AKA: LE-5B. Status: In production. Date: 1995-2001. Number: 10 . Thrust: 137.00 kN (30,798 lbf). Unfuelled mass: 269 kg (593 lb). Specific impulse: 447 s. Burn time: 534 s. Height: 2.78 m (9.13 ft).

The result was a simplified, lower cost version of the LE-5A using an expander bleed cycle turbopump. The engine could be throttled to 5% idle mode.

Engine: 269 kg (593 lb). Chamber Pressure: 36.00 bar. Area Ratio: 110. Oxidizer to Fuel Ratio: 5.

Country: Japan. Launch Vehicles: H-IIA 212, H-IIA 2024. Propellants: Lox/LH2. Stages: LE-5B. Agency: Mitsubishi. Bibliography: 225. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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