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LE-5 engine
AKA: LE-5. Number: 9 . Thrust: 103.00 kN (23,155 lbf). Unfuelled mass: 245 kg (540 lb). Specific impulse: 450 s. Burn time: 370 s. Height: 2.67 m (8.75 ft). Diameter: 2.49 m (8.16 ft).
Engine: 245 kg (540 lb). Chamber Pressure: 36.00 bar. Area Ratio: 140. Thrust to Weight Ratio: 50. Oxidizer to Fuel Ratio: 5.5.
| LE-5A Mitsubishi LOx/LH2 rocket engine. Used on H-2 launch vehicle. First flight 1994. |
 | LE-5B engine 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. |
| HIMES engine Mitsubishi LOx/LH2 rocket engine. Design 1999. Used on H-2 HIMES launch vehicle. |
| LACE/LE-5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. Design 1999. Used on H-2 HIMES launch vehicle. |
| MB-35 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. |
| MB-45 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000. |
 | MB-60 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. |
Country: Japan. Launch Vehicles: H-1. Propellants: Lox/LH2. Stages: LE-5. Agency: Mitsubishi. Bibliography: 225.
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