LE-5 engine
Engine · Japan
Original archive entry. The text, images and links below are kept as they were written.
Mitsubishi LOx/LH2 rocket engine. Used on H-1 launch vehicle. First flight 1986.
Engine: 245 kg (540 lb). Chamber Pressure: 36.00 bar. Area Ratio: 140. Thrust to Weight Ratio: 50. Oxidizer to Fuel Ratio: 5.5.
Subtopics
- 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.