LE-7
Engine · Japan
Original archive entry. The text, images and links below are kept as they were written.
Mitsubishi LOx/LH2 rocket engine for H-2 upper stages. Staged combustion turbopump. No throttle capability. First flight 1994.
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.
Related
- Country
- Japan
- Launch Vehicles
- H-II, H-II HIMES
- Propellants
- Lox/LH2
- Stages
- H-2-1
- Agency
- Mitsubishi
- Bibliography
- 225