LE-5B engine
Engine · Japan
Original archive entry. The text, images and links below are kept as they were written.
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.
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.
Related
- Country
- Japan
- Launch Vehicles
- H-IIA 212, H-IIA 2024
- Propellants
- Lox/LH2
- Stages
- LE-5B
- Agency
- Mitsubishi
- Bibliography
- 225