RD-0120M-CH
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/LCH4 rocket engine. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.
Engine: 2,600 kg (5,700 lb). Chamber Pressure: 186.00 bar. Thrust to Weight Ratio: 67.45. Oxidizer to Fuel Ratio: 3.4.
Related
- Country
- Russia
- Propellants
- Lox/LCH4
- Agency
- Kosberg bureau