RD-0244-HC
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/Kerosene rocket engine. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
Engine: 540 kg (1,190 lb). Chamber Pressure: 230.00 bar. Thrust to Weight Ratio: 130.29. Oxidizer to Fuel Ratio: 2.7.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Agency
- Kosberg bureau