RD-0128
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps.
Engine: 370 kg (810 lb). Chamber Pressure: 118.00 bar. Thrust to Weight Ratio: 27.02. Oxidizer to Fuel Ratio: 6.
Related
- Country
- Russia
- Propellants
- Lox/LH2
- Agency
- Kosberg bureau
- Bibliography
- 342