RD-0126A
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: KBKhA
Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.
Engine: 340 kg (740 lb). Chamber Pressure: 118.00 bar. Thrust to Weight Ratio: 29.41. Oxidizer to Fuel Ratio: 6.
Related
- Country
- Russia
- Propellants
- Lox/LH2
- Agency
- Kosberg bureau