RD-192
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/LCH4 rocket engine. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349.
Engine: 3,300 kg (7,200 lb). Chamber Pressure: 257.00 bar. Thrust to Weight Ratio: 66.06. Oxidizer to Fuel Ratio: 3.5.
Related
- Country
- Russia
- Propellants
- Lox/LCH4
- Agency
- Glushko bureau