RD-161P
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko H2O2/Kerosene rocket engine. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%.
Throttled thrust(vac): 14.700 kN (3,305 lbf). Engine: 105 kg (231 lb). Chamber Pressure: 117.70 bar. Area Ratio: 265. Thrust to Weight Ratio: 23.79. Oxidizer to Fuel Ratio: 5.9.
Related
- Country
- Russia
- Launch Vehicles
- Soyuz M
- Propellants
- H2O2/Kerosene
- Agency
- Glushko bureau
- Bibliography
- 318