RD-868
Engine · Ukraine
Original archive entry. The text, images and links below are kept as they were written.
Credit: Yuzhnoye
Yuzhnoye N2O4/UDMH rocket engine. Apogee stage. Developed 1983-. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.
Burn time 1600 / 7200 sec. Oxidizer to fuel ratio 2.2 / 1.6.
Chambers: 1 + x. Engine: 203 kg (447 lb). Chamber Pressure: 91.50 bar. Thrust to Weight Ratio: 11.67. Oxidizer to Fuel Ratio: 2.2.
Related
- Family
- Storable liquid
- Country
- Ukraine
- Propellants
- N2O4/UDMH
- Agency
- Yuzhnoye
- Bibliography
- 348