DST-200A
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Isayev N2O4/UDMH rocket engine. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST-200. 100,0000 ignitions.
Engine: 1.70 kg (3.70 lb). Chamber Pressure: 7.00 bar. Area Ratio: 100. Thrust to Weight Ratio: 11.76. Oxidizer to Fuel Ratio: 1.85.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Agency
- Isayev bureau
- Bibliography
- 350