RD-0205
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
RD-0205 8D46 on stage 8S816 (UR-200)
Credit: © Mark Wade
Kosberg N2O4/UDMH rocket engine. UR-200 stage 2. Engine unit consisting of 1 RD-0206 main engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. First flight 1963.
Engine: 552 kg (1,216 lb). Area Ratio: 48.07. Thrust to Weight Ratio: 113.2. Oxidizer to Fuel Ratio: 2.625.
Related
- Family
- Storable liquid
- Country
- Russia
- Launch Vehicles
- Initial UR-500, UR-200
- Propellants
- N2O4/UDMH
- Stages
- UR-200-2
- Agency
- Kosberg bureau
Photo Gallery
RD-0205
Credit: KBKhA
