RD-0210
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965.
Oxidizer pre-burner gas routed to main chamber after driving turbine.
Engine: 566 kg (1,247 lb). Chamber Pressure: 147.00 bar. Area Ratio: 81.3. Thrust to Weight Ratio: 104.87.
Related
- Family
- Storable liquid
- Country
- Russia
- Launch Vehicles
- UR-500, Proton-K, Proton-K/D, Proton-K/DM, Proton-K/D-1, Proton-K/DM-2, Proton-K/DM-2 DM1, Proton-K/D-2, Proton-K/17S40, Proton-K/17S40 DM2, Proton-K/DM-2M DM3
- Propellants
- N2O4/UDMH
- Stages
- UR-700-4, UR-500-2, Proton K-2
- Agency
- Kosberg bureau