RD-0210

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RD-0210

Part of RD-0202

RD-0210
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.

AKA: 8D411K;8D49;RD-465;RD-465, 8D49. Date: 1962-65. Number: 1240 . Thrust: 582.10 kN (130,861 lbf). Unfuelled mass: 566 kg (1,247 lb). Specific impulse: 327 s. Burn time: 230 s. Height: 2.33 m (7.64 ft). Diameter: 1.47 m (4.82 ft).

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.

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. Bibliography: 307, 342, 95, 7479.

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