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RD-0108
Part of RD-0106 Family
RD-0110 Engine
RD-0110 Engine
Soyuz 11A511 Stage 2 engine displayed at Tsiolkovskiy Museum in Kaluga.
Credit: © Mark Wade
Kosberg LOx/Kerosene rocket engine. Voskhod 11A57, Molniya 8K78 stage 3. First flight 1960.

AKA: 11D55;8D715K;8D715P;RD-461;RD-461, 11D55, 8D715K, RO-8;RO-8. Date: 1961-65. Number: 326 . Thrust: 297.90 kN (66,971 lbf). Unfuelled mass: 410 kg (900 lb). Specific impulse: 326 s. Burn time: 250 s. Diameter: 0.64 m (2.09 ft).

Chambers: 4. Engine: 410 kg (900 lb). Chamber Pressure: 68.20 bar. Propellant Formulation: Lox/T-1. Thrust to Weight Ratio: 74.09.



Country: Russia. Launch Vehicles: Molniya 8K78, Voskhod 11A57. Propellants: Lox/Kerosene. Stages: Molniya 8K78-2, Voskhod 11A57-2. Agency: Kosberg bureau. Bibliography: 177, 7465.

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