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RD-0110
Part of RD-0106
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. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. First flight 1964.

AKA: 11D55;RD-461. Date: 1964-69. Number: 1136 . Thrust: 297.90 kN (66,971 lbf). Unfuelled mass: 408 kg (899 lb). Specific impulse: 326 s. Burn time: 250 s. Height: 1.58 m (5.18 ft). Diameter: 2.24 m (7.34 ft).

Chambers: 4. Engine: 408 kg (899 lb). Chamber Pressure: 68.20 bar. Area Ratio: 82.2. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 74.46. Oxidizer to Fuel Ratio: 2.2.

Country: Russia. Launch Vehicles: Soyuz 11A511, Molniya 8K78M, Soyuz-U, Soyuz-U2, Soyuz M. Propellants: Lox/Kerosene. Stages: Soyuz 11A511-2, Soyuz 11A511U2-2, Molniya 8K78M-2, Soyuz 11A511U-2. Agency: Kosberg bureau. Bibliography: 177, 225, 226, 307, 320, 403, 95, 7467.
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Credit: KBKhA
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Credit: KBKhA
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Credit: © Mark Wade
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