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RD-108-11D512
Part of RD-107
R-7 aft end
Credit: © Mark Wade
Glushko LOx/Kerosene rocket engine. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. First flight 1965.
AKA: 11D512. Status: Design 2000. Number: 752 . Thrust: 997.00 kN (224,134 lbf). Unfuelled mass: 1,400 kg (3,000 lb). Specific impulse: 315 s. Specific impulse sea level: 248 s. Burn time: 286 s. Height: 2.86 m (9.38 ft). Diameter: 0.67 m (2.19 ft).
Chambers: 4. Thrust (sl): 746.400 kN (167,797 lbf). Thrust (sl): 76,100 kgf. Engine: 1,400 kg (3,000 lb). Chamber Pressure: 51.00 bar. Thrust to Weight Ratio: 72.59.
Country:
Russia.
Launch Vehicles:
Soyuz 11A511,
Soyuz-U.
Propellants:
Lox/Kerosene.
Stages:
Soyuz 11A511-1,
Soyuz 11A511U-1.
Agency:
Glushko bureau.
Bibliography:
173,
21,
225,
287.
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| RD-107 Credit: © Mark Wade |
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