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RD-161-1
Part of RD-160 Family
Glushko LOx/Kerosene rocket engine. Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump.

AKA: RD-161 (1). Status: Development ended 2000. Thrust: 19.60 kN (4,406 lbf). Unfuelled mass: 119 kg (262 lb). Specific impulse: 360 s. Burn time: 900 s. Height: 1.70 m (5.50 ft). Diameter: 0.78 m (2.55 ft).

Engine: 119 kg (262 lb). Chamber Pressure: 117.70 bar. Area Ratio: 351.6. Thrust to Weight Ratio: 16.8. Oxidizer to Fuel Ratio: 2.6.



Country: Russia. Propellants: Lox/Kerosene. Stages: Soyuz M-3. Agency: Glushko bureau. Bibliography: 318.

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