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RD-161P
Part of RD-160 Family
Glushko H2O2/Kerosene rocket engine. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%.

Status: Developed 1993-. Date: 1993-. Thrust: 24.50 kN (5,508 lbf). Unfuelled mass: 105 kg (231 lb). Specific impulse: 319 s. Burn time: 900 s. Height: 1.45 m (4.75 ft). Diameter: 1.24 m (4.06 ft).

Throttled thrust(vac): 14.700 kN (3,305 lbf). Engine: 105 kg (231 lb). Chamber Pressure: 117.70 bar. Area Ratio: 265. Thrust to Weight Ratio: 23.79. Oxidizer to Fuel Ratio: 5.9.



Country: Russia. Launch Vehicles: Soyuz M. Propellants: H2O2/Kerosene. Agency: Glushko bureau. Bibliography: 318.

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