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Engine Model: RD-161-1. Manufacturer Name: RD-161 (1). Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 19.600 kN (4,406 lbf). Isp: 360 sec. Burn time: 900 sec. Mass Engine: 119 kg (262 lb). Diameter: 0.78 m (2.55 ft). Length: 1.70 m (5.50 ft). Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 351.60. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 16.80. Country: Russia. Status: Development ended 2000.

Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump.

Engine Model: RD-161-2. Manufacturer Name: RD-161 (2). Designer: Glushko. Propellants: Lox/Kerosene. Thrust(vac): 19.900 kN (4,474 lbf). Isp: 365 sec. Burn time: 900 sec. Mass Engine: 141 kg (310 lb). Diameter: 1.02 m (3.34 ft). Length: 2.21 m (7.25 ft). Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 370.60. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 14.39. Country: Russia. Status: Design concept 1990's.

Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump.

Engine Model: RD-161P. Manufacturer Name: RD-161P. Designer: Glushko. Developed in: 1993-. Application: Soyuz M stage 3 (block LM). Propellants: H2O2/Kerosene. Thrust(vac): 24.500 kN (5,508 lbf). Throttled thrust(vac): 14.700 kN (3,305 lbf). Isp: 319 sec. Burn time: 900 sec. Mass Engine: 105 kg (231 lb). Diameter: 1.24 m (4.06 ft). Length: 1.45 m (4.75 ft). Chambers: 1. Chamber Pressure: 117.70 bar. Area Ratio: 265.00. Oxidizer to Fuel Ratio: 5.90. Thrust to Weight Ratio: 23.79. Country: Russia. Status: Developed 1993-.

Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%.

RD-161 used on Rocket Stages
  • Used on stage: Block L. on launch vehicle: N1.
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