Status: Developed 1993-. Date: 1993-. Thrust: 19.60 kN (4,406 lbf). Unfuelled mass: 129 kg (284 lb). Specific impulse: 381 s. Burn time: 900 s. Height: 1.70 m (5.50 ft). Diameter: 0.76 m (2.51 ft).
In 1996 the RD-161 prototype had been completed, development of a methane version was estimated to take four years. Nozzle expansion ratio is 120/0.05=2400.
Engine: 129 kg (284 lb). Chamber Pressure: 118.00 bar. Area Ratio: 352. Thrust to Weight Ratio: 15.5. Oxidizer to Fuel Ratio: 3.69.
|RD-161P 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%.|
|RD-161-2 Glushko LOx/Kerosene rocket engine. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump.|
|RD-161-1 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.|