RD-160
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/LCH4 rocket engine. Upper stage. Developed 1993-1996. Methane version of LOx / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes.
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.
Subtopics
- 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.
Related
- Country
- Russia
- Propellants
- Lox/LCH4
- Agency
- Glushko bureau
- Bibliography
- 325