RD-161-2

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

RD-161-2

Part of RD-160

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.

AKA: RD-161 (2). Status: Design concept 1990's. Thrust: 19.90 kN (4,474 lbf). Unfuelled mass: 141 kg (310 lb). Specific impulse: 365 s. Burn time: 900 s. Height: 2.21 m (7.25 ft). Diameter: 1.02 m (3.34 ft).

Engine: 141 kg (310 lb). Chamber Pressure: 117.70 bar. Area Ratio: 370.6. Thrust to Weight Ratio: 14.39. Oxidizer to Fuel Ratio: 2.6.

Country: Russia. Propellants: Lox/Kerosene. Agency: Glushko bureau. Bibliography: 318.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z