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-0140
Part of RD-0120 Family
Kosberg LOx/LNG rocket engine. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle.

Status: Developed 1998-on. Date: 1998-. Thrust: 2,086.00 kN (468,951 lbf). Unfuelled mass: 1,689 kg (3,723 lb). Specific impulse: 349 s. Specific impulse sea level: 300 s. Height: 5.04 m (16.53 ft).

Engine: 1,689 kg (3,723 lb). Thrust to Weight Ratio: 125.93.



Country: Russia. Propellants: Lox/LNG. Agency: Kosberg bureau. Bibliography: 403.

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
© 1997-2017 Mark Wade - Contact
© / Conditions for Use