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-0256-Methane
Part of RD-0228
Kosberg LOx/LCH4 rocket engine. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.

AKA: RD-0256-Methan. Status: Design concept 1996-. Date: 1996-. Thrust: 836.00 kN (187,940 lbf). Unfuelled mass: 770 kg (1,690 lb). Specific impulse: 353 s.

Engine: 770 kg (1,690 lb). Chamber Pressure: 176.00 bar. Thrust to Weight Ratio: 110.71. Oxidizer to Fuel Ratio: 3.4.



Country: Russia. Propellants: Lox/LCH4. Agency: Kosberg bureau.

Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use