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-0120M-CH
Part of RD-0120
Kosberg LOx/LCH4 rocket engine. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.

Status: Design concept 1990's. Thrust: 1,720.00 kN (386,670 lbf). Unfuelled mass: 2,600 kg (5,700 lb). Specific impulse: 372 s.

Engine: 2,600 kg (5,700 lb). Chamber Pressure: 186.00 bar. Thrust to Weight Ratio: 67.45. 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