|
RD-0120-CH
|
|
Manufacturer Name: RD-0120-CH. Designer: Kosberg. Propellants: Lox/LCH4. Thrust(vac): 1,576.000 kN (354,298 lbf). Isp: 363 sec. Mass Engine: 2,370 kg (5,220 lb). Chambers: 1. Chamber Pressure: 172.50 bar. Oxidizer to Fuel Ratio: 3.40. Thrust to Weight Ratio: 67.80. Country: Russia. Status: Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant.
Bibliography and Further Reading - Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|