This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Manufacturer Name: RD-0120M-CH. Designer: Kosberg. Propellants: Lox/LCH4 Thrust(vac): 175,391 kgf. Thrust(vac): 1,720.00 kN. Isp: 372 sec. Mass Engine: 2,600 kg. Chambers: 1. Chamber Pressure: 186.00 bar. Oxidizer to Fuel Ratio: 3.40. Country: Russia. Status: Design concept 1990's. References: 342 . Comments: Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .