RD-0120M-CH

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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.

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