RD-0256-Methane (original) (raw)

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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.

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