RD-0234-CH

Engine · Russia

Original archive entry. The text, images and links below are kept as they were written.

Kosberg LOx/LCH4 rocket engine. Developed 1996-. Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants.

Engine: 390 kg (850 lb). Chamber Pressure: 176.00 bar. Thrust to Weight Ratio: 115.38. Oxidizer to Fuel Ratio: 3.4.

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