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

Status: Developed 1996-. Date: 1996-. Thrust: 442.00 kN (99,365 lbf). Unfuelled mass: 390 kg (850 lb). Specific impulse: 343 s. Specific impulse sea level: 310 s.

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



Country: Russia. Propellants: Lox/LCH4. Agency: Kosberg bureau.

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