RD-0234-HC

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RD-0234-HC

Part of RD-0234

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

Status: Developed 1996-. Date: 1996-. Thrust: 516.00 kN (116,001 lbf). Unfuelled mass: 390 kg (850 lb). Specific impulse: 331 s. Specific impulse sea level: 310 s.

Engine: 390 kg (850 lb). Chamber Pressure: 196.00 bar. Thrust to Weight Ratio: 134.91. Oxidizer to Fuel Ratio: 2.6.

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

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