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RD-0256-HC
Part of RD-0228 Family
Kosberg LOx/Kerosene rocket engine. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Status: Design concept 1996-. Date: 1996-. Thrust: 820.00 kN (184,340 lbf). Unfuelled mass: 770 kg (1,690 lb). Specific impulse: 344 s.

Engine: 770 kg (1,690 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 108.59. Oxidizer to Fuel Ratio: 2.6.



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

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