Encyclopedia entry

RD-0245-HC

Engine · Russia

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

Kosberg LOx/Kerosene rocket engine. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Chambers: 4. Engine: 290 kg (630 lb). Chamber Pressure: 142.00 bar. Thrust to Weight Ratio: 75.24. Oxidizer to Fuel Ratio: 2.3.

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