RD-0210-HC

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RD-0210-HC

Part of RD-0202

Kosberg LOx/Kerosene rocket engine. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Status: Design concept 1990's. Thrust: 592.00 kN (133,086 lbf). Unfuelled mass: 570 kg (1,250 lb). Specific impulse: 342 s.

Engine: 570 kg (1,250 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 105.9. Oxidizer to Fuel Ratio: 2.6.

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

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