RD-0242-HC

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RD-0242-HC

Part of RD-0242

Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.

Status: Developed 1998-. Date: 1998-. Thrust: 125.00 kN (28,101 lbf). Unfuelled mass: 120 kg (260 lb). Specific impulse: 312 s.

Engine: 120 kg (260 lb). Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 106.21. Oxidizer to Fuel Ratio: 2.6.

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

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