RD-0155

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RD-0155

RD-0155
Credit: KBKhA

Kosberg LOx/Kerosene rocket engine. Engine proposed to replace RD-107 in Onega and Avrora versions of the Soyuz launch vehicle.

Status: Design concept 2007. Date: 1998-. Thrust: 902.50 kN (202,890 lbf). Specific impulse: 296 s. Specific impulse sea level: 296 s.

The engine consists of two chambers, a fixed inner chamber and a gimbaled outer chamber. Chamber pressure in the fixed chamber, 180 kg/m2; in the gimbaled chamber, 160 kg/m2.

Chambers: 2. Thrust (sl): 902.500 kN (202,890 lbf). Thrust (sl): 92,000 kgf. Engine: 1,150 kg (2,530 lb). Chamber Pressure: 176.00 bar.

Country: Russia. Propellants: Lox/Kerosene. Agency: Kosberg bureau. Bibliography: 4484.

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