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RD-0133
Part of RD-0131 Family
Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump.

Status: Design concept 1996-. Date: 1996-. Thrust: 98.00 kN (22,031 lbf). Unfuelled mass: 390 kg (850 lb). Specific impulse: 467 s. Height: 1.43 m (4.69 ft).

Chambers: 4. Engine: 390 kg (850 lb). Chamber Pressure: 83.00 bar. Thrust to Weight Ratio: 25.64. Oxidizer to Fuel Ratio: 6.



Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau. Bibliography: 342.

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