RD-0132

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RD-0132

Part of RD-0131

Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump.

Status: Design concept 1996-. Date: 1996-. Thrust: 98.00 kN (22,031 lbf). Unfuelled mass: 370 kg (810 lb). Specific impulse: 469 s. Height: 1.38 m (4.52 ft).

Chambers: 4. Engine: 370 kg (810 lb). Chamber Pressure: 98.00 bar. Thrust to Weight Ratio: 27.02. Oxidizer to Fuel Ratio: 5.9.

Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau. Bibliography: 327, 342.

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