RD-0140

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RD-0140

Part of RD-0120

Kosberg LOx/LNG rocket engine. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle.

Status: Developed 1998-on. Date: 1998-. Thrust: 2,086.00 kN (468,951 lbf). Unfuelled mass: 1,689 kg (3,723 lb). Specific impulse: 349 s. Specific impulse sea level: 300 s. Height: 5.04 m (16.53 ft).

Engine: 1,689 kg (3,723 lb). Thrust to Weight Ratio: 125.93.

Country: Russia. Propellants: Lox/LNG. Agency: Kosberg bureau. Bibliography: 403.

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