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RD-192
Part of RD-170 Family
Glushko LOx/LCH4 rocket engine. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349.

Status: Developed 1996-. Date: 1996-. Thrust: 2,138.00 kN (480,641 lbf). Unfuelled mass: 3,300 kg (7,200 lb). Specific impulse: 356 s. Specific impulse sea level: 330 s. Height: 4.05 m (13.28 ft). Diameter: 2.00 m (6.50 ft).

Engine: 3,300 kg (7,200 lb). Chamber Pressure: 257.00 bar. Thrust to Weight Ratio: 66.06. Oxidizer to Fuel Ratio: 3.5.



Country: Russia. Propellants: Lox/LCH4. Agency: Glushko bureau. Bibliography: 325, 402.

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