This page no longer updated from 31 October 2001. Latest version can be found at RD-192S

Manufacturer Name: RD-192S. Designer: Glushko. Developed in: 1996-. Propellants: Lox/LCH4 Thrust(vac): 217,000 kgf. Thrust(vac): 2,128.00 kN. Isp: 372 sec. Diameter: 2.4 m. Length: 4.8 m. Chambers: 1. Chamber Pressure: 196.00 bar. Oxidizer to Fuel Ratio: 3.50. Country: Russia. Status: Developed 1996-on. References: 402 . Comments: Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes. Status 1998 project based on RD-191 protoype, development estimated for four years.
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Last update 12 March 2001.
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© Mark Wade, 2001 .