This page no longer updated from 31 October 2001. Latest version can be found at RS-X

Designer: Rocketdyne. Propellants: Lox/Kerosene Thrust(vac): 192,730 kgf. Thrust(vac): 1,890.00 kN. Chambers: 1. Country: USA. Status: Design concept -1997. Comments: A system studied at Rocketdyne which was a derivative of the MA and RS systems for ELV applications. The RS-X would employ existing Delta and Atlas engine hardware on a new thrust chamber assembly to generate a thrust of 1890 kN..
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Last update 12 March 2001.
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© Mark Wade, 2001 .