This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com

astronautix.com 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..
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .