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The erosion of rocket-nozzle ablative thermal protection materials during solid- rocket-motor burning time needs to be accounted for to get reliable performance pre- dictions, especially for long-duration firings and/or small nozzles (i.e. upper stages). This work numerically investigates the erosion behavior as a function of chamber con- ditions for the nozzles of VEGA launch vehicle solid rocket motors, Zefiro 9, Zefiro 23, and P80.
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This page is a summary of: Numerical Simulation of Chemical Erosion in VEGA Launcher Solid-Propellant Rocket Motor Nozzles, July 2015, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2015-4175.
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