The Space Shuttle Columbia was lost due to an impact on the reinforced carbon-carbon leading edge. This paper recounts analysis performed during the Columbia accident investigation to understand foam insulation impacts on the leading edge panels, part of the shuttle's thermal protection system. The study was carried out through large-scale numerical simulation. A numerical model was developed to model the reinforced carbon-carbon panels that comprise the leading edge. An analytic boundary condition was developed to represent the foam impact. Dynamic computations were then performed with the model to determine stress levels and histories within the panel and its ribs. Comparisons were made with results of the two tests performed during the investigation. The model developed in this work was used to explore questions such as impact location and its effect on the stresses seen in the panel face and ribs and the effect of foam impactor rotational velocity on the stress levels.
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