Abstract
Honeycomb sandwich panels are kind of composite panels constructed by bonding core material of honeycomb structures with thin plate surfaces together. Since honeycomb sandwich panels (Briefly called composite panels) have the light-weight and high strength performances, they are widely utilized in many fields, especially light-weight required aerospace field. However, data on impact resistant properties of such composite panels are not widely publicized, and the testing method is not clearly specified. Therefore, in this study, the local buckling tendency of composite panels was experimentally evaluated with respect to various design variables, such as the foil thickness, cell size and specimen dimension of honeycomb structures. As conclusion, under local compressive loading for honeycomb sandwich panels, honeycomb cores are buckled before reaching yielded points and cause the danger of panles being degraded from their original levels.
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