Carbon fiber reinforced plastic (CFRP) stiffened structures exhibit several advantages over those constructed from metallic materials, particularly in terms of their high specific mechanical properties. Whereas nowadays the applications of CFRP structures are becoming more and more both in aeronautical and mechanical industries, their efficient use is restricted by the limited availability of buckling design criteria, mainly due to uncertainties related to the behaviour of these structures under repeated cyclic buckling, Singer et al. [1]. This paper presents some results obtained during an European research project, COCOMAT (Improved MATerial Exploitation at Safe Design of COmposite Airframe Structures by Accurate Simulation of Collapse) on stringer stiffened composite panels subjected to cyclic buckling, Degenhardt et al. [2]. Presented results are part of an investigation carried out for understanding what happens to the post-buckling field of such a structure after that the buckling load is reached Thousands of times.
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