Abstract
Abstract For the preliminary structural design of aircraft, spacecraft and marine vessels, computationally efficient and sufficiently accurate computational methods are necessary. The present work contributes to this field by deriving a new closed-form analytical solution for the local buckling analysis of omega-stringer-stiffened composite panels. Hereby, the plates of the assembly are modelled separately and include the stiffener foot. The principle of the minimum potential energy is used in a Ritz-like approach and leads to an explicit analytical formulation of the critical buckling load. The compliance to geometric and dynamic boundary conditions is ensured. The panel is uniaxially loaded and investigated for different geometrical and material configurations. For the verification of the presented method, a finite element analysis is performed as well as a solution of the Levy type is obtained. Very good agreement of the new closed-form analytical approach with finite element analyses is shown in numerical studies for technical relevant areas of the design space.
Published Version
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