Abstract
The paper deals with the analysis of the effective stiffness of stiffened metallic panels under combined compression and shear stress as used, for example, in aircraft fuselages. The first part presents the realization of the compression and shear test facility in a finite element model. Verification of the finite element model is important for subsequent parameter variations. The second part of the paper presents the approach used to find the effective skin stiffness. On the one hand, a comparison between the results for pure compression stress and the effective width method is made and, on the other hand, the results for pure shear stress are compared with the method of Kuhn. A new approach is derived from the finite element results for combined compression and shear stress. Further parametric studies are necessary to verify the new method.
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