For the purpose of optimizing the design of stiffened composite laminates in compression, numerical results from a layerwise (zig-zag) finite element model are presented. The laminate is subdivided into element layers in the thickness direction. The element layers and stiffeners are modeled using the degenerated shell element and general 3-D beam element, respectively. The advantage of this model is its ability to predict the effects of the lateral stability of the stiffener on the buckling of the laminate itself. The influence of the degree of orthotropy, laminate aspect ratio, and laminate layouts, as well as the stiffener orientation and sectional dimensions, are investigated through parametric studies. The significance of this study lies in the ability of the proposed finite element model to predict the optimum stiffener depth and ply-angle of the laminate. The findings clearly show that deeper stiffeners do not always lead to stiffer composite laminates.
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