Postbuckling Responses of the Panels Subjected to Combined Compression and Shear Stresses

In general, many numerical techniques are in place for the study of buckling and post-buckling responses of the composite structures, but these are computationally expensive. Relatively few equivalent analytical techniques are available, especially for evaluation of post-buckling responses. In this paper an analytical approach is presented for the determination of post-buckling responses of rectangular panels made of symmetric orthotropic laminates and supported by stiffeners (especially used in the monocoque and semi-monocoque aircraft structures), and subjected to combined compressive and shear loads, majorly based on the effective width concept. They are used to calculate the loss in the stiffness of the panels and the compressive stresses induced in the stiffening members, under a combined effect of shear and compressive stresses. For illustration, a series of parametric curves that are characteristic of the post-buckling behavior of the orthotropic panels (of aspect ratio 2.5) with transverse stiffeners have been reported.