Buckling is possible for thin composite skins of light aircraft wing high-lift devices loaded above limit level. Aim of this work is to create a method for orthotropic panels minimal thickness definition with possible post-buckling behavior considering residual strength support. Hinge supported composite panels loaded in compression and shear jointly are considered. Method based on analytic solution of non-linear problem and design method by post-buckling state is suggested in the paper. In order to explain peculiarities of above-mentioned method examples of panels design loaded with tangential force supporting strength and stability are shown in this work. It is demonstrated that for panels minimal thickness calculation by strength, stability, and post-buckling behavior conditions corresponding linear, second- and third-degree equations in unknown thicknesses are derived. In order to develop design method by post-buckling state with combined loading analytic solution of non-linear problem using Bubnov-Galerkin method is shown in the paper. Chai criterion including all components of acting forces and stress critical values for residual strength has been used for composite package based on the conditions of combined loading. Variants of developed applied methods of design based on post-buckling state with only tangential force acting and with combined loading by compression and shear flows are shown in this work.
Geometrically non-linear problem of orthotropic thin rectangular panel post-buckling behavior with shear is solved. Deflection function takes all-boundary rigid support conditions into account. Based on derived solution method of smooth panels design which can be used for aircraft structures rib and spar webs optimal parameters is suggested.
Analytical solution of geometrically non-linear problem of post-buckling behavior of thin rectangular plate of asymmetric structure with shear taking rigid support along all sides into account is obtained. Shown solution can be used for post-buckling behavior estimation of surface defect similar to delamination for composite panels.
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