Research objects in the paper include the upper metal load-bearing reinforced panels of the medium-duty aircraft wing caisson, which are loaded with the compressive and tangential forces. Stability loss in the skins exposed to loads close to the operational level is considered acceptable. In this case, the skins are classified as the medium-thick plates. Analysis of their geometrically nonlinear behavior should take into account the membrane and bending stresses. The paper proposes applied methods (algorithms) in determining the minimum thickness of skins loaded with compressive, tangential and combined forces with the acceptable initial stage of the geometrically nonlinear behavior. These methods (algorithms) are based on introducing analytical solutions to the geometrically nonlinear problems obtained by the Bubnov — Galerkin method. The paper formulates issues of the general methodology (algorithm) to determine the metal panel minimum thickness taking into account the membrane and bending stresses arising in the postbuckling state. Besides, it presents specifics of the applied methods (algorithms) in the panels’ design taking into consideration the two loading levels. In this case, it becomes necessary in the postbuckling state to ensure stability at the first loading level and strength at the second.

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