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Abstract

A method for dimensioning of panels stiffened by triangular pockets that make it possible to take into account aeronautical specifics and more particularly the stresses that are admissible for the different types of buckling and the calculations of adapted reserve factors is presented. The method relates to dimensioning of a substantially plane panel of homogeneous and isotropic material by an analytical procedure, wherein the panel is composed of a skin reinforced by an assembly of three parallel bundles of stiffeners integrated with the panel, and triangular pockets defined on the skin, the stiffeners are strip-shaped and the panel must satisfy a specification of mechanical resistance to predetermined external loads, including steps organized in such a way that they can be repeated iteratively for different values of input data until reserve factors are obtained to determine the dimensions and arrangement of the panel elements necessary to obtain the imposed mechanical resistance.

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First Claim