Analytical methodology for the design of load-bearing anisotropic panels for the wingbox of a light aircraft subject to geometric nonlinearity under compression

Year 2024, Volume: 42 Issue: 6, 1756 - 1762, 09.12.2024

Oleg Mitrofanov Maksim Shkurin

https://izlik.org/JA63RD66CA

Abstract

The subject of this research is the upper load-bearing anisotropic panels of the wingbox of the forward-swept wing of a light aircraft, exposed mainly to longitudinal compression. The panels are fixed along the long sides. The paper considers how to determine the minimum thickness of these panels at a postbuckling state under loads exceeding the operational level. Based on the analytical solution for geometrically nonlinear problems obtained by the Bub-nov-Galerkin method, a technique for designing anisotropic panels at a postbuckling state is proposed. To determine the panel’s thickness, the strength criteria for a monolayer of the composite material were used. The main result of the work is a nonlinear equation for the panel’s minimum thickness. It incorporates the equivalence of the membrane stresses due to panel buckling and the limit stresses of the composite package monolayer.

Keywords

Geometrically Non-Linear Behavior , Anisotropic Material , Rectangular Panels , Longitudinal Compression

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