Manipulation of optimal size-weight project parameters of composite structurally anisotropic aircraft panels with restrictions according to the refined buckling theory

This article discusses the challenge of defining the geometry parameters for minimum mass stiffened aircraft panels made of composite materials. The thickness and size of the panel elements are unknown variables, and the optimal design is based on the condition of equal buckling. To solve this problem, the authors reduce the optimal design problem to the investigation of the weight function with multiple variables using analytical methods and refined buckling theory restrictions. The article introduces novel mathematical relationships for investigating the buckling of structurally anisotropic composite panels. The model couples bending with a plane stress state, resulting in a boundary value problem that involves solving an eighth-order partial differential equation within a rectangular field. To facilitate this, a software package was developed using the MATLAB operating environment. A set of computer programs was created to conduct multi-criteria optimization of the optimal design of structurally anisotropic aircraft composite panels. The study also examines the impact of design parameters on the critical buckling forces for both bending and torsion modes. The results of a new implementation of an optimal size-weight project for carbon-epoxy skin are given. A project with restrictions on the refined buckling theory for structurally anisotropic aircraft panels made of composite materials has been manipulated in terms of plies thicknesses. Optimal solutions are obtained.