Abstract
In modern passenger aircraft, polymeric composite materials (PCM) are used to ensure the mass excellence of both lightly loaded elements and aggregates, including wings and feathers caissons. The use of such materials instead of metal alloys makes it possible to reduce the weight of structures, increase the service life, and reduce the complexity of manufacturing and material consumption. Based on the finite element method, a caisson model was created using shell finite elements (FE), considering the anisotropic properties of PCM. To solve the problems of buckling of the elements of the caisson from the PCM, a method of analytical optimization of the stringers pitch and web plates has been developed. Analytical calculation of the local model based on the loads obtained from the global shell finite element model (FEM). The developed methodology allows obtaining a design of a caisson with a minimum mass while maintaining the necessary stiffness and strength characteristics.
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