Abstract
The article considers the results of multicriteria optimization of the unmanned aircraft composite wing. Minimum deflection, mass and normal stresses acting along the reinforcement directions are taken as optimization criteria. The thicknesses of the load-bearing frame elements and wing skin elements were selected as optimization parameters for three types of composites: carbon fiber reinforced plastic (CFRP) based on unidirectional carbon layers, CFRP based on carbon fabric layers, and fiberglass laminate based on E-glass fiberglass. A checking calculation of the optimal composite wing stability was performed using a geometrically nonlinear model. The calculation of the stress-strain state of the wing was performed using an anisotropic linear elastic material model. Calculations were carried out using finite element software packages ANSYS and FEMAP.
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