Finite Element Analysis of Structural Strength of a UAV Composite Wing
Aiming at the force-bearing requirements of a certain type of subsonic UAV,in order to evaluate the stiffness and strength of the wing,the aerodynamic performance of the UAV was analyzed under three working conditions using CFD software,and the pressure obtained from the CFD software calculation was applied to the wing surface as an external load,then the strength of the wing was calibrated in the finite element software.The results show that the pressure on the wing surface,the deformation and stress of the wing,as well as the stress of the wing filling foam increase with the increasing side-slip angle,conversely,the stress of the wing beam decreases.The deformation of the wing is not more than 5%of the half wingspan length,the maximum stresses of the wing skin,wing beam,and wing filling foam are 62.68MPa,14.3MPa,and 0.95MPa,respectively,which are less than the allowable stresses of the materials,the strengths of each structure of the wing and the overall stiffness of the wing meet the design requirements.
wingcomposite materialfinite element analysisstructural strengthunmanned aerial vehicle
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