Finite element analysis of an unmanned aerial-vehicle wing under compressive loading combined with optical testing

doi:10.16731/j.cnki.1671-3133.2018.09.017

Abstract

Abstract: A full-scale ANSYS model of one UAV wing was developed to carry out Finite Element Analysis(FEA).Nonlinear contact algorithm was performed to mainly study the effects of algorithm types with different normal stiffness factors and penetration tolerances on the iteration number and the model stiffness.Deformation process of the wing under a compressive loading condition was directly investigated by using the Three-Dimensional Digital Image Correlation(3D-DIC) technique.The numerical results agree well with experimental measurements,showing that the finite element model is rational.Finally,the stress distributions of wing skin and internal components were predicted,which provided a beneficial reference for further modifications.

Key words: wing structure, finite element analysis, contact analysis, three-dimensional digital image correlation, stress distributions

CLC Number:

TP391.9

Li Xiangping, Liu Haicong. Finite element analysis of an unmanned aerial-vehicle wing under compressive loading combined with optical testing[J]. Modern Manufacturing Engineering, 2018, 456(9): 88-93.

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Finite element analysis of an unmanned aerial-vehicle wing under compressive loading combined with optical testing

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