Modelling, Simulation and Analysis of a High-Speed Wing of the UAV

This paper investigates a high-speed experimental wing for an unmanned aerial vehicle (UAV) using software like CATIA, HYPERMESH, and NASTRAN. The analysis includes modal, static structural, and buckling analysis using NASTRAN. The wing of UAV is made of Glass fiber reinforced polymer (GFRP) composite. The result from this study meets the standard allowable parameters for stress, strain, displacement, failure index and buckling factor during 2g maneuver at a velocity of 120 m/s. The modal analysis results showed that the connections are perfect and there are no free components. The linear static structural analysis gave the values which are within the allowable limits. The failure index is found to be 0.16 and the buckling factor is 1.267 which indicates that the structure is resistant to buckling.