Structural and Fatigue Analysis of a UAV Wing

Abstract

In this study, the structural and fatigue analyses of an unmanned aerial vehicle wing are investigated together. The spar, which is the main load carrier of the wing, and the ribs, which are the structural support parts that give the wing its aerodynamic shape, are analyzed using different numbers. Accordingly, 5 cases with different rip and spar numbers were examined with the finite element method. Additionally, aluminium and carbon epoxy materials were considered for the wing material in the simulations. The wall thickness for the wing is 0.5 mm and 1 mm, and the applied loads are 80 N, 150 N, and 250 N, respectively. As a result of these inputs, total deformation, maximum principal elastic strain, and fatigue analyses were performed.