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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
