Recent advancements in communications, materials technology and fabrication technology tends to improvisation in design and structural ability of economical UAV’s to serve as a multipurpose utility tool in different sectors viz., scientific, civil, agriculture and military sectors. The paper describes the design and structural analysis of a fixed wing UAV for a selected airfoil profile. The paper also describes the conditions and constraints assumed during the design of an UAV and the importance of structural analysis. The design is done in CATIA V5 and structural analysis using ANSYS workbench. Individual parts are designed and are then assembled as per the constraints involved. The structural analysis is done considering the wing to be made of depron foam and assuming the wing to be a cantilever beam.
A et al. (Mon,) studied this question.
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