TAGRA 2025

Composite materials have become increasingly important in aerospace and automotive applications due to their high specific strength, corrosion resistance, superior fatigue properties, and inherent vibration damping capabilities. These advantages make them particularly suitable for lightweight structural components where performance, durability, and efficiency are critical design factors. In unmanned aerial vehicles (UAVs), the use of composite structures is particularly attractive because weight reduction directly contributes to increased flight time, improved maneuverability, and reduced energy consumption. This study investigates the structural behavior of a hybrid composite-metallic UAV wing configuration using finite element analysis in the ANSYS Workbench environment. The wing model integrates carbon fiber reinforced polymer (CFRP) coatings with metallic beams and ribs to provide an optimized balance between stiffness, strength, and manufacturability. Static loading, aerodynamic pressure distributions, and material-specific failure criteria are evaluated to assess the overall structural integrity of the design. Modal analysis is also performed to determine the inherent frequencies and potential resonance risks associated with UAV operational conditions. The results provide information on stress concentration regions, deformation characteristics, and the contribution of composite layers to the overall stiffness increase. Comparisons between fully metallic and hybrid configurations highlight the performance advantages and weight savings achieved through composite integration. The findings demonstrate that the hybrid composite-metallic architecture increases structural efficiency while maintaining rigidity under expected service loads. This study contributes to the development of lightweight, high-performance UAV structures and provides guidance for future design optimization and material selection.