Computational Structural Analysis of Active Aeroelastic Wing of Unmanned Aerial Vehicle with Two Different Materials
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Abstract
Structural analysis is an essential aspect of UAV structure's design and development. The structural analysis of an Active Aeroelastic Wing (AAW) structure for an unmanned aerial vehicle was presented in this research. AAW technology is an integral effect of wing aerodynamics, controls and structure to control the wing structure. A wing structure with a twist at the tip has been created. The novelty here is not an only one fixed wing twist angle, the twist angle was varied from 0° to 10°. Mostly wing undergoes the major shape changes, leading to changes in both aerodynamic and structural characteristics. AAW configurations with different materials and twist angles were analysed to assess the structural efficiency of the UAV wing structure. The stresses due to pressure and other loads are computed using structural analysis of the wing. Numerical structural analyses have been done on the wing. The ultimate goal was to compare the computational structural analysis of an AAW with different twist angles. The wing is assumed to be a cantilever beam and static structural analysis was performed with an angular velocity of 120 rad/s.
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