Dynamic and aeroelastic analysis of UAV wing with moving force, moving moment and moving torque

Next-generation UAV wing configurations featuring span morphing or moving mass actuation mechanisms offer solutions to limitations in aerodynamic performance and control authority found in traditional designs. This study investigates the aeroelastic response of such a UAV wing subjected to not only aerodynamic loads but also moving force, moment, and torque along the span. This study mathematically models the structural dynamics due to the dynamic motion of the loads. For aeroelastic analysis, the unsteady aerodynamic effects are captured using Wagner’s formulations. The wing’s response is analysed across four phases of load movement: (I) motion from root to tip, (II) static loading at the tip, (III) return motion to the root, and (IV) free vibration after motion. Simulations show that aerodynamic damping significantly reduces bending vibrations, particularly at lower speeds, but has less influence on torsional motion. The results highlight Phase III as the most critical for design due to its higher oscillation frequencies and amplitudes. Key design recommendations include increasing torsional stiffness and accounting for dynamic effects during reverse load motion. These findings provide valuable guidance for improving the aeroelastic stability and structural integrity of advanced UAV wings under dynamic loading conditions.