Design and reliability study of folding wing mechanism for unmanned aerial vehicle (UAV)

This study presents the design and investigation of a novel unmanned wing mechanism, which employs a crank-slider configuration driven by a linear motor. The proposed mechanism offers high efficiency, a compact structural layout, and precise controllability. It effectively addresses several reliability concerns associated with conventional folding mechanisms commonly used in small unmanned aerial vehicles. A mathematical model of the mechanism is established using the complex vector method, and the kinematic relationships among the linkages are derived. The kinematic performance of the design is validated through MATLAB simulations, confirming smooth and stable wingspan control. For mechanical evaluation, deformation, and stress distribution analyses are conducted using ANSYS finite element analysis. The results demonstrate that the mechanism exhibits stable operation and structural durability under maximum loading conditions. Furthermore, an optimization of the structurally weak regions significantly reduces stress concentrations and enhances the load-bearing capacity of the system.