Design and Aerodynamic Analysis of Leading Edge for Morphing Wing

The incorporation of a drooping leading-edge wing optimizes the aerodynamic efficiency of aircraft under different flight conditions. The optimal positioning of leading-edge stringers for the cruise condition was determined in this study through the optimization of equivalent stress in fluid–structure coupling. This optimization significantly improved the load-carrying capacity of the leading edge during flight. The optimization significantly enhanced the load-carrying capacity of the leading edge during flight. The suitability of four configurations of the Watt-I six-bar mechanism in the skeletal structure of leading-edge droop (LD) was further evaluated. The establishment of a unified kinematic equation was followed by the utilization of genetic algorithms to optimize the mechanism parameters. The simulation results from the rigid–flexible coupling analysis demonstrate that the dual-drive-point mechanism exhibits minimal deviation in the airfoil curve. The aerodynamic analyses of various drogue angles also demonstrated a significant improvement in the aerodynamic performance of the drooping leading-edge airfoil compared to the standard airfoil. The variable camber leading-edge mechanism underwent numerical simulation validation before its fabrication as an experimental prototype, followed by the completion of deformation drive and static stiffness tests.