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.
Design and Aerodynamic Analysis of Leading Edge for Morphing Wing
Journal of Aircraft ; 1-12
01.01.2025
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
MORPHING LEADING-EDGE TUBERCLES ON CESSNA 172 WING
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