A flexible wing structure design method based on aerodynamic optimization results

Abstract

The present application belongs to the field of aircraft structure design, and in particular, relates to a method for designing a flexible wing structure based on aerodynamic optimization results. The method includes: step one, obtaining the initial geometric parameters of a flapping-wing aircraft, and constructing a flapping-wing three-dimensional model based on the initial geometric parameters; step two, constructing a flapping-wing motion model of the flapping-wing three-dimensional model; step three, performing finite element aerodynamic calculations based on the flapping-wing three-dimensional model and the flapping-wing motion model to obtain the torsion angle corresponding to the optimal aerodynamic state; step four, constructing a flapping-wing topology optimization model based on the torsion angle, and performing topology optimization on the flapping-wing topology optimization model; step five, designing a flapping-wing structure based on the topology optimization results. The present application gives full play to the advantages of computational fluid dynamics and computational structural mechanics simulation, effectively reduces the cost caused by a large amount of repetitive experimental work in flapping-wing design, and provides a more effective guidance means for the design of flapping wings with efficient aerodynamic performance.