Aerodynamic Performance Optimization of Flapping Wing Aircraft Based on Kriging Surrogate Model

Ornithopters have an extremely efficient way of flying, with outstanding advantages over other vehicles, and are therefore the direction of future vehicle development. Aerodynamic characteristics correlation research plays a vital role in any type of vehicle, so a flapping wing vehicle aerodynamic performance optimization method aiming at the coupling of lift and pitch is proposed in this paper. First, the Hicks Henne method is used to parametrize the airfoil to facilitate the generation of new airfoils during the optimization iteration. By establishing the computational domain division of the C- type structural grid, the aerodynamic parameters are obtained by numerical calculation method. Then, the experiment design is carried out by Latin Hypercube sampling method, and the sample points are selected in the design space. The Dynamic Kriging Proxy Model, which can be updated repeatedly, is established. When the dynamic surrogate model meets the termination iteration conditions, the surrogate model has converged and the accuracy meets the requirements. Finally, combining the advantages of genetic algorithm and particle swarm optimization algorithm, the genetic particle swarm optimization algorithm is developed, and the agent model is used as fitness function to optimize the parameters of the flapping wing.