小型无人机翼型优化设计

Optimization Design for Mini-UAV Airfoil

摘要:

采用类别形状函数变换(CST)方法对翼型参数化描述；利用 Fluent软件,进行翼型升力系数和阻力系数的气动计算；以升阻比最大为优化目标,通过拉丁超立方设计生成样本点,建立了径向基神经网络(RBF)代理模型；使用粒子群优化算法(PSO),在 Isight平台上,实现对 Clark Y翼型优化的整个过程。优化翼型升阻比比原始翼型提高了约 10%,表明此种方法是可行的,可用于小型无人机设计的工程中。

Abstract:

The CST universal parametric geometry representation method was used to describe the parametric air. foil,and lift coefficient and drag coefficient of the designed airfoil was directly calculated by Fluent. The maxi. mum lift-drag ratio as the goal was achieved by employing PSO algorithm. The latin hypercube method was em. ployed to construct the initial sample points used in a RBF surrogate model. The software of Isight was used to realize the design processes. The maximum lift-drag ratio was significantly improved by about 10%. The result showed that this approach was feasible and could be used as reference for Mini-UAV design in engineering.