基于任意空间属性FFD技术的融合式翼稍小翼稳健型气动优化设计

 以非均匀有理B样条基函数为空间控制体属性,建立了任意空间形状自由变形(FFD)技术参数化方法。所建立的气动外形参数化系统通过FFD控制体的分布以及控制顶点的合理选取,能够对任意复杂外形进行参数化设计。首先采用FFD控制体对某型客机翼稍小翼进行空间属性构建;然后结合基于Delaunay图映射技术建立了结构对接网格变形模式,采用分群粒子群算法以及误差反向传播训练算法(BP)神经网络进行稳健型气动优化系统的构建;最后对某型客机融合式翼稍小翼的后掠角、倾斜角和高度等参数进行稳健型气动优化设计,分析对比了优化前后翼梢小翼表面压力云图、截面压力分布及载荷分布。优化设计结果表明:设计后的翼稍小翼的升阻比与阻力发散特性明显提高。

Study of Robust Winglet Design Based on Arbitrary Space Shape FFD Technique

An arbitrary space shape free-form deformation (FFD) technique is first established in this paper based on the non-uniform rational B-splines basis function, and any complex configuration can be parameterized through choosing an FFD shape and lattice reasonably. First an airliner wingtip is parameterized using the FFD technique. Then the multi-block structure grid deformation technique is established by the Delaunay graph mapping method. An aerodynamic optimization design system is established by combining the FFD technique, the grouping particle swarm optimization arithmetic with the back propagation (BP) neural network approximation model. Finally, it processes the robust aerodynamic optimization design of the winglet by taking the swept angle, deflection angle and height of the airliner as design variables. The surface pressure contour, pressure distribution of the wing section and load distribution of the initial and optimized winglet are analyzed. The results show that the optimized winglet has significantly better aerodynamic characteristics.