高速组合体布局飞行器外形快速优化方法研究

Research on Shape Optimization of Wing-body Hypersonic Vehicle

针对概念设计阶段高速组合体布局飞行器外形快速优化问题,建立了基于灵敏度分析和工程算法的外形快速优化流程。建立了组合布局飞行器参数化外形模型,采用回归方法分析各外形参数对升阻比、升力载荷系数的影响程度和规律,获取关键外形参数及其灵敏度排序。考虑压心、装填能力、驻点热流等约束条件对升阻比和升力载荷系数进行多目标优化。最后,用CFD方法验证了优化的有效性,可为高速组合体布局优化设计提供一定的参考。

Wing-body hypersonic vehicle has a large number of geometry parameters and it costs too much time to optimize all the parameters especially in concept design phase. To overcome this difficulty,a wing-body hypersonic vehicle quick shape optimization routine is proposed. A parametric body-wing aircraft shape is prepared for the routine while higher lift-drag ratio and lower weight-lift coefficient requirements are put forward. By means of orthogonal experiment and regression sensitivity analysis,the influence of the geometry parameters on lift-drag ratio and weight-lift coefficient is obtained and key geometry parameters on concerned performances are extracted using regression sensitivity analysis with engineering based aerodynamic tool. Then,a multi-object genetic algorithm is applied to optimize these key geometry parameters. With several vital constrains,high lift-drag and low weight-lift coefficient shape is designed and optimized in a short time. At last,the optimization was proved a success and verified its effectiveness by CFD calculations,which provides reference value to wing-body hypersonic vehicle shape design.