超临界机翼多目标气动优化设计的策略与方法

Strategies and methods for multi-objective aerodynamic optimization design for supercritical wings

超临界机翼的气动设计十分复杂,往往需要借助于有效的优化手段。然而,优化方法本身往往无法直接表达真实完整的设计意图,因此需要将工程需求和约束转换为优化方法所能处理的数学形式。本文首先探讨了梯度优化方法和进化类优化方法在气动优化中的表现。之后简要总结了前人在飞机气动设计中提出的准则和要求,并基于压力分布形态定义了超临界机翼气动设计的关键特征及定量要求,探究其在超临界机翼气动优化设计中的应用效果。研究结果表明,在多目标优化中引入面向压力分布形态特征的目标和约束,能有效引导优化体现工程设计思想,进而提高优化效率。

Optimization methods are often applied in aerodynamic design of modern civil aircraft supercritical wings.However,optimization algorithms cannot directly describe the industrial requirements,therefore,corresponding mathematical descriptions must be developed to tackle the problem.In the present paper,gradient algorithms and stochastic algorithms are compared in a supercritical wing optimization.Then,several requirements of aircraft aerodynamic design are summarized and mathematically described,and these criteria are applied to a multi-objective stochastic optimization method as objectives and constraints.The method is applied to a civil aircraft wing aerodynamic optimization,and the results show that better efficiency and result can be obtained by using pressure distribution guided objectives and constraints.