适合概念设计的制导炮弹气动外形优化方法

An aerodynamic shape optimization method for projectile conceptual design

为了构建能够满足复杂外形制导炮弹气动外形优化设计的方法,给出了基于解析函数和UG NX软件二次开发系统的制导炮弹参数化建模基本原理和具体实施方法,并使用遗传算法为优化算法,结合高精度面元法的气动特性预估程序,完成概念设计阶段的制导炮弹气动外形优化的快速优化设计。以翼-身-尾布局形式的制导炮弹气动外形优化设计为算例,对该优化方法进行了考核验证。算例验证结果表明:气动外形优化方法在使用较少的参数条件下,能够构建具有复杂形状的弹身和翼型的制导炮弹气动布局,并能在构建几何外形的同时快速生成不同拓扑结构外形的面元网格,结合遗传算法能够在制导炮弹概念设计阶段快速得到较优的外形布局,具有很好的工程应用前景。

In order to satisfy the aerodynamic shape optimization design of complex shape guided projectile,the basic principle and specific implementation method of parametric modeling of guided projectile are given based on analytic function and the secondary development system of UG NX software.Genetic algorithms are used as optimization algorithms.Combined with the aerodynamic characteristics prediction program using high precision panel method,the rapid design of aerodynamic shape optimization of guided projectile in conceptual design phase is completed.Taking the aerodynamic shape optimization design of the guided projectile in the form of wing-tail-layout as an example,the optimization method is verified.The results show that the aerodynamic shape optimization method using fewer parameters can construct the aerodynamic layout of guided projectile with complex body and airfoil.Surface element mesh with different topological structures can be quickly generated while constructing geometric shapes.Combined with genetic algorithm,a better shape layout can be quickly obtained in the conceptual design phase of guided projectile.It has a good prospect for engineering application.