一种计及气动和隐身约束的结构两级优化设计方法  

The Research of Structural Optimization with the Constraints of Aerodynamics and Radar Cross Section(RCS) of Aircraft

作　　者：苟仲秋[1] 宋笔锋[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《系统工程理论与实践》2006年第3期135-140,共6页Systems Engineering-Theory & Practice

基　　金：863-705(2003AA754010)

摘　　要：针对计及气动和隐身约束的结构优化中所面临的计算困难,以减少结构、气动和隐身重分析次数,降低计算量为核心,基于并行子空间思路提出了一种计及气动和隐身约束的结构两级优化设计框架.该框架将设计变量区分为全局变量和局部变量,系统级优化全局变量,而将局部变量放在学科级优化.仅将全局变量作为系统级优化响应面的输入变量,大大降低了构造响应面近似模型的代价.以计及气动和隐身约束的无人机机翼结构优化为例说明方法的有效性.The development of structural optimization calls for considering the influence of aerodynamics and radar cross section （RCS） of aircraft. So models and software＇s flow charts for structural optimization based on Concurrent Subspace Optimization（ CSSO）, with the constraints of aerodynamics and radar cross section （RCS） are presented and studied. The response surface technique is adopted to simulate the single disciplinary model, including structure disciplinary, aerodynamics disciplinary and radar detection and the dimension of input variables for response surface is decreased by distinguishing system variables which explicitly impact more than one subsystem from local variables which explicitly impact only one subsystem. The new constructing response surface method is integrated into a twolevel optimization frame, to solve complex engineering systems, in which system level optimizer optimizes system design variables and subsystem level optimizers optimize local design variables. These measures will reduce the times of single disciplinary re-analysis greatly. The effectiveness of the models, software flow charts and techniques for improving optimization process in this paper is shown by an example, which is about design optimization of a wing structure in ＂global hawk aircraft＂.

关 键 词：多学科设计优化 并行子空间优化 结构优化 响应面 

分 类 号：V214.19[航空宇航科学与技术—航空宇航推进理论与工程]