基于Sobol法的整体翼梁损伤容限设计参数灵敏度分析  

Analysis of Parameter Sensitivity on Damage Tolerance Design of Overall Beam Based on Sobol Method

作　　者：尹俊杰[1] 常飞[1] 李曙林[1] 杨哲[1] 石晓鹏[1] 

机构地区：[1]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《空军工程大学学报（自然科学版）》2013年第6期9-12,共4页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(51201182)

摘　　要：针对飞机结构设计中设计变量灵敏度的问题,提出了基于Sobol法的全局灵敏度分析策略。以飞机整体翼梁结构损伤容限设计为例,设计变量为翼梁结构截面参数,应用支持向量机理论分别构造以截面参数为输入、应力强度因子和结构重量为响应的代理模型,结合Sobol法计算输入对响应的灵敏度大小,并对计算结果进行分析。分析结果表明:在对整体结构进行损伤容限优化设计时,可以将其设计变量由6个变为4个,灵敏度较小的2个设计变量可以设为一个定值。Aimed at the problem of the sensitivity of design variables in the design of aircraft structures,this paper puts forward a global sensitivity analyzing strategy based on Sobol＇s method and support vector ma-chine method,and analyzes the parameter sensitivity with Sobol method by taking damage tolerance design to the aircraft overall beam as example,the overall beam cross-section parameters as design variables,and respectively constructing the replacement models of stress intensity factor and structure weight with the application of support vector machine theory.The result shows that the conclusion obtained can provide a guidance for selecting the design parameters and modifying the design variables in the optimization design of the structure.

关 键 词：Sobol法 整体翼梁 损伤容限 灵敏度 支持向量机 

分 类 号：V252[一般工业技术—材料科学与工程]