CAJ | 학술논문

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。
침대비궤결구설계중설계변량령민도적문제，제출료기우 Sobol 법적전국령민도분석책략。이비궤정체익량결구손상용한설계위례，설계변량위익량결구절면삼수，응용지지향량궤이론분별구조이절면삼수위수입、응력강도인자화결구중량위향응적대리모형，결합 Sobol 법계산수입대향응적령민도대소，병대계산결과진행분석。분석결과표명：재대정체결구진행손상용한우화설계시，가이장기설계변량유6개변위4개，령민도교소적2개설계변량가이설위일개정치。
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.