飞行器非线性振动试验与模型修正研究进展  

Advances in vibration testing and model updating for nonlinear aerospace structures

作　　者：王兴 WANG Xing(School of Aeronautics and Astronautics,Shenzhen campus of Sun Yat-sen University,Shenzhen 518107,China;Shenzhen Key Laboratory of Intelligent Microsatellite Constellation,Shenzhen 518107,China)

机构地区：[1]中山大学·深圳航空航天学院,广东深圳518107 [2]深圳市智能微小卫星星座技术与应用重点实验室,广东深圳518107

出　　处：《力学进展》2024年第4期669-699,共31页Advances in Mechanics

基　　金：国家自然科学基金资助项目(12072378,52005522);深圳市科技计划资助项目(RCYX20210706092137055,ZDSYS20210623091808026和No.202206193000001,20220815155101002)。

摘　　要：面向质量更轻、承载能力更强,柔性变形更大的先进飞行器,首先对其地面振动试验及使役过程中观察到的非线性振动现象进行梳理,归纳出两类典型的非线性结构模型−局部非线性结构和分布式非线性结构,对其基本概念进行了阐述.随后,从频响函数试验、纯模态试验、自由衰减试验等技术路径总结了非线性振动试验方法的研究进展.最后,根据两类非线性结构动力学方程的特点分别归纳了与之相适应的有限元模型修正流程及关键辨识方法,展望了发展趋势并给出研究建议.有望为未来飞行器非线性振动试验与精准建模提供有益参考.For lighter,stronger and more flexible aerospace structures,the nonlinear phenomena observed during ground vibration tests and in-service operations are first sorted out.Two types of typical nonlinear structures-localised and distributed nonlinear structures−are then highlighted,the basic concepts of which are explained.Secondly,the vibration testing techniques developed for these nonlinear structures are compared,and the research progress is summarised from the perspective of frequency response test,pure modal test,free decay test and others.Finally,model updating procedures of the two types of nonlinear structures are analysed,with identification methods discussed.Future perspectives are pointed out and research suggestions are also highlighted.It is expected to provide a useful reference for the future development of vibration testing techniques and accurate modelling methods of nonlinear aerospace structures.

关 键 词：飞行器结构 非线性振动 振动试验 模型修正 

分 类 号：V416.2[航空宇航科学与技术—航空宇航推进理论与工程]