A model-updating approach based on the component mode synthesis method and perturbation analysis

被引:8
|
作者
Wang, T. [3 ,4 ]
He, H. [1 ,2 ]
Yan, W. [1 ]
Chen, G. P. [1 ,2 ]
机构
[1] State Key Lab Mech & Control Mech Struct, Nanjing 210016, Jiangsu, Peoples R China
[2] Nanjing Univ Aeronaut & Astronaut, Inst Vibrat Engn Res, Nanjing 210016, Jiangsu, Peoples R China
[3] Nanjing Univ Aeronaut & Astronaut, Res Inst Pilotless Aircraft, Nanjing 210016, Jiangsu, Peoples R China
[4] Nanjing Univ Aeronaut & Astronaut, Key Lab Small & Medium Sized Unmanned Aerial Vehi, Minist Ind & Informat Technol, Nanjing 210016, Jiangsu, Peoples R China
基金
中国国家自然科学基金;
关键词
Component mode synthesis; Model updating; Perturbation method; Model reduction; FINITE-ELEMENT MODEL; DYNAMIC-ANALYSIS; SYSTEMS; VIBRATION; OPTIMIZATION; PROPAGATION; REDUCTION;
D O I
10.1016/j.jsv.2018.07.026
中图分类号
O42 [声学];
学科分类号
070206 ; 082403 ;
摘要
A model updating approach based on an improved free-interface component mode synthesis method is proposed. First, the equivalent higher-order matrix of the system is developed using a set of linearly independent vectors to capture the effects of the neglected higher-order modes. Second, the perturbation method is applied to derive the change for both eigenvalues and eigenvectors of each component while implementing a modification to the updated finite element model. The perturbation for both the eigenvalues and eigenvectors of each component are used to formulate the synthesis equations containing the perturbation expression. Next, the model-updating process is conducted using the synthesis model for which the degrees of freedom have been greatly reduced. The reduction in the total degree of freedom speeds up the solution process for the modelupdating problem. Finally, the computational efficiency and accuracy of the presented method is demonstrated using a wing structure and by modal testing of a bolted plate. (C) 2018 Elsevier Ltd. All rights reserved.
引用
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页码:349 / 365
页数:17
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