飞行器非线性振动试验与模型修正研究进展

王兴

doi:10.6052/1000-0992-24-011

飞行器非线性振动试验与模型修正研究进展

doi: 10.6052/1000-0992-24-011 cstr: 32046.14.1000-0992-24-011

王兴^,

中山大学深圳航空航天学院, 广东深圳 518107
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

基金项目: 作者感谢国家自然科学基金(12072378, 52005522)的资助, 感谢深圳市科技计划资助项目(RCYX20210706092137055, ZDSYS20210623091808026和No. 202206193000001, 20220815155101002)对本文试验研究所需软硬件的支持. 此外, 作者由衷地感谢多名匿名审稿人对本文的修改意见和建议.

详细信息

作者简介:
王兴, 中山大学“百人计划”副教授, 博士生导师. 主要研究兴趣为飞行器结构动力学、航天器振动试验技术与模型修正方法、航天结构在轨装配等. 目前为中国振动工程学会模态分析与试验专委会委员. 近五年, 主持国家自然科学基金青年项目1项、面上项目1项, 主持航天领域纵向/横向项目10余项, 在《AIAA Journal》《Mechanical Systems and Signal Processing》《Journal of Sound and Vibration》《振动工程学报》等学术期刊和国内外学术会议上发表论文20余篇, 担任《AIAA Journal》《Mechanical Systems and Signal Processing》《Journal of Sound and Vibration》《振动工程学报》等多个期刊的审稿人

通讯作者:
wangxing5@mail.sysu.edu.cn

中图分类号: V416.2
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出版历程
- 收稿日期: 2024-04-07
- 录用日期: 2024-08-19
- 网络出版日期: 2024-08-27

Advances in vibration testing and model updating for nonlinear aerospace structures

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

More Information

Corresponding author: wangxing5@mail.sysu.edu.cn

摘要

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.
- 飞行器结构 /
- 非线性振动 /
- 振动试验 /
- 模型修正
Abstract: 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.
- aerospace structure /
- nonlinear vibration /
- vibration testing /
- model updating

HTML全文

图 1 欧洲机械臂地面振动试验(Göge et al. 2005a). (a)试验场景, (b)辨识得到模态刚度的非线性曲线

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图 2 航天器桁架关节的非线性振动试验(Li et al. 2022a, 2023). (a)试验场景, (b)辨识得到的力矩-转角曲线

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图 3 航空发动机部段连接结构的振动试验(Boswald & Link 2004). (a)试验场景, (b)单个螺栓结构的非线性模型

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图 4 美国F-16翼尖挂架的地面振动试验 (Noël et al. 2013). (a)试验场景, (b) 频响函数测量结果

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图 5 欧洲SmallSat地面振动试验(Noël & Kerschen 2017). (a)扫频试验场景, (b) 试验测得的复杂非线性振动响应

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图 6 本文重点讨论的飞行器非线性动力学以及成熟的飞行器结构动力学和非线性振动的研究范畴

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图 7 欧洲SmallSat卫星飞轮支架振动试验(Noël & Kerschen 2017). (a)飞轮支架局部图, (b)正扫和反扫试验中测得的支架位置相对位移响应

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图 8 航空发动机风扇叶片的纯模态试验(Wang et al. 2022). (a)振动试验场景, (b)全场加速度与激振力的相位差图

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图 9 基于数字图像相关的连接结构非线性振动试验(Chen et al. 2022). (a)相机与被测结构, (b)多点响应测量结果

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图 10 基于频响函数数据的局部非线性结构有限元模型修正的一般流程(Wang et al. 2018b)

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图 11 利用等效动刚度图法辨识卫星金属橡胶阻尼器参数(Wang & Zheng 2016). (a)试验场景, (b)等效动刚度实部图

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图 12 本文提炼归纳出的利用基础线性模态的分布式非线性结构有限元模型修正流程

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图 13 基于骨架线匹配的曲梁结构单模态辨识 (Van Damme et al. 2020). (a)曲梁结构, (b)骨架线迭代过程

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图 14 浸入水中圆杆的非线性振动试验与耦合模态辨识 (Le Guisquet & Amabili 2021b). (a)试验场景. (b)驱动模态(driven mode)频响函数对比, (c)伴随模态(companion mode)频响函数对比

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