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基于扩散兰姆波场幅度特性的多铆接带式连接铝合金飞机面板疲劳裂纹检测

Fatigue-Crack Detection in a Multi-Riveted Strap-Joint Aluminium Aircraft Panel Using Amplitude Characteristics of Diffuse Lamb Wave Field.

作者信息

Stolze Frank H G, Worden Keith, Manson Graeme, Staszewski Wieslaw J

机构信息

Department of Mechanical Engineering, Sheffield University, Mappin St., Sheffield S1 3JD, UK.

Department of Robotics and Mechatronics, AGH University of Science and Technology, Al. Mickiewicza 30, 30-059 Krakow, Poland.

出版信息

Materials (Basel). 2023 Feb 15;16(4):1619. doi: 10.3390/ma16041619.

DOI:10.3390/ma16041619
PMID:36837249
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC9960847/
Abstract

Structural health monitoring of riveted aircraft panels is a real challenge for maintenance engineers. Here, a diffused Lamb wave field is used for fatigue-crack detection in a multi-riveted strap-joint aircraft panel. The panel is instrumented with a network of low-profile surface-bonded piezoceramic transducers. Various amplitude characteristics of Lamb waves are used to extract information on fatigue damage. A statistical outlier analysis based on these characteristics is also performed to detect damage. The experimental work is supported by simplified modelling of wave scattering from crack tips to explain complex response features. The Local Interaction Simulation Approach (LISA) is used for this modelling task. The results demonstrate the potential and limitations of the method for reliable fatigue-crack detection in complex aircraft components.

摘要

铆接飞机面板的结构健康监测对维修工程师来说是一项真正的挑战。在此，扩散兰姆波场被用于检测多铆接带接头飞机面板中的疲劳裂纹。该面板配备了一个由低剖面表面粘贴式压电陶瓷换能器组成的网络。利用兰姆波的各种幅度特性来提取有关疲劳损伤的信息。还基于这些特性进行统计离群值分析以检测损伤。通过对裂纹尖端波散射的简化建模来支持实验工作，以解释复杂的响应特征。局部相互作用模拟方法（LISA）用于此建模任务。结果证明了该方法在复杂飞机部件中进行可靠疲劳裂纹检测的潜力和局限性。

https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3ff6/9960847/b6ba472a514a/materials-16-01619-g013.jpg
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