Probability of detection of cracks in metal structures using guided wave based on a signal response analysis model

被引：0
作者：
Wang L. [1 ,2 ]
Yang Y. [2 ]
Liu G. [2 ]
Wang X. [2 ]
Li J. [2 ]
Ren Y. [2 ]
机构：
[1] State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] National Laboratory of Strength and Structural Integrity, Aircraft Strength Research Institute of China, Xi'an
来源：
Zhendong yu Chongji/Journal of Vibration and Shock | 2024年 / 43卷 / 02期
关键词：
fatigue crack; guided wave; metal; probability of detection (POD); structural health monitoring;
D O I：
10.13465/j.cnki.jvs.2024.02.004
中图分类号：
学科分类号：
摘要：
In order to realize the condition-based maintenance and formulate the inspection and maintenance scheme during the service, the probability of detection (POD) for guided wave damage monitoring technology must be clarified, as a new nondestructive testing method. A novel POD computation method was presented for guided wave detection based on a signal response analysis model. First, the statistical computation model of POD was obtained by establishing the mapping relationship between the damage features of online response guided waves and fatigue cracks. Then, by analyzing the quantitative effect of uncertainties of fitting parameters on the statistical computation model, POD computation models under different confident levels were obtained. The proposed method was validated by fatigue cracks monitoring experiments on metal center-hole and lap specimens. The results show that damage features, fitting functions and transducers monitoring schemes all have effects on the POD, and the detectable crack length under 95% confidence level and 90% detection probability for center-hole and lap metal structures are about 2. 6 mm and 9. 5 mm respectively. © 2024 Chinese Vibration Engineering Society. All rights reserved.
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页码：32 / 41and186
相关论文
共 24 条
  • [1] CUI Degang, BAO Rui, ZHANG Rui, Et al., Development of aircraft structural fatigue and structural integrity : review[J], Acta Aeronautica et Astronautica Sinica, 42, 5, (2021)
  • [2] SUN Xiasheng, SU Shaopu, SUN Hanbin, Et al., Current status and prospect of overseas research on aeronautical fatigue, Acta Aeronautica et Astronautica Sinica, 42, 5, (2021)
  • [3] WANG Yuanda, LIANG Yongsheng, WANG Hongwei, Design of durability and damage tolerance for aircraft structure, Aircraft Design, 29, 1, pp. 37-43, (2009)
  • [4] SUN Xiasheng, XIAO Yingchun, Opportunity and challenges of aircraft structural health monitoring, Acta Aeronautica et Astronautica Sinica, 35, 12, pp. 3199-3212, (2014)
  • [5] Non-destructive evaluation system reliability assessment : MIL-HDBK-1823, (1999)
  • [6] BERGER U., Onboard-SHM for life time prediction and damage detection on aircraft structure using fibre optical sensor and Lamb wave technology [C], 6th European Workshop on Structural Health Monitoring-Tu. 2. A. 1, (2012)
  • [7] DERRISO M M, MCCURRY C D, KABBAN M S., A novel approach for implementing structural health monitoring systems for aerospace structures, Structural Health Monitoring (SHM) in Aerospace Structures, 2, pp. 33-56, (2016)
  • [8] BOLLER C., Next generation structural health monitoring and its integration into aircraft design, International Journal of Systems Science, 31, 11, pp. 1333-1349, (2000)
  • [9] KALE A A, HAFTKA R T, SANKAR B V., Tradeoff of structural weight and inspection cost in reliability based optimization using multiple inspection types [C], 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, (2004)
  • [10] NAN Y, ALIABADI M H., Hierarchical approach for uncertainty quantification and reliability assessment of guided wave based structural health monitoring, Structural Health Monitoring, 20, 5, pp. 2274-2299, (2020)
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