不确定环境因素影响下PZT传感器疲劳裂纹检测

Q4 Engineering Fatigue of Aircraft Structures Pub Date : 2016-06-01 DOI:10.1515/fas-2016-0010
M. Dziendzikowski, S. Klimaszewski, K. Dragan
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引用次数: 2

摘要

摘要本文提出了一种利用稀疏PZT压电换能器网络产生的导弹性波对疲劳裂纹扩展监测进行定性评估的技术。两个损伤指数(DIs)与给定传感器接收的总能量相关,用于检测疲劳裂纹并监测其扩展。所提出的指标带有边际信号信息含量,以降低它们相对于其他可能扭曲接收信号的不希望的不可控因素的灵敏度。这样做的原因是为了限制误叫率,这除了对系统的损伤检测能力外,在实际应用中也起着至关重要的作用。然而,即使是这种简化的损伤指标也可能在长期内发生变化,从而导致误分类问题。考虑到单一的感知路径,很难区分DIs的最终变化是由损伤引起的还是由这些DIs的退相干引起的。因此,基于对每条感知路径上获得的DIs分别固定的阈值水平的评估方法最终会导致错误调用。另一种方法是比较所有传感路径的di变化。发展损伤只对其附近的传感路径造成信号失真。为了降低误分类风险,提出了一种补偿这种DIs漂移的方法。该方法的主要特点和损伤检测能力将通过对飞机面板进行实验室疲劳测试来验证。该方法已在某直升机尾吊臂的疲劳试验中得到验证。
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Fatigue Cracks Detection using PZT Transducers under the Influence of Uncertain Environmental Factors
Abstract This paper presents technique for qualitative assessment of fatigue crack growth monitoring, utilizing guided elastic waves generated by the sparse PZT piezoelectric transducers network in the pitch – catch configuration. Two Damage Indices (DIs) correlated with the total energy received by a given sensor are used to detect fatigue cracks and monitor their growth. The indices proposed carry marginal signal information content in order to decrease their sensitivity with respect to other undesired non-controllable factors which may distort the received signal. The reason for that is to limit the false calls ratio which besides the damage detection capability of a system, plays a crucial role in applications. However, even such simplified damage indices can alter over a long term, leading to the misclassification problem. Considering a single sensing path, it is very difficult to distinguish whether the resultant change of DIs is caused by a damage or due to decoherence of these DIs. Therefore, assessment approaches based on threshold levels fixed separately for DIs obtained on each of the sensing paths, would eventually lead to a false call. An alternative approach is to compare changes of DIs for all sensing paths. Developing damage distorts the signal only for the sensing paths in its proximity. In order to decrease the misclassification risk, a method of compensating such DIs drift is proposed. The main features and damage detection capabilities of this method will be demonstrated by conducting a laboratory fatigue test of an aircraft panel. The proposed approach has been verified on a real structure during fatigue test of a helicopter tail boom.
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来源期刊
Fatigue of Aircraft Structures
Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality
CiteScore
0.40
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期刊介绍: The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.
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