基于Lamb波和典型相关分析的复合材料结构损伤监测

Damage Monitoring of Composite Structures Based on Lamb Wave and Canonical Correlation Analysis

为了监测复合材料尾翼结构在受载条件下的健康状况变化,该文提出了一种基于超声导波和典型相关分析的结构健康监测方法。首先,将代表结构健康状况的基准信号和损伤信号之间的相关系数定义为损伤指数,通过典型结构试验确定损伤指数阈值。然后,在载荷施加的过程中以损伤指数超过该阈值的信号路径数量作为衡量结构健康状态的结构损伤指标,通过监测该指标的变化掌握结构的健康状况。在全尺寸复合材料尾翼损伤演化监测实验中,验证了该方法对于复合材料飞行器结构损伤扩展监测的有效性。研究结果表明,结构损伤指标的变化可以反应结构健康状况的变化趋势,在役结构健康监测方法可以实现对复合材料尾翼结构的实时监测。

In order to monitor the health condition of composite tail structure under load condition,a structural health monitoring（SHM）method based on the ultrasonic guided waves and canonical correlation analysis was proposed in this paper.First,the correlation coefficient between the reference signal representing the structural health condition and the damage signal is defined as the damage index.The threshold of damage index was determined based on a typical structure loading test.Then,the numbers of paths which damage indices exceed the threshold were chosen as the indicator of structure health status.Finally,the effectiveness of the proposed method for monitoring the structural damage expansion of the composite aircraft is verified by the SHM experiment of a full-scale composite horizontal tail.The experimental results show that the change of structural damage index can reflect the trend of structural health status,and the in-service structural health monitoring method can realize real-time monitoring of composite structure.