Composite aircraft debonding visualization by laser ultrasonic scanning excitation and integrated piezoelectric sensing
Composite aircraft debonding visualization by laser ultrasonic scanning excitation and integrated piezoelectric sensing
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DOI：
10.1002/stc.1504
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发表时间：
2012-11-01
影响因子：
5.4
通讯作者：
Park, Gyuhae
中科院分区：
文献类型：
--
作者：
Chia, Chen Ciang;Jeong, Hyo-Mi;Park, Gyuhae
利用基于激光的超声传播成像系统对两个碳纤维增强塑料机翼进行了检测，以实现脱粘模式制造缺陷和损伤的可视化。提出了复合材料脱粘检测机理的假设，并通过对复合材料翼面结构粘合线的检测结果进行了验证。检查表明，从成像结果可以直观地看到和/或测量粘结不良缺陷、人工纵梁尖端脱粘和真正的剥离的位置、形状和大小。在空间分辨率和损伤检测能力方面，该成像系统的性能优于手动超声C扫描。检查的另一个发现是在两个铆接位置之间发生了皮肤屈曲。最重要的是，结构元素或特征的存在，如横梁、纵梁、肋骨、凸耳、检查窗，甚至嵌入的PZT元素，都不会对检查产生不利影响。版权所有(C)2012 John Wiley&Sons，Ltd.
Two aircraft wings made of carbon fiber-reinforced plastic material were inspected using the laser-based ultrasonic propagation imaging system for the visualization of manufacturing defect and damages of debonding mode. Hypotheses of the detection mechanism of composite debonding were presented and validated through the inspection results for the bonding lines of the composite wing structures. The inspection showed that the location, shape, and size of the poor bonding defect, artificial stringer tip debonding, and real skinspar debonding can be visualized and/or measured from the imaging results. The performance of the imaging system was found better than that of a manual ultrasonic C-scan in terms of spatial resolution and damage detectability. Another finding from the inspection was the occurrence of skin buckling between two riveted locations. Most importantly, the presence of structural elements or features such as spars, stringers, ribs, lugs, inspection windows, and even embedded PZT elements did not adversely affect the inspection. Copyright (C) 2012 John Wiley & Sons, Ltd.