Damage growth monitoring for a bonding layer of the aircraft bonding structure
Damage growth monitoring for a bonding layer of the aircraft bonding structure
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飞机粘接结构粘接层的损伤增长监测
DOI：
10.1117/12.658555
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发表时间：
2006
期刊：
影响因子：
--
通讯作者：
T. Sakurai
中科院分区：
文献类型：
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作者：
T. Ogisu;M. Shimanuki;H. Yoneda;Y. Okabe;J. Kuwahara;N. Takeda;T. Sakurai
本研究是关于为开发应用于下一代飞机的先进复合材料粘接结构的损伤监测系统而进行的试验的一些结果。在过去的研究中，我们成功地接收了数百kHz的弹性波（兰姆波）发射的PZT通过使用光纤传感器粘贴或嵌入在一个标本。此外，通过使用FBG光纤传感器嵌入在CFRP试样或具有蒙皮/桁条粘结结构的结构元件试样的粘结界面中或粘结到试样的表面，测试结果已被证实，并且事实被验证，关于复合材料的结构，根据损伤增长的弹性波的变化可以以高精度接收。作者还建议可以通过计算弹性波来检测复合材料内部产生的损伤。在这项研究中，我们制造了一个结构元件试样，其中一个小直径的光纤传感器嵌入在粘接界面，这是模拟实际复合材料结构的蒙皮/纵梁粘接结构。我们还自行研制了一套可检测1 MHz弹性波的系统，并根据相应的试件进行了优化。在结构试件的临界区域设置人工损伤作为损伤起始点。实验结果表明，该监测系统可以检测到20 mm ~ 2损伤的发生和发展过程中伴随的弹性波变化。
This study is about some of the results of the test performed for the purpose of developing the damage monitoring system with the advanced composite bonding structure applied to a next generation aircraft. Through the past researches, we succeeded in receiving hundreds of kHz of elastic waves (lamb waves) launched from PZT byusing an optical fiber sensor bonded to or embedded in a specimen. Furthermore, by using an FBG optical fiber sensor embedded in the bonding interface of a CFRP coupon specimen or a structure element specimen with skin/stringer bonded structure or bonded to the surface of the specimen, the test results have been proven and the fact is verified that regarding the structure of composites, variations of elastic waves according to damage growth can be received with high accuracy. The authors also suggest it is possible to detect a damage, which is generated inside composites by calculating the elastic waves. For this study, we manufactured a structural element specimen where a small-diameter optical fiber sensor is embedded in the bonding interface, which is simulated a skin/stringer bonding structure of actual composite structures. We also developed the system, which is detecting elastic (lamb) wave up to 1MHz on our own and optimized it according to the corresponding specimen. Furthermore, an artificial damage is installed to critical area of the structural element specimen as a damage origin point. It is verified that our monitoring system can detect the variations of elastic waves accompanying the damage of 20mm2 occurring and growing from the artificial damage by the applied cyclic load.