复合材料直升机旋翼叶片和无人机翼段诱导缺陷的无损检测与量化

D. Findeis, J. Gryzagoridis, V. Musonda
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引用次数: 7

摘要

采用数字剪切成像和红外热成像(IRT)技术对复合材料性质的飞机结构样品进行无损检测。介绍了技术的背景信息,并指出,在文献中审查的许多检查工作都集中在缺陷的定性评估上,而不是定量的。然而,如果必须建立被检查部件是否适合服务的阈值拒绝标准,则需要对缺陷进行量化。本文对直升机主旋翼叶片和无人机复合材料的诱导缺陷进行了量化研究。数字剪切术显示的条纹图案被用来通过将条纹的数量与缺陷或缺陷的深度联系起来来量化缺陷。通过材料表面缺陷上方的热点温度指示,实现了IRT对缺陷的定性评价。研究结果表明,剪切成像技术比红外热成像技术更灵敏。应该提到的是,没有为复合材料的测试量身定制的“既定标准程序”。每种被测试的复合材料对缺陷检测的反应可能不同,这通常取决于组件的几何形状和适合特定测试的加载系统的合适选择。本文报告的实验程序可作为设计任何特定复合材料部件或结构缺陷检测的测试或校准程序的基础。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
NDT detection and quantification of induced defects on composite helicopter rotor blade and UAV wing sections
Digital Shearography and Infrared Thermography (IRT) techniques were employed to test non-destructively samples from aircraft structures of composite material nature. Background information on the techniques is presented and it is noted that much of the inspection work reviewed in the literature has focused on qualitative evaluation of the defects rather than quantitative. There is however, need to quantify the defects if the threshold rejection criterion of whether the component inspected is fit for service has to be established. In this paper an attempt to quantify induced defects on a helicopter main rotor blade and Unmanned Aerospace Vehicle (UAV) composite material is presented. The fringe patterns exhibited by Digital Shearography were used to quantify the defects by relating the number of fringes created to the depth of the defect or flaw. Qualitative evaluation of defects with IRT was achieved through a hot spot temperature indication above the flaw on the surface of the material. The results of the work indicate that the Shearographic technique proved to be more sensitive than the IRT technique. It should be mentioned that there is "no set standard procedure" tailored for testing of composites. Each composite material tested is more likely to respond differently to defect detection and this depends generally on the component geometry and a suitable selection of the loading system to suit a particular test. The experimental procedure that is reported in this paper can be used as a basis for designing a testing or calibration procedure for defects detection on any particular composite material component or structure.
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