飞机复合材料层压缺陷原位超声波检测的探头研制及试验

Probe Design and Experiment In-situ Ultrasonic Detection of Aircraft Composite Lamination Defects

为了解决飞机复合材料层压缺陷原位检测的难题,通过理论计算和试验研究,确定了双晶探头的焦距及倾斜角、压电晶片宽度及隔板厚度,探头规格等主要参数,研制了适合飞机复合材料层压结构原位检测的双晶超声波探头,方便地实现了复合材料层压板的原位检测。

In order to meet the requirement for aircraft composites laminate in-situ testing, the main parameters about the focal length and inclination angle, width and thickness of the piezoelectric wafer separator, and probe specifications etc are determined through the theoretical calculation and experimental research. The bimorph ultrasonic probe for in-situ detection of composite laminated structure is developed and in situ detection of composite laminates is easily realized.