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

作　　者：袁英民[1] 孙金立[1] 陈新波[1] 

机构地区：[1]海军航空工程学院青岛校区海军航空装备无损检测中心,青岛266041

出　　处：《无损检测》2013年第7期19-20,53,共3页Nondestructive Testing

摘　　要：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.

关 键 词：复合材料 层压结构 原位超声检测 探头 

分 类 号：TG115.28[金属学及工艺—物理冶金]