复合材料机翼前梁装配应力超声无损测量  

Assembly Stress Measurement of Front Beam in Composite Wing Based on Ultrasonic Non-destructive Testing Method

作　　者：葛恩德 王伟[3] 陈磊 周玉锋[3] 张宇民[3] Ge Ende;Wang Wei;Chen Lei;Zhou Yufeng;Zhang Yumin(Institute of Aeronautical Manufacturing Technology,Shanghai Aircraft Manufacturing Co.,Ltd.,Shanghai 201324,China;National Engineering Research Center for Commercial Aircraft Manufacturing,Shanghai 200436,China;Science and Technology on Advanced Composites in Special Environments Laboratory,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]上海飞机制造有限公司航空制造技术研究所,上海201324 [2]国家商用飞机制造工程技术研究中心,上海200436 [3]哈尔滨工业大学特种环境复合材料技术重点实验室,哈尔滨150001

出　　处：《工程塑料应用》2018年第7期96-100,106,共6页Engineering Plastics Application

基　　金：国家973计划项目(2014CB046504;2014CB046505)

摘　　要：针对装配应力是影响飞机构件连接性能的重要因素,也是复合材料装配质量研究的难点所在的问题,通过考虑被测材料各向异性对超声波传播特性的影响,改进传统超声应力检测方法,得到适用于纤维增强类复合材料平面应力的检测方法。为了验证改进方法的可行性,对复合材料机翼中实际采用的碳纤维增强树脂基复合材料结构件进行了装配应力的检测。经可行性分析,确定复合材料结构件应力检测主要实验方案,为今后飞机复材结构件的内部应力检测试验提供基础。Aiming at the problems that assembly stress was an important factor affecting the connection performance of aircraft components, and it was also a difficult point for the study of the assembly quality of composite materials, by considering the infiuence of anisotropy of measured material on the propagation characteristics of ultrasonic waves, the traditional ultrasonic stress measuring method was improved, and the measuring method for plane stress of fiber reinforced composites was obtained. In order to verify the feasibility of the improved method,the assembly stress of carbon fiber reinforced polymer matrix composite structure was tested in composite wing. Through the feasibility analysis, the main test plan of stress measuring for composite structure components was determined, which provided a basis for the future internal stress test of aircraft composite structures.

关 键 词：超声应力检测 装配应力 复合材料 LCR波 

分 类 号：TB33[一般工业技术—材料科学与工程] V258[航空宇航科学与技术—航空宇航制造工程]