复合材料层合厚板的冲击响应及分层损伤研究

复合材料层合结构是飞机的主要受力构件,研究其冲击响应及分层损伤非常重要。针对5 mm厚40层铺层的层合板分别进行15 J、30 J、45 J的落锤实验,研究低能量冲击的动力响应。然后进行超声C扫描检测获得各界面的分层损伤情况,以分析分层损伤在面内及厚度方向上的分布特性,并在此基础上研究损伤的形成机理,对分层的分布特性进行解释。据此,可对层合板界面分层损伤进行预测,使其得以在实际工程中评估剩余强度以保证构件安全,同时也将有助于层合板的结构优化设计。

Study of Impact Response and Delamination in Thick Composite Laminates

Since composite laminated structure is an essential component in airplane construction, it is necessary to study its impact response and delamination. In this paper, Drop weight tests were carried out to the composite laminates with the impact energy of 15 J, 30 J, 45 J respectively. The thickness of the laminates are 5 mm with 40 layers included. Therefore, the impact dynamic response could be studied. Ultrasonic C-scan was then used to get the delamination region of each interface. The distribution characteristics of the delamination both in ply and along thickness were focused on, and then turn over the verification again by discussing the damage mechanism. Accordingly, it will be possible to predict the delamination of a composite laminates, and make further efforts to evaluate residual strength for safety in practical application. Moreover, it may contribute to the optimization design for composite laminated structures.