Open-hole tensile progressive damage and failure prediction of carbon fiber-reinforced PEEK-titanium laminates
Open-hole tensile progressive damage and failure prediction of carbon fiber-reinforced PEEK-titanium laminates
复制标题
DOI：
10.1016/j.compositesb.2015.12.049
复制
发表时间：
2016-04-15
影响因子：
13.1
通讯作者：
Tao, Jie
中科院分区：
文献类型：
--
作者：
Du, Dandan;Hu, Yubing;Tao, Jie
本文研究了一种热塑性塑料基纤维金属层压板（FML），通过热压工艺制备，利用钛箔，碳纤维增强PEEK垫片，PEEK薄膜（界面粘结层）。采用数值模拟和试验相结合的方法，研究了开孔拉伸过程中的渐进损伤破坏机理。在模拟过程中，我们采用了三个失败的标准钛（韧性损伤），braugs（一个渐进的损伤方面的应变），和界面粘结层（内聚模型）来预测层压板的失败。在实验中进一步验证了其损伤行为。开孔抗拉强度和应力应变响应与数值模拟结果吻合较好。结果表明，纤维沿加载方向沿着断裂始于层合板屈服点之后，随后是基体损伤。当施加的载荷达到极限值时，钛层和纤维层之间的分层扩展到整个截面，导致钛断裂。验证模型也可用于其他类似结构的缺口或螺栓FML。(C)2016爱思唯尔有限公司版权所有
This paper studied a thermoplastic-based fiber metal laminate (FML) prepared via a hot-pressing process utilizing titanium foils, carbon fiber reinforced PEEK prepregs, and PEEK films (interface bonding layers). The open-hole tensile progressive damage and failure mechanisms were investigated by numerical and experimental methods. During the simulation, we employed three failure criterions for titanium (ductile damage), prepregs (a progressive damage in terms of strains), and interface bonding layers (cohesive model) to predict the failure of the laminates. In the experiments, the damage behavior was further verified. The open-hole tensile strength and stress strain response agreed well with the numerical results. It was found that fiber breakage along the loading direction initiated after yield point of the laminates, following by matrix damage. When the applied load reached the ultimate value, the delamination between the titanium layer and the fiber layer propagated to the entire section, causing titanium fracture. The validated model can also be used on other notched or bolted FMLs with similar structure. (C) 2016 Elsevier Ltd. All rights reserved.