Abstract
In order to develop a High Speed Civil Transport, weight reduction by the use of advanced composite materials is one of the most important technical issues. However, composite laminates have very low interlaminar fracture resistance. Therefore, the interlaminar fracture toughness of composites has consequently become a critical design parameter for the aircraft structures. In this research, mode-I interlaminar fracture behavior of heat-resistant polyimide CFRP (Carbon Fiber Reinforced Plastics) was investigated by way of the double-cantilever-beam (DCB) test at high temperature up to 200℃. In the DCB tests at high temperature, fiber cross-over bridging was observed. In order to evaluate the influence of the bridging zone length on the crack growth resistance curve (R-curve), the DCB tests were conducted using specimens with different thicknesses. Fractographic observations of the fracture surface were performed in order to assess the crack growth behavior. The bridging characteristics were evaluated using a bridging law which describes the relationship between the crack closure traction resulting from the bridging fibers and the local crack opening displacement.
Published Version (
Free)
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call