Abstract
T700/6808 composite has been widely used in aerospace field and the damage in composite will seriously influence the safety of aircraft. However, the behavior of damage evolution in T700/6808 composite when it suffered from tensile loading is seldom researched. In this paper, the acoustic emission (AE) technology is employed to research the process of damage evolution in T700/6808 composite under tensile loading. Results show that the damage in T700/6808 composite is small in the initial stage of tensile loading, and main damage is the matrix cracking. The composite has serious damage in the middle stage of tensile loading, which mainly includes the matrix cracking and the interface damage as well as the fiber breakage. The number of fiber breakages decreases rapidly in the later stage of tensile loading. When it comes into the stage of load holding, the composite has relatively smaller damage than that in the stage of tensile loading, and the fiber breakage rarely occurs in the composite. Analysis of damage modes shows that the criticality of the matrix cracking and the interface damage is higher than the fiber breakage, which illustrates that the reliability of T700/6808 composite could be improved by the optimization of matrix and interface.
Highlights
T700/6808 composite is a new kind of carbon fiber reinforced epoxy resin matrix composite, which has been widely used in the aircraft structure for its excellent properties, such as light weight, high specific strength, and well resistance to the fatigue fracture [1, 2]
Three specimens were used in the experiment, and it is found that the damage behavior and the change trend of Acoustic emission (AE) signal are similar among three specimens during tensile testing; the specimen of number 1 is studied in detail
In the initial stage of tensile loading (0–60 s), the AE hit number is mainly distributed in the interval between 0 and 20. When it comes into the middle stage of tensile loading from 60 s, the AE hit number suddenly increases to about 85
Summary
T700/6808 composite is a new kind of carbon fiber reinforced epoxy resin matrix composite, which has been widely used in the aircraft structure for its excellent properties, such as light weight, high specific strength, and well resistance to the fatigue fracture [1, 2]. T700/6808 composite which will influence the structural safety of aircraft. Chou et al [6] used the AE method to detect the damage in carbon fiber composite pressure vessel. Maillet et al [8] proposed an AE detection method with double sensors, which could evaluate the energy attenuation of damage process in composite structure. Saeedifar et al [9] used AE method for detecting the delamination damage in glass reinforced epoxy resin composite. Masmoudi et al [11]
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
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
