| Citation: |
ZHANG Xudong, DUAN Qingfeng, CAO Dongfeng, et al. Decoupling cohesion method based on Mode I delamination damage mechanism of composite materials[J]. Acta Materiae Compositae Sinica, 2024, 41(9): 4942-4955. DOI: 10.13801/j.cnki.fhclxb.20240311.004
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Delamination damage is one of the most common failure modes in composite laminated panel structures. Delamination damage has the characteristics of complex damage mechanisms and difficult to observe damage evolution processes. It is crucial to deeply analyze the impact of various damage mechanisms on the process of delamination propagation in order to study layered damage. In order to deeply analyze the interrelationships between various damage mechanisms in the crack tip damage zone and the evolution process of fiber bridging damage, this paper conducted a research on a mode I interlayer failure cohesive force method based on the decoupling of damage mechanisms through a combination of experiments and numerical analysis.
In terms of experiments, three different interlayer layers (0//0, 0//45, 0//90) were specifically used to design T700 level carbon fiber/epoxy composite laminates and conduct Mode I delamination tests. By observing the initiation of delamination and the process of damage evolution, the load displacement curve and R-curve patterns of DCB test results were summarized. Based on various characterization methods such as sample fracture morphology and SEM, the damage mechanism at the crack tip was revealed. A new method for decoupling the layered damage mechanism was proposed based on this experiment. This method is based on the superposition of three bilinear cohesive force constitutive models, and decouples the layered damage mechanisms of different damage scales by establishing cohesive force unit models, independently characterizing the contributions of different damage mechanisms in the process of layered expansion
(1) The Mode I fracture toughness is significantly affected by the interlayer angle, showing an increasing trend with the increase of interlayer angle. The initial fracture toughness value of the 0//0 specimen is not significantly different from the steady-state fracture toughness value, while the difference between the 0//45 and 0//90 specimens is significant. The crack propagation path of the specimen is also affected by the ply angle. The crack propagation path of the 0//0 specimen is relatively smooth, while the crack propagation paths of the 0//45 and 0//90 specimens are more winding and rugged, resulting in more energy loss. This is one of the influencing factors on the nominal fracture toughness value.(2) The interlayer angle has a significant impact on fiber bridging. The fiber bridging amount in the 0//0 sample is relatively small, resulting in a less obvious R curve phenomenon and a slower evolution rate of the R curve. The 0//90 sample has the highest fiber bridging content and a significant R curve phenomenon, while the R curve evolution rate is the fastest.(3) Through SEM characterization, it was found that the damage zone at the crack tip is composed of two main damage mechanisms: matrix fracture and matrix/fiber separation. Some fiber bridges formed by dislocation after matrix/fiber separation interact with the damage zone at the crack tip. It was also found that the matrix of the 0//0 specimen is mainly brittle fracture, while the matrix of the 0//90 specimen exhibits plastic shear deformation in addition to brittle fracture. The differences in interlayer damage mechanisms determine the differences in interlayer fracture toughness values.(4) On the basis of the experiment, a new method for decoupling the damage mechanism was proposed. By coupling three bilinear cohesive force constitutive models, a decoupled cohesive force element model is established. One constitutive model corresponds to two damage mechanisms: matrix cracking and matrix/fiber separation without displacement. The other two constitutive models correspond to two different scale damage mechanisms of fiber bridging. The three constitutive models correspond to three cohesive force elements. This method effectively simulated the crack propagation behavior of DCB specimens in various layers, independently characterizing the contributions of different damage mechanisms in the crack tip damage zone during the damage evolution process. The simulation results obtained are consistent with the experimental results. At the same time, this method also has the advantages of simple modeling, clear damage mechanism, most parameters can be directly obtained from experiments, and high computational efficiency.Conclusions: This study compared the Mode I delamination test results of T700 level carbon fiber/epoxy composite materials with three different interlayer angles, analyzed the influence of different interlayer angles on the damage zone and bridging fiber area at the crack tip, and revealed the damage mechanism at the crack tip through microscopic characterization methods. On the basis of experiments, this study proposes a new method for decoupling damage mechanisms. By coupling three bilinear cohesive force constitutive models, a decoupled cohesive force unit model is established. One constitutive model corresponds to two types of damage mechanisms: matrix cracking and matrix/fiber separation without dislocation, while the other two constitutive models correspond to two different scales of damage mechanisms: fiber bridging. The simulation results obtained are consistent with the experimental results. This method effectively simulates the damage evolution process of crack tip damage zones in specimens with different interlayer layers. It not only independently characterizes the different damage mechanisms in the crack tip damage zone, but also reveals the contribution of each damage mechanism to the delamination propagation process. It provides a favorable tool for simulating the mode I delamination fatigue damage evolution of composite materials under more complex fatigue cyclic loads in the future.
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