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제안 방법
- Energy based damage evolution is used in this study that employes energy release rates. BK(benzeggagh Kenane) is the most popular energy-based criterion as shown in equation 15.
- In this study, the main objective is to develop a progressive damage model that accounts in-plane failure as well as delamination and debonding damage between the fiber and matrix. In-plane damage modeling is done by using ABAQUS built in damage material model(hashin failure criteria).
- Progressive damage analysis is carried out on all lamina orientations, i.e., 0°, 45°, -45°, and 90° angles.
- Chen’s model and the present study are much closer to the experimental tensile strength. The current study provides the complete detail of the damage modes as well as accurately predicts the open-hole tensile strength.
- , 0°, 45°, -45°, and 90° angles. The significance of this study as compared to previous studies is that it presents the complete details of the damage initiation and progression of each ply in different damage modes such as described earlier in Hashin Failure criteria(fiber tension failure, fiber compression failure, matrix tension failure, and matrix compression failure).
- Most recently, cohesive zone modeling by using cohesive elements in ABAQUS is being used to predict the mechanical response and failure behavior of the composite structures and proven to be the reliable approach for modeling delamination failure. Therefore, in this study, the combination of Hashin damage model and cohesive zone elements is used to predict the correct failure modes and strength prediction of the notched composite laminates.
이론/모형
- The damage model provides a complete detail about the in-plane as well as delamination damage in a composite plate. ABAQUS built-in material model (hashin damage) was used for modeling laminate failure, and delamination damage was modeled by employing a layer of cohesive zone elements. Damage due to the matrix tension failure dominated in both damage initiation and damage evolution, whereas, fiber damage only occurred in 00 ply.
- Therefore, proper failure criteria are needed that accounts for all the damage modes in the notched composite structures. ABAQUS built-in material model(hashin damage model) is used in this study for modeling laminate failure and delamination is modeled by using cohesive elements. These damage models are discussed in detail in the following subsections.
- Damage initiation and the progression in the ply is characterized by using the inbuilt damage material model Hashin Failure criterion in the ABAQUS. The output variables assigned for the damage initiation are HSNMTCRT, HSNMCCRT, HSNFTCRT, and HSNFCCRT for the matrix and fiber failure in both tension and compression modes.
- The red colour indicates the most delaminated area and, the blue colour shows the undamaged area in the plot. In this work, the ABAQUS cohesive element is used for modeling delamination modeling. Delamination modeling using a cohesive element is very sensitive to the element size, and the element size must be small enough to capture the stress gradient in the wake of cracks.
- In this study, the main objective is to develop a progressive damage model that accounts in-plane failure as well as delamination and debonding damage between the fiber and matrix. In-plane damage modeling is done by using ABAQUS built in damage material model(hashin failure criteria). Delamination modeling is carried out by using cohesive zone approach.
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