Abstract
A new fatigue life prediction model is developed for composite laminates based on both infrared thermographic data and stiffness degradation process. The fatigue limit is firstly determined by the improved thermographic method and then a two-parameter function is proposed to describe the normalized stiffness degradation of specimens subjected to various maximum loading stresses. These two parameters can be calibrated by the stiffness degradation data and stabilized temperature data. Thereafter, the calibrated model can be used to predict S-N curve. The proposed model is applied the experimental data from literature and the results show that the predicted S-N curve has a well agreement with the experimental one.
Highlights
Fatigue property of composite laminates receives more and more concerns since they are usually used in aerospace, automotive and marine load-bearing components
There are three different improved graphic methods and we chose Method 2 and Method 3 here because for the infrared thermography (IRT) data in [18], the values of fatigue limit determined by Method 1 and Method 3 are the same, while Method 3 has a relative larger application scope
The proposed model combined temperature rising with the stiffness degradation process
Summary
Fatigue property of composite laminates receives more and more concerns since they are usually used in aerospace, automotive and marine load-bearing components. Based on IRT data analysis, many criteria have been developed to rapidly determine fatigue limit and obtain S-N curves for metallic alloys [1,2,3,4,5,6,7]. Those criteria may not be accurate any more for composite laminates because damage and failure mechanisms are different and more complicated (compared to metallic materials). After parameter calibration with the experimental stiffness degradation and IRT data, the model can be used to predict S-N curve
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