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现有含冲击损伤复合材料层合板的寿命预测方法是建立在冲击后复合材料层合板的疲劳性能基础之上的,导致模型和方法不具有通用性。因此,针对含冲击损伤的复合材料层合板,基于逐渐累积损伤理论和无损单向板的疲劳特性,建立一种具有普遍适用性的三维逐渐累积损伤的疲劳寿命预测方法。该方法可对不同铺层参数、不同几何尺寸以及不同冲击条件下层合板的疲劳寿命进行预测。为了在缺少冲击试验时也能实现受到冲击载荷后层合板的疲劳寿命预测,对层合板在冲击载荷及冲击后疲劳载荷作用下的破坏进行全程分析,将预测得到的冲击损伤状态用于分析冲击后的疲劳寿命。同时基于全程分析的方法,开发了参数化的复合材料层合结构冲击及冲击后疲劳破坏模拟程序。与试验对比,最大误差为7.78%。
The existing methods for predicting the life of composite laminates with impact damage are based on the fatigue properties of the composite laminates after impact, resulting in the lack of commonality of models and methods. Therefore, based on the theory of progressive cumulative damage and the fatigue characteristics of non-destructive unidirectional plates, a fatigue life prediction method for three-dimensional progressive cumulative damage with general applicability is proposed for composite laminates with impact damage. The method can predict the fatigue life of laminate under different ply parameters, different geometrical dimensions and different impact conditions. In order to predict the fatigue life of laminates subjected to impact load in the absence of impact test, the damage of laminates under impact loads and post-impact fatigue loads is analyzed. The predicted impact damage state is used to analyze the impact After the fatigue life. At the same time, based on the method of full analysis, a parametric composite laminated structure impact and impact fatigue damage simulation program was developed. Compared with the test, the maximum error is 7.78%.