The increasing use of composite materials in the aviation industry has led to a greater need to maintain composite structures’ safety against impact damage, especially when exposed to repetitive loading. Since experimental work can be challenging, proposing a simple and practical method of co-simulating composite laminates’ impact and fatigue behavior is crucial. This research presents composite and cohesive fatigue models based on the fundamental models of Shokrieh-Lessard and Turon. Additionally, two impact models with parameters consistent with these fatigue models are presented as well. Then, the impacted composite laminates are analyzed using a VUMAT that includes these models, and the results are compared to experimental data. The numerical analysis shows that the propagation patterns and shapes of different damage modes for impact and tension–tension fatigue are similar to experimental observations. However, for tension–compression, the simulation results differ partially from the tests. The tensile fatigue results showed that the impact had no significant effect on the specimen’s life. In contrast, a 2.1 J impact reduces specimens’ fatigue life for a maximum load of more than 40 % of the compressive strength, under tension–compression fatigue.

中文翻译：

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受影响的碳/环氧复合材料层压板的疲劳寿命模拟

复合材料在航空工业中的使用越来越多，因此更加需要保持复合材料结构的安全性以防止冲击损坏，特别是在承受重复载荷时。由于实验工作可能具有挑战性，因此提出一种简单实用的方法来协同模拟复合材料层合板的冲击和疲劳行为至关重要。本研究提出了基于 Shokrieh-Lessard 和 Turon 基本模型的复合疲劳模型和内聚疲劳模型。此外，还提出了两个参数与这些疲劳模型一致的冲击模型。然后，使用包含这些模型的 VUMAT 分析受影响的复合材料层压板，并将结果与​​实验数据进行比较。数值分析表明，冲击和拉拉疲劳不同损伤模式的传播模式和形状与实验观察结果相似。然而，对于拉伸-压缩，模拟结果与测试部分不同。拉伸疲劳结果表明冲击对试件的寿命没有显着影响。相比之下，在拉压疲劳下，最大载荷超过压缩强度 40% 时，2.1 J 的冲击会缩短样本的疲劳寿命。