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Analysis of the plastic zone under mixed mode fracture in bonded composite repair of aircraft structures

机译：飞机结构粘结复合修复混合模式断裂塑性区分析

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摘要

Material fracture by opening (mode I) is not the only failure criteria responsible for fracture propagation. Many industrial examples show the presence of mode II and mixed mode I + II. In the present work, numerical analyses of the three-dimensional and non-linear finite element method are used to estimate the performance of the bonded composite repair of metallic aircraft structures with a pre-existent damage by analyzing the plastic zone size ahead of repaired cracks under mixed mode loading, to assess the effect of the composite repair system on the plastic zone. The Von Mises stress is used to predict yielding of materials under this loading condition. The extension of the plastic zone, which takes place at the tip of a crack, strictly depends on many variables, such as the yield stress of the material, the loading conditions, the crack size and the thickness of the cracked component.
机译：开孔造成材料断裂（模式I）不是造成裂纹扩展的唯一失败准则。许多工业示例显示了模式II和混合模式I + II的存在。在目前的工作中，通过三维和非线性有限元方法的数值分析，通过分析修复后的裂纹前的塑性区大小，来估计具有预先损坏的金属飞机结构的粘结复合材料修复的性能。在混合模式载荷下，评估复合修复系统对塑性区的影响。冯·米塞斯（Von Mises）应力用于预测在此加载条件下材料的屈服。发生在裂纹尖端的塑性区的延伸严格取决于许多变量，例如材料的屈服应力，载荷条件，裂纹尺寸和裂纹组件的厚度。

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