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Fatigue analysis of cracked thick aluminum plate bonded with composite patches

机译：复合补片粘结的开裂厚铝板的疲劳分析

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Repairs of metallic aircraft structures with composite patches have been accepted as a reliable technology, and studies for crack repairs to 11.43 mm thick aluminum plate are conducted in this paper. The stresses analyses are performed for four different aluminum plates, including no crack, with crack, with crack and single-side patched composites, as well as crack and double-side patched composites. The stress intensity factor analysis and the fatigue life calculations are performed for the following two cases: the cracked aluminum plate and the cracked plate repaired with the composite patches. The fatigue experimental tests for the above structures were conducted with MTS test machine. The Paris law of crack propagation and the nonlinear material properties of the aluminum combined with the FEM is to predict the fatigue life. It is showed that fatigue crack propagation characteristics obtained from FEM match very well with the experimental results.
机译：用复合材料修补金属飞机结构已被认为是一项可靠的技术，并且本文对11.43毫米厚的铝板进行了裂纹修复研究。对四个不同的铝板进行了应力分析，包括无裂纹，有裂纹，有裂纹和单面修补的复合材料，以及有裂纹和双面修补的复合材料。针对以下两种情况进行了应力强度因子分析和疲劳寿命计算：破裂的铝板和用复合补片修复的破裂的板。用MTS试验机对上述结构进行了疲劳试验。裂纹扩展的巴黎定律和铝的非线性材料特性与有限元法相结合，可以预测疲劳寿命。结果表明，有限元分析得到的疲劳裂纹扩展特征与实验结果吻合良好。

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