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用带中心裂纹的Ｌｙ１２ＣＺ铝合金板模拟飞机的损伤结构，对于不同的修补方式（单边和双边修补），不同的补片材料（铝合金和复合材料）和几何尺寸以及脱胶等因素，进行了静强度和疲劳裂纹扩展试验． 实验表明． 胶结修补能明显地提高损伤结构的强度和疲劳寿命，同时实验还为修补实践的选材和几何参数的设计等提供了大量数据． 文中最后给出了修补结构疲劳裂纹的有限元计算估计，并与试验结果进行了比较和分析．
The damage structure of the aircraft was modeled using a Ly12CZ aluminum alloy plate with a central crack for various repair methods (unilateral and bilateral trimming), different patch materials (aluminum alloy and composite) and geometric dimensions, and degumming Static strength and fatigue crack propagation test. Experiments show. The cementing repair can obviously improve the strength and fatigue life of the damaged structure. At the same time, the experiment provides a large amount of data for the material selection and geometric parameter design of the repair practice. Finally, the finite element calculation of the fatigue crack in repair structure is given and compared with the experimental results.