飞机中金属结构件的局部损伤会显著降低其机械强度与疲劳寿命，复合材料粘接修补作为一种高效的解决方案，在近年来引起了广泛的关注。聚焦于碳纤维层合板对铝合金结构件的静拉伸强度的修补效果，设计圆孔及裂缝两种铝合金结构件的典型缺陷模式，结合试验分析及有限元计算，探究了修补方式（单侧修补及双侧修补）、复合材料补片厚度以及铝合金结构件厚度等修补因素的影响。设计了楔子耐久性试验对常用的胶膜及表面处理方法进行了选择，在此基础上设计静拉伸试验方案针对上述修补因素开展分析。构建了复合材料修补铝合金试件的有限元模型，并基于试验结果验证了该模型对修补效果预测的有效性。分析结果表明，碳纤维层合板可有效修补含有典型缺陷的铝合金结构件，其修补后强度恢复率达到95%以上。复合材料补片厚度在满足最小要求时，0.5 mm及1.0 mm厚的复材补片均可使铝合金试件恢复至接近完好试件的强度。在复合材料补片厚度一定时，铝合金母板厚度增加10%，修补效果降低10%，而修补方式则对修补效果未见显著影响。

Localized damage incurred by metal structural components within aircraft can significantly diminish the strength and fatigue durability. In recent years, the bonding repair technique involving composite material has garnered substantial attention as an efficient solution to this issue. Focusing on the repair effect of carbon fiber laminates on the static tensile strength of aluminum alloy structural components, two typical defect modes of circular holes and cracks in aluminum alloy structural components were designed. Combined with experimental analysis and finite element calculation, the influence of repair methods (single-side repair and double-side repair), composite material patch thickness, and aluminum alloy structural component thickness on repair factors was explored. A durability test for wedges was designed to select commonly used adhesive films and surface treatment methods. Based on this, a static tensile test plan was designed to analyze the repair factors mentioned above. A finite element model for repairing aluminum alloy specimens with composite materials was constructed, and the effectiveness of the model in predicting the repair effect was verified based on experimental results. The analysis reveal that carbon fiber laminates exhibit a notable capacity for effectively repairing typical defects in aluminum alloy structural components. The repaired strength closely approximates that of pristine specimens, and the strength recovery rate after repair can reach over 95%. When the thickness of the composite patch meets the minimum requirement, both 0.5 mm and 1.0 mm thick composite patches can restore the strength of the aluminum alloy specimens to nearly that of the intact specimens. When the thickness of the composite patch is constant, a 10% increase in the thickness of the aluminum alloy base plate leads to a 10% decrease in the repair effect, and the repair method does not exert a substantial influence on the overall repair effectiveness.