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.