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为评估金属损伤复合材料胶接修补结构的剩余强度和剩余寿命,进行了含腐蚀和疲劳损伤LY12CZ航空铝合金板碳/环氧复合材料补片胶接修复结构的力学性能试验,分析了在静拉伸和疲劳载荷作用下修补结构的破坏模式、失效机理。试验研究发现:复合材料胶接修补技术有效改善了腐蚀和疲劳损伤这两类损伤区域的受力状况,恢复了其载荷传递路线,其静拉伸失效形式为金属韧性断裂后胶层脱粘的分步渐进式破坏;与含损伤未修补试样相比,胶接修补大幅度提高了试件的剩余强度和剩余寿命恢复率,修补后铝合金试件承载能力增加了约25%,疲劳寿命增加至修补前的约4倍~5倍。
In order to evaluate the residual strength and residual life of the adhesive-repaired structure of metal-damaged composite, the mechanical properties of the composite structure of LY12CZ aeronautic aluminum alloy plate with epoxy / epoxy composite were investigated. Failure mode and failure mechanism of repaired structures under tension and fatigue loads. The experimental results show that the composite cementing repair technology can effectively improve the stress conditions of corrosion and fatigue damage, and restore the load transfer route. The static tensile failure mode is the debonding of the layer after the ductile fracture Compared with the uncoated samples, the adhesive bond repairing greatly improved the residual strength and the remaining life recovery rate. The carrying capacity of the repaired aluminum alloy increased about 25%, and the fatigue life Increased to about 4 times before repair to 5 times.