为研究金属裂纹板复合材料胶接修补结构的裂纹扩展行为, 进行了LY12CZ航空铝合金裂纹板碳/环氧复合材料补片胶接修复结构的疲劳性能测试试验, 观察修补结构疲劳失效模式, 并测量一定疲劳周次下的铝合金板的裂纹长度。建立了考虑裂纹扩展, 界面脱粘两种失效模式相互耦合的三维非线性有限元分析模型, 计算出不同裂纹长度对应的疲劳寿命, 对修补结构的疲劳性能进行了评估, 其数值计算与试验结果吻合较好。
Fatigue crack growth test for cracked metallic plate of LY12CZ aluminum alloy repaired with adhesive bonding Carbon/epoxy composite patch is conducted to validate the crack growth behaviour of crack patching.The main fatigue failure modes observed in the test are crack growth and adhesive debonding.The crack length and debonding area are measured with different numbers of cycles.The nonlinear 3D finite element model considering adhesive debonding and crack growth are developed.The experimental and analytical results are in good agreement with each other.
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