随着复合材料在航空结构中的广泛应用,航空复合材料修补技术也成为研究热点.通过复合材料单面胶接维修方法,将抛物线型损伤演化规律应用于胶层的损伤分析.对商业有限元软件进行了二次开发并建立了数值模型,研究了补片尺寸与厚度对修补结构压缩强度的影响.对复合材料胶接修补结构试验件进行剩余强度试验,研究了补片形状、尺寸、厚度等参数对修补后结构压缩剩余强度的影响.数值模拟结果与试验值吻合良好,误差在5%以内.%With the wide application of composite materials in aviation structures, the study on the aeronautical com-posite materials repairing has become a research focus. Under the background of single-sided adhesive bonding repaired composite laminates, this paper analyzed the residual strength of adhesive bonding composite structures and applied the failure theories and damage to the evolution of adhesive bonding composites. Based on FEM software platform, this paper proposed a united method for integrating multiple UMAT subroutines, and the numerical model had been establishment to analyze the compression strength variation with different diameters of single-sided adhesive bonding repaired composite laminates. An experimental test had been processed on single-sided adhesive bonding repaired composite laminates. By comparing the compression strength of different groups with different thickness, different shapes and different stacking se-quences of repairing patch, this paper investigated and generated design references that how to increase their compression residual strength to these composite structures. And the relative errors between predicted values and experimental results were less than 5 percent.
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