With the wide application of composite materials in aviation structures

the study on the aeronautical composite 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 sequences 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.