Composite bonding repair was one of the important processes for aircraft structural repair and the scientific bonding process design was an important factor to ensure the repair effect of aircraft damage structure.In order to study the influence of adhesive technology on repair and explore the best bonding process parameters,the finite element model was established to analyze the load transfer behavior of composite bonding repair interface by ANSYS workbench.The material and thickness of the patch,shear modulus and thickness of adhesive layer were taken to discuss the effect on bonding repair.The simulation results show that when the patch material is boron epoxy resin,the risk of adhesive failure is the smallest.When the patch is thicker,the effect of bonding repair is good,but too thick patch will weaken the effect of bonding repair.The larger shear modulus of the adhesive,the better the repairing of the damaged area.It is suggested to choose adhesive with high shear modulus in engineering application.The thicker layer will increase the probability of defects in the layer so as to weaken the repair effect.Therefore it is suggested to select the layer with minimum thickness reasonably.At last, the surface treatment of the repair interface,the glue overflow at the end of the composite material and the chamfering treatment are all beneficial to the load transfer of the repaired structure,to ease the stress of the adhesive interface and to reduce the risk of layer failure.