Study on Residual Stress Control of Damaged Aircraft Component Based on Non-uniform Overlap Ratio Laser Shock Peening

Based on the fitting relationship between residual compressive stress and overlap ratio, the laser spot path was designed under non-uniform overlap ratio. A laser shock peening finite element (FE) model for laser shock peening damaged 7075 aluminum alloy component was established based on ABAQUS software. The non-uniform overlap ratio laser shock peening simulation was realized and the distribution of residual stress was obtained. The results show that the non-uniform overlap ratio laser shock peening can keep the surface of the specimen in a state of uniform stress after grinding or under tensile load. By increasing the overlap ratio to control residual stress, the surface of the repaired component can be kept in a state of uniform compressive stress under tensile load, so as to inhibit the initiation and propagation of fatigue cracks. The experimental results are consistent with the simulation results, which verifies the reliability of the model.