飞机受损件激光喷丸残余应力调控研究

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

论文基于残余压应力-激光喷丸搭接率的拟合关系式,设计出非均匀搭接率下的激光光斑位置路径;基于ABAQUS软件建立了7075-T6铝合金受损件激光喷丸有限元模型,实现了非均匀搭接率下激光喷丸有限元数值模拟并获得残余应力场的分布情况。结果表明,采用非均匀搭接率的激光喷丸方法可使试样表面在打磨或受到拉伸载荷后仍处于应力均匀分布的状态;通过增加搭接率调控残余应力值的大小,还可实现修复件表面在受到拉伸载荷时处于均匀压应力状态,从而抑制疲劳裂纹的萌生和扩展。试验结果与模拟结果一致,验证了模型的可靠性。

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.