Journal of South China University of Technology(Natural Science Edition) ›› 2022, Vol. 50 ›› Issue (3): 73-79.doi: 10.12141/j.issn.1000-565X.210309

Special Issue: 2022年机械工程

• Mechanical Engineering • Previous Articles     Next Articles

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

ZHANG Junhao1 CHENG Xiuquan2 XIA Qinxiang1 CHENG Sizhu2   

  1. 1. School of Mechanical and Automobile Engineering, South China University of Technology, Guangzhou 510640, Guangdong, China; 
    2.Aircraft Maintenance Engineering College, Guangzhou Civil Aviation College, Guangzhou 510403, Guangdong, China
  • Received:2021-05-17 Revised:2021-06-21 Online:2022-03-25 Published:2022-03-01
  • Contact: 夏琴香（1964-），女，博士，教授，主要从事塑性成形、模具及装备技术研究。 E-mail:meqxxia@scut.edu.cn
  • About author:张俊豪（1992-），男，博士生，主要从事塑性成形、模具及装备技术研究。E-mail：415709826@qq.com
  • Supported by:
    Supported by the National Natural Science Foundation of China（51575117）, Guangdong Basic and Applied Basic Research Fund Project (2021A1515011074)

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Abstract: 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.

Key words: 7075 aluminum alloy, damaged component, laser shock peening, non-uniform overlap, residual stress control

CLC Number: