Laser shot peening deformation correction strategy for complex aviation structural components based on equivalent stress method

Aiming at the deformation problem of aviation aluminum alloy structural components during processing, this paper proposes a laser shot peening deformation correction strategy based on the equivalent stress method. By combining theoretical and simulation methods, the deformation control strategy of typical 7050-T7451 aluminum alloy structural components is studied. Firstly, typical characteristic structures were analyzed based on complex structural components. Then, deformation prediction models were established for T-shaped parts and spacer frame workpieces: After double-sided shot peening of the T-shaped part, symmetrical upward convex bending deformation occurred, and its deflection had a nonlinear relationship with the laser power density and the thickness of the web plate. Single-sided shot peening of the spacer frame components can induce local bulging deformation. The maximum bulging height is quantitatively correlated with power density, shot peening area and structural parameters. Finally, taking a certain large wall panel as an example, through a zoned and step-by-step correction strategy, the overall bending deformation was corrected by double-sided shot peening of the reinforcing ribs (power density 1.47–2.54 GW/cm²) first, and then the bulging deformation was eliminated by single-sided shot peening of the web plate of the spacer frame (2.26 GW/cm²). Reduce the maximum bending and bulging deformation by 93.0% and 91.2% respectively. The research results provide a theoretical framework and preliminary simulation-based validation for the precise deformation correction of complex structural components in aviation.