To address the conflict issues among structural mass, maximum deformation, and equivalent stress in traditional lightweight design of aircraft structures, and to improve optimization efficiency while reducing complexity, a multi-objective genetic algorithm optimization mechanism based on a BP neural network surrogate model was proposed. Additionally, to explore new internal structural layouts for wings, a curved beam rib configuration was adopted. The feasibility of this method was validated using the wing box of a specific aircraft as the research subject. Compared to the original wing box, the optimization mechanism achieved an 8.16% reduction in mass, a 0.42% decrease in structural deformation, and a 12.75% reduction in maximum equivalent stress, significantly enhancing structural performance. The established optimization mechanism can serve as a reference for the lightweight design of aircraft structures.
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