The invention provides a wing structure mechanics high-fidelity order reduction simulation method. The method comprises the steps of finite element grid node pairing and rigid body constraint application, non-shear load loading analysis, shear load loading analysis and equivalent section attribute calculation. The invention relates to electronic equipment and a storage medium, which are used for the method. According to the method, the problem that the internal force of the structure does not have periodicity when the slender structure is under the action of the shearing force is well solved,the shearing force condition is corrected by utilizing the mechanical response of the structure unit cells under the action of the bending load, the disturbance displacement field and the surface force are restrained, the form is simple and clear, and the embeddability is good. According to the method, the equivalent section stiffness matrix of the equivalent reduced-order model can be calculatedby simulating deformation of the wing structure unit cells under different loads, so that a reduced-order model unit is provided for finite element analysis of the aircraft wing, and the analysis efficiency of the aircraft wing model is improved.