Mechanical connection mechanisms used in space optical systems experience problems with lubrication, thermal expansion coefficient matching, problems related to its complex structure, and small docking eccentricities. In this study, a flux-pinning interface scheme, which can be applied to a large segmented reflect mirror in space, was proposed. The mathematical model that contained the current equivalent distribution model was built and calculated by the H-formulation method,then, verification experiments were designed to demonstrate the effectiveness of the model. The relationship between the levitation force, stiffness, and relative position of the flux pinning interface under three working condition was obtained using the finite element method. The results indicate that when the distance between the superconductor and permanent magnet is 5 mm, the stiffness of the vertical direction ky can reach 7 000 N/m; when the distance between the superconductor and permanent magnet is 10 mm and it is in a central position, the stiffness of the lateral direction kx can reach 3 800 N/m. The stiffness of the vertical direction ky when Δx=4 mm drops by 20% as compared with the one with Δx=0 mm, therefore, the mechanism can provide greater Δx values than traditional mechanisms and sufficient stiffness, which can also be used for buffering when docking.