Abstract: Through the finite element analysis of gyroscope fiber-optical ring under the linear acceleration field of spacecraft in large maneuvering motion, the deformation mechanism of the fiber-optical ring was obtained. Based on the theoretical knowledge of anisotropic materials, the micro-mechanics finite element method was used to apply periodic boundary conditions to the representative volume element (RVE) of the fiber-optical ring. Therefore, the equivalent material parameters of the fiber-optical ring were analyzed. The finite element program ANSYS was adopted to establish the spatial finite element model of the fiber-optical ring assembly and apply the acceleration field. The contact element was established to analyze the structural contact coupling effect during the deformation process. The analysis results show that the U-shaped structure and top cover of the fiber-optical ring assembly structure will contact with the fiber-optical ring after deformation under the action of acceleration field. In addition, the U-shaped structure and top cover structure will deform under the action of inertial force, which will affect the deformation of the fiber-optical ring.