For identification of the coupling stiffness of MEMS (Micro-electro-mechanical System) gyroscopes, a identification method was proposed based on the frequency response characteristics of the drive-axis, sense axis, drive-to-rotation coupling and rotation-to-sense coupling. A dual-mass linear vibrating MEMS gyroscope with decoupled drive-to-sense and sense-to-drive displacement was designed. Based on simplified stiffness characteristics of the beams, the dynamic planar movement equations of the gyroscope were established and the drive-axis, sense-axis, drive-to-rotation and drive-to-sense transfer functions were derived. According to the coupling model, the sources of stiffness coupling were attributed to the stiffness error of specific beams. The drive-to-rotation coupling stiffness could be identified by the ratio of drive-to-rotation coupling to drive-axis frequency responses, and rotation-to-sense coupling stiffness could be identified by the ratio of drive-to-sense to sense-axis frequency responses. The frequency responses of the gyroscope were investigated by the proposed coupling stiffness identification method, and results show that coupling stiffness coefficients by drive-to-rotation and rotation-to-sense for the tested gyroscope are 0.14 N and 0.054 33 N, respectively. It concludes that the identification results provide references for laser trimming of the beams for gyroscopes.