Abstract: In order to understand the resonance mechanism between the control moment gyroscope (CMG) and the honeycomb panel to guide the micro-vibration ground tests, an equivalent dynamic model of CMG on honeycomb panel was established. A semi-analytical solution of the stiffness matrix of honeycomb panel was derived by the equivalent plate theory and thin plate theory. By combining the CMG inertia matrix and gyroscopic matrix, which vary with the frame angle, the variation pattern of the CMG natural frequency and its fluctuation were obtained. The design suggestion for the CMG was proposed in order to provide theoretical support and guidance for the ground test design of CMG, as well as solve the resonance problem between CMG and honeycomb panel.