Modeling and Experimental Study on the Micro-Vibration Transmission of a Control Moment Gyro

A control moment gyro (CMG) is the main source of vibration disturbance in the spacecraft. This paper presents a vibration mathematical model with 18 degrees of freedom by Lagrange energy method, for solving the problem that the transmission mechanism for the micro-vibration of the CMG is not clear. The parameters of the micro-vibration transmission model are identified by modal analysis, frequency response analysis, and dynamic-static unbalanced excitation analysis. The numerical simulation was performed to obtain the disturbance force of the CMG. The prototype was fabricated and an experimental system was established. The test results show that the numerical and experimental values of the disturbance force have highly consistent in accuracy, the maximum deviation is 4.77%. It demonstrates that the establishment of the micro-vibration transfer model of the CMG can predict its micro-vibration characteristics. This paper provides a sound theoretical basis and guidance for designing the CMG with ultra-low micro-vibration.