Micro-vibration Analysis of a Satellite on Orbit by Using a Flexible Multibody Dynamic Model

During the on-orbit operation of a satellite, the micro-vibration generated by various disturbance sources affects the attitude stability and pointing accuracy of the satellite, as a result, reduces the performance of the payload on the satellite. In this paper, the micro-vibration analysis of a satellite dynamic simulation of the flexible multibody system of the micro-vibration satellite is studied by using a flexible multibody dynamic model, which takes the main disturbance sources and payload requirements into consideration. Firstly, the absolute nodal coordinate formulation (ANCF) and the natural coordinate formulation (NCF) are used to accurately describe the large deformations and large overall motions of the whole satellite and rigid payloads, respectively. Secondly, the rigid body dynamic model of the momentum wheel is derived in detail through Lagrange equation. Then, the orbital dynamics of the satellite is established by using coordinate transformation, through which the specific expressions of Coriolis force and centrifugal force are obtained. Finally, the influence of the momentum wheel, solar array drive assembly (SADA), and attitude adjustment of the satellite on the micro-vibration of the payloads is studied via numerical analysis. The responses of the payloads and corresponding transferring route of micro-vibration under different conditions are analyzed, which provides a theoretical reference for the subsequent micro-vibration suppression.