Influence of satellite control force on its flexible solar panel during orbit maneuver

The control force during satellite orbit maneuver may stimulate the vibration of the flexible solar panel. In this paper, we analyze the influence of the orbit control force on the satellite flexible solar panel. First, the kinematic relationship of the satellite is described. The reference frames and the angles between these frames are defined. The velocity of any point mass on the satellite is derived. Then, the dynamic model of the satellite with a large flexible solar panel is established using Lagrange equations. This dynamic model includes the orbit motion, the attitude motion of the satellite and the flexible vibration of the solar panel. After that, the influence of the orbit control force on the flexible panel is analyzed in detail. The coupling matrixes are calculated, and the dynamic coupling character between the flexible vibration modals and the motion of the satellite is studied. Finally, numerical simulation is carried out to analyze the dynamic character of the satellite during orbit maneuver. When the orbit control force is along the X direction of the satellite body and the solar panel is parallel to it, the control force stimulates in-plane vibration of the panel. The largest vibration modal coordinate is about 1 × 10^-2 m at first and then the vibration attenuates gradually due to the structure damping. This vibration affects the attitude of the satellite, and the largest angular velocity of the attitude is about 5 × 10^-3(°/s). When the solar panel is vertical to the orbit control force, the control force stimulates curving vibration of the panel. The largest vibration modal coordinate is about 0.12 m. This vibration also affects the attitude of the satellite, and the largest angular velocity of the attitude is about 0.02 (°/s). In this case, the orbit control force stimulates the flexible vibration more violently when the panel is vertical to it.