Abstract: Aiming at the on-orbit satellite disturbance phenomenon induced by solar arrays, this paper performs optimal design from both structural simulation and control system perspectives to improve satellite attitude stability. In terms of structure, a satellite vibration model is established, and the Lagrange equation is applied to analyze the system vibration characteristics, clarify the mechanism of satellite vibration excited by solar arrays, and propose a structural optimization design scheme. In the control aspect, combined with the coupled dynamic model of the satellite bus and solar arrays, the attitude PID control law is adopted for simulation. The control system bandwidth is analyzed based on the simulation results, and optimal tuning of the control parameters is implemented. Finally, verification is conducted using on-orbit satellite data. The results demonstrate that the satellite dynamic model can basically reproduce the on-orbit jitter phenomenon of the satellite. The optimized control parameters significantly enhance the satellite stability, suppress the vibration of the satellite caused by solar array disturbances in orbit, and improve the satellite control stability by 1–2 orders of magnitude.

Key words: solar array disturbances, high stability, attitude control, attitude dynamics, optimal design method