Abstract
A control strategy combining the analytical solution of the dynamics and the controller design is proposed for solving the problem of star attitude stabilization during the deployment process of a three-body tethered satellite system. By applying averaging methods to the dynamic equations governing subsatellite attitude oscillations in a three-body tethered satellite system,analytical solutions for end satellites attitude oscillations are obtained,laying the groundwork for controller design. A sliding mode control law is developed based on the simplified dynamic equations to suppress subsatellite attitude oscillations,and the stability of the closed-loop system is theoretically proven using Lyapunov theory. The feasibility and effectiveness of the proposed method are validated through simulation experiments. Simulation results not only affirm the accuracy of the theoretical analytical solutions but also validate the efficacy of the controller.
| Translated title of the contribution | Attitude Control of End Satellites in the Three-body Tethered System Based on the Averaging Method |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 1261-1268 |
| Number of pages | 8 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 45 |
| Issue number | 8 |
| DOIs | |
| State | Published - Aug 2024 |