Finite-time Control of Satellites Formation[-1.5mm] Based on Terminal Sliding Mode
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摘要: 针对考虑参考星机动的编队飞行相对位置控制问题，给出了一种基于终端滑模的有限时间控制方法. 基于编队卫星相对运动动力学模型，设计了有限时间终端滑模控制器，同时证明了该控制器作用下系统状态误差可在有限时间内收敛. 以编队构型重构和考虑参考星机动时的构型保持控制为例，利用本文控制方法进行了仿真分析. 仿真结果表明，基于终端滑模的有限时间控制方法相比于传统的线性滑模控制方法，在保证编队飞行控制高精度的同时，有效提升了误差的收敛速度，验证了该方法的有效性和优越性.Abstract: Aiming at the relative control problem of reference satellite maneuver-considered formation flying, a finite-time control method based on terminal sliding mode (TSM) is given. Based on the dynamic model of formation satellites relative motion, a finite-time terminal sliding controller is designed, and it is proven that the system state error can converge in finite time under the controller. Lastly, the formation reconfiguration and the formation keeping considering reference satellite maneuver are simulated and analyzed with the control method. The results show that the finite-time control method based on terminal sliding mode has higher formation control precision as well as faster error convergence speed compared with the traditional linear sliding mode.
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