Finite time attitude control of double tethered satellites system in deep space

Chuanjiang Li, Junyu Yao, Bo Li, G. Ma
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引用次数: 1

Abstract

A finite time attitude control law incorporating a disturbance observer is proposed for double tethered satellites system (2-TSS) with a variable length tether in deep space. For each single tethered satellite, a disturbance observer combining with the theory of Extended State Observer (ESO) is firstly utilized to precisely estimate the synthesis of external bounded disturbances and parameter uncertainties. The stability of the observer is analyzed so that the observation errors are globally uniformly ultimately bounded and finally converge to a small neighborhood. Then to realize attitude control with high precision and fast response in finite time, a finite time attitude control law is proposed through designing a fast nonsingular sliding mode surface with a specific switching function. The Lyapunov stability analysis is performed to show that the system states are finite time stable and that the sliding mode surface can reach a small region of origin. Finally, numerical simulations demonstrate the effectiveness of proposed control schemes with disturbance observer.
深空双系绳卫星系统的有限时间姿态控制
针对深空变长系绳双系卫星系统(2-TSS),提出了一种包含扰动观测器的有限时间姿态控制律。针对单个系绳卫星,首先利用扰动观测器结合扩展状态观测器(ESO)理论对外部有界扰动和参数不确定性的综合进行精确估计。分析了观测器的稳定性,使观测误差全局一致最终有界,最终收敛到一个小邻域。然后,通过设计具有特定切换函数的快速非奇异滑模曲面,提出了一种有限时间姿态控制律,以实现有限时间内高精度、快速响应的姿态控制。通过Lyapunov稳定性分析表明,系统状态是有限时间稳定的,并且滑模表面可以到达一个小的原点区域。最后,通过数值仿真验证了所提扰动观测器控制方案的有效性。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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