Finite-time output feedback attitude tracking control for rigid spacecraft

被引：0

作者：

Zong Q. ^{[1
]}

Shao S. ^{[1
]}

Zhang X. ^{[1
]}

Wang D. ^{[1
]}

Liu W. ^{[2
]}

机构：

[1] School of Electrical Engineering and Automation, Tianjin University, Tianjin

[2] Beijing Institute of Control Engineering, Beijing

来源：

Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology | 2017年 / 49卷 / 09期

关键词：

Attitude tracking; Disturbance observer; Output feedback; Sliding mode control; State observer;

D O I：

10.11918/j.issn.0367-6234.201612060

中图分类号：

学科分类号：

摘要：

To improve the reliability of spacecraft system, this paper researches the finite-time output feedback attitude tracking control for rigid spacecraft without angular velocity measurement. The attitude derivative is firstly viewed as an unknown state, and a modified adaptive super-twisting sliding mode state observer is designed and the requirement for the upper bound of unknown state is avoided. By extending dimensions of attitude kinematics equation, the precise angular velocity was estimated in finite time. Then, considering environmental disturbances and system uncertainties, and combining a continuous adaptive approach for estimating the upper bound of system uncertainties, a novel finite-time disturbance observer was designed. Based on the terminal sliding mode, a continuous finite-time attitude tracking controllers is also designed. The control chattering is greatly reduced and the finite-time stability for the observer and the controller is proved via the Lyapunov theory. Finally, simulation results illustrate the effectiveness of the proposed method. © 2017, Editorial Board of Journal of Harbin Institute of Technology. All right reserved.

引用

页码：136 / 143

页数：7

共 21 条

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