Attitude tracking control model design for rigid spacecrafts based on discrete-time sliding mode

被引：0

作者：

Wen, Weibin ^{[1
]}

Fu, Qiang ^{[1
]}

Wang, Fang ^{[1
]}

Xiao, Yuan ^{[1
]}

Wang, Tao ^{[2
]}

机构：

[1] Key Laboratory of Lunar and Deep Space Exploration, National Astronomical Observatories, Chinese Academy of Sciences, Beijing

[2] Huayun Shinetek Science and Technology Co., Ltd., Beijing

来源：

Harbin Gongye Daxue Xuebao/Journal of Harbin Institute of Technology | 2015年 / 47卷 / 03期

关键词：

Attitude tracking; Decoupling control; Discrete-time sliding mode control; Rigid spacecraft;

D O I：

10.11918/j.issn.0367-6234.2015.03.002

中图分类号：

学科分类号：

摘要：

In order to improve the robust performance to parametric perturbations and external environment disturbances for rigid spacecrafts, an attitude tracking controller based on the discrete-time sliding mode control principle is proposed. The spacecraft model is firstly modeled. Considering the time-varying and interfering moments and even disturbances, the system is then decoupled into independent discrete-time subsystems via the input-output feedback linearization. To this end, the discrete-time sliding mode attitude control law is designed from the exponential approach law. Simulation results indicate that the discrete-time control system proposed can ensure the attitude stabilization of rigid spacecrafts while realizing the decoupling control among channels. Moreover, the system is robust to the parametric perturbations and external disturbances and the attitude angle tracking errors can be reduced effectively. In addition, the tracking dynamic characteristics and the sampling period are validated for the system considered. ©, 2015, Harbin Institute of Technology. All right reserved.

引用

页码：8 / 14

页数：6

共 7 条

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