| 引用本文: | 朱庆华,董瑞琦,马广富.基于动态滑模控制的挠性航天器姿态控制[J].控制理论与应用,2018,35(10):1430~1435.[点击复制] |
| ZHU Qing-hua,DONG Rui-qi,MA Guang-fu.Dynamical sliding mode for flexible spacecraft attitude control[J].Control Theory and Technology,2018,35(10):1430~1435.[点击复制] |
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| 基于动态滑模控制的挠性航天器姿态控制 |
| Dynamical sliding mode for flexible spacecraft attitude control |
| 摘要点击 3242 全文点击 1312 投稿时间：2017-11-23 修订日期：2018-09-17 |
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| DOI编号 10.7641/CTA.2018.70863 |
| 2018,35(10):1430-1435 |
| 中文关键词 挠性航天器 姿态镇定 动态滑模 |
| 英文关键词 flexible spacecraft attitude stabilization dynamical sliding mode control |
| 基金项目 深圳市学科布局项目(JCYJ20170413112722597), 国家自然科学基金项目(61603111), 深圳市基础研究项目(JCYJ20170307150227897), 广东省自然科学基金项目(2017A030313340) 资助. |
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| 中文摘要 |
| 本文采用滑动模态控制方法对挠性航天器设计了姿态镇定控制律. 首先, 建立了挠性航天器的数学模型. 其中,
挠性航天器的运动学方程采用姿态四元数描述. 然后, 通过引入动态切换函数, 设计挠性航天器的动态滑模姿态控制律.
该控制律能对滑模姿态控制律中由符号函数项引起的抖振进行抑制. 采用Lyapunov方法证明了所设计的动态滑模姿态
控制律能使闭环航天器姿态系统稳定. 最后, 通过数值仿真例子验证了所提出方法的有效性. |
| 英文摘要 |
| In this paper, the sliding mode control technique is adopted to design attitude stable controllers for flexible spacecraft.
First, the mathematical model of the flexible spacecraft is constructed. The kinematic equation of the flexible spacecraft is
described by quaternion. Then, by introducing the dynamical switching function, an dynamical sliding mode control law
is proposed for the flexible spacecraft attitude control. The proposed dynamical sliding mode control law can suppress the
chattering raised by the sign function of the control law. Finally, a numerical example is employed to verify the effectiveness
of the presented control law. |
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