Attitude stabilization of rigid spacecraft with finite‐time convergence
Attitude stabilization of rigid spacecraft with finite‐time convergence
复制标题
DOI：
10.1002/rnc.1624
复制
发表时间：
2011-04
影响因子：
3.9
通讯作者：
Zhenglong Zhu;Yuanqing Xia;M. Fu
中科院分区：
文献类型：
--
作者：
Zhenglong Zhu;Yuanqing Xia;M. Fu
研究了具有惯性不确定性和外部干扰的航天器非线性动力学模型的姿态控制问题。提出了两种滑模控制器，以迫使闭环系统的状态变量在有限时间内收敛到原点。特别地，第二种控制设计包括对不确定性和干扰的自适应估计，从而有效地减少了不期望的抖振。仿真结果验证了控制策略的有效性。版权所有© 2010约翰威利父子有限公司.
The problem of attitude control for a spacecraft model which is nonlinear in dynamics with inertia uncertainty and external disturbance is investigated in this paper. Two sliding mode controllers are proposed to force the state variables of the closed‐loop system to converge to the origin in finite time. Specially, the second control design consists of the estimation of the uncertainty and disturbance by adaptive method and thus it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright © 2010 John Wiley & Sons, Ltd.