Attitude Tracking of Rigid Spacecraft With Bounded Disturbances
Attitude Tracking of Rigid Spacecraft With Bounded Disturbances
复制标题
具有有限扰动的刚性航天器姿态跟踪
DOI：
10.1109/tie.2010.2046611
复制
发表时间：
2011-02-01
影响因子：
7.7
通讯作者：
Wang, Shuo
中科院分区：
文献类型：
--
作者：
Xia, Yuanqing;Zhu, Zheng;Wang, Shuo
The problem of attitude control for a spacecraft model that is nonlinear in dynamics with inertia uncertainty and external disturbance has been investigated. Adaptive law and extended state observer are applied to estimate the disturbance, by which sliding-mode controllers are designed to combine the two approaches in order to force the state variables of the closed-loop system to converge to the reference attitude states. Also, simulation results are presented to illustrate the effectiveness of the control strategies.
