Robust Nonlinear Attitude Tracking for Rigid Spacecraft with Constrained Control Inputs

被引：0
|
作者：
Sun, Liang [1 ]
Zhu, Bing [2 ]
机构：
[1] Univ Sci & Technol Beijing, Sch Automat & Elect Engn, Beijing 100083, Peoples R China
[2] Beihang Univ, Sch Automat Sci & Elect Engn, Res Div 7, Beijing 100191, Peoples R China
来源：
2018 3RD IEEE INTERNATIONAL CONFERENCE ON ADVANCED ROBOTICS AND MECHATRONICS (IEEE ICARM) | 2018年
关键词：
SLIDING-MODE CONTROL; VARIABLE-STRUCTURE CONTROL; BACKSTEPPING CONTROL; CONTROL DESIGN; STABILIZATION; SATELLITE; DYNAMICS;
D O I：
暂无
中图分类号：
TP3 [计算技术、计算机技术];
学科分类号：
0812 ;
摘要：
A robust nonlinear attitude tracking controller for rigid spacecraft subject to constrained control inputs and modeling uncertainties is proposed in this paper. Control input constraint in the controller is guaranteed by using continuously differentially hyperbolic tangent function and bounded properties of attitude parameters. The spacecraft inertia parametric uncertainties and bounded external disturbances are attenuated by bounded robust control term. It is proved via Lyapunov method that attitude tracking errors in closed-loop system are all uniformly ultimately bounded. The numerical simulation is presented to demonstrate the controller performance.
引用
收藏
页码：225 / 229
页数：5
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