Sliding mode attitude tracking of rigid spacecraft with disturbances

被引：144
作者：
Lu, Kunfeng [1 ]
Xia, Yuanqing [1 ]
Zhu, Zheng [1 ]
Basin, Michael V. [2 ]
机构：
[1] Beijing Inst Technol, Sch Automat, Beijing 100081, Peoples R China
[2] Autonomous Univ Nuevo Leon, Dept Phys & Math Sci, San Nicolas De Los Garza, Nuevo Leon, Mexico
来源：
JOURNAL OF THE FRANKLIN INSTITUTE-ENGINEERING AND APPLIED MATHEMATICS | 2012年 / 349卷 / 02期
基金：
中国国家自然科学基金;
关键词：
VARIABLE-STRUCTURE CONTROL; FLEXIBLE SPACECRAFT; NONLINEAR-SYSTEMS; ROBUST-CONTROL; STABILIZATION; REJECTION; CONTROLLER; GUIDANCE;
D O I：
10.1016/j.jfranklin.2011.07.019
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
The attitude tracking control problem of a spacecraft nonlinear model with external disturbances and inertia uncertainties is addressed in this paper. First, a new sliding mode controller is designed to ensure the asymptotic convergence of the attitude and angular velocity tracking errors against external disturbances and inertia uncertainties by using a modified differentiator to estimate the total disturbances. Second, an adaptive algorithm is applied to compensating the disturbances, by which another sliding mode controller is successfully designed to achieve a high performance on the attitude tracking in the presence of the inertia uncertainties, external disturbances and actuator saturations. Finally, simulation results are presented to illustrate effectiveness of the control strategies. (c) 2011 The Franklin Institute. Published by Elsevier Ltd. All rights reserved.
引用
收藏
页码：413 / 440
页数：28
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