Backstepping control for attitude tracking of the spacecraft under input saturation

被引：37
作者：
Guo, Yong [1 ]
Guo, Jin-hua [2 ]
Song, Shen-min [3 ]
机构：
[1] Northwestern Polytech Univ, Sch Automat, Xian 710072, Shaanxi, Peoples R China
[2] China Acad Launch Vehicle Technol, Res & Dev Ctr, Beijing 100000, Peoples R China
[3] Harbin Inst Technol, Ctr Control Theory & Guidance Technol, Harbin 150001, Heilongjiang, Peoples R China
来源：
ACTA ASTRONAUTICA | 2017年 / 138卷
基金：
中国国家自然科学基金;
关键词：
Finite-time stability; Input saturation; Rotation matrix; Backstepping control; Adaptive control; FORMATION FLYING SPACECRAFT; COORDINATION CONTROL; STABILIZATION; SYSTEMS;
D O I：
10.1016/j.actaastro.2017.06.002
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Finite-time control schemes without the drawback of unwinding are investigated by backstepping method for the spacecraft. The first finite-time controller is robust to external disturbances in which a novel virtual angular velocity is designed to avoid that the trace of the error rotation matrix equals to one. By using adaptive control, the second finite-time controller that can deal with input saturation is also robust to external disturbances. Theoretical analysis and numerical simulations are presented to prove the validity of the designed controllers.
引用
收藏
页码：318 / 325
页数：8
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