Adaptive finite-time attitude stabilization for rigid spacecraft with actuator faults and saturation constraints

被引：60

作者：

Lu, Kunfeng ^{[1
,2
]}

Xia, Yuanqing ^{[3
]}

Fu, Mengyin ^{[3
]}

Yu, Chunmei ^{[1
,2
,4
]}

机构：

[1] Beijing Aerosp Automat Control Inst, Beijing 100854, Peoples R China

[2] Natl Key Lab Sci & Technol Aerosp Intelligent Con, Beijing 100854, Peoples R China

[3] Beijing Inst Technol, Sch Automat, Beijing 100081, Peoples R China

[4] Natl Univ Def Technol, Aerosp & Mat Engn, Changsha 410073, Hunan, Peoples R China

来源：

INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL | 2016年 / 26卷 / 01期

基金：

中国国家自然科学基金;

关键词：

finite-time control; fast terminal sliding mode control; adaptive control; attitude stabilization; actuator faults; TRACKING CONTROL; TOLERANT CONTROL; DESIGN;

D O I：

10.1002/rnc.3289

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 stabilization problem for rigid spacecraft in the presence of inertial uncertainties, external disturbances, actuator saturations, and actuator faults is addressed in this paper. First, a novel fast terminal sliding mode manifold is designed to avoid the singularity problem while providing high control ability. In addition, fast terminal sliding mode control laws are proposed to make the spacecraft system trajectory fast converge onto the fast terminal sliding mode surface and finally evolve into small region in finite time, which cannot be achieved by the previous literatures. Based on the real sliding mode context, a practical adaptive fast terminal sliding mode control law is presented to guarantee attitude stabilization in finite time. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright (C) 2015 John Wiley & Sons, Ltd.

引用

页码：28 / 46

页数：19

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