Attitude Tracking Control of Rigid Spacecraft With Actuator Misalignment and Fault

被引：66

作者：

Xiao, Bing ^{[1
]}

Hu, Qinglei ^{[1
]}

Wang, Danwei ^{[2
]}

Poh, Eng Kee ^{[3
]}

机构：

[1] Harbin Inst Technol, Dept Control Sci & Engn, Harbin 150001, Peoples R China

[2] Nanyang Technol Univ, Sch Elect & Elect Engn, Singapore 639798, Singapore

[3] DSO Natl Labs, Singapore 118230, Singapore

来源：

IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY | 2013年 / 21卷 / 06期

基金：

中国国家自然科学基金;

关键词：

Actuator fault; attitude tracking; finite-time; misalignment; spacecraft; TOLERANT CONTROL; SATELLITE; DESIGN; ROBUST; VELOCITY; SYSTEMS;

D O I：

10.1109/TCST.2012.2237403

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

A control scheme is developed to address the attitude tracking problem of a rigid spacecraft. A sufficient condition to accommodate actuator misalignment is presented. The controller asymptotically stabilizes the closed- loop attitude tracking system. The desired attitude trajectories can be tracked in finite time, even in the presence of uncertain inertia tensor, external disturbances, actuator fault, and actuator misalignment. The attitude tracking performance of the controller is evaluated through an illustrative example.

引用

页码：2360 / 2366

页数：7

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