Please use this identifier to cite or link to this item:
Scopus Web of Science® Altmetric
Type: Journal article
Title: Attitude stabilization of spacecrafts under actuator saturation and partial loss of control effectiveness
Author: Xiao, B.
Hu, Q.
Shi, P.
Citation: IEEE Transactions on Control Systems Technology, 2013; 21(6):2251-2263
Publisher: IEEE-Inst Electrical Electronics Engineers Inc
Issue Date: 2013
ISSN: 1063-6536
Statement of
Bing Xiao, Qinglei Hu, and Peng Shi
Abstract: A practical solution is presented to the problem of fault tolerant attitude stabilization for a rigid spacecraft by using feedback from attitude orientation only. The attitude system, represented by modified Rodriguez parameters, is considered in the presence of external disturbances, uncertain inertia parameters, and actuator saturation. A low-cost control scheme is developed to compensate for the partial loss of actuator effectiveness fault. The derived controller not only has the capability to protect the control effort from actuator saturation but also guarantees all the signals in the closed-loop system to be uniformly ultimately bounded. Another feature of the approach is that the implementation of the controller does not require any rate sensor to measure angular velocity. An example is included to verify those highly desirable features in comparison with the conventional velocity-free control strategy.
Keywords: Actuator saturation
attitude stabilization
fault tolerant control (FTC)
uniformly ultimately bounded
velocity free
Rights: © 2013 IEEE
DOI: 10.1109/TCST.2012.2236327
Published version:
Appears in Collections:Aurora harvest
Electrical and Electronic Engineering publications

Files in This Item:
There are no files associated with this item.

Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.