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An almost disturbance decoupling solution of the attitude control problem

An almost disturbance decoupling solution of the attitude control problem Purpose – The purpose of this paper is to derive a robust nonlinear attitude control law intended for practical application. Design/methodology/approach – The method of input/output feedback linearization is utilized for having a linear model and a recently developed almost disturbance decoupling (ADD) approach is adopted for designing a robust satellite attitude control (SAC) system. The kinematics of the satellite is modeled by modified Rodriguez parameters because of their continuous invertibility. The design is simulated on the model of a realistic satellite project (BILSAT‐I), which is developed by the Turkish Scientific and Technological Research Council. Findings – The torque requirement of the operation does not exceed the maximum limit provided by the actuator. The square error levels are staying under the boundary of final global attractor, which is one of the important proofs for the successful operation of the generated ADD control law. Originality/value – The ADD concept is investigated on SAC problem. By that way, simple control structures with known disturbance attenuation capability can be designed. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

An almost disturbance decoupling solution of the attitude control problem

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Publisher
Emerald Publishing
Copyright
Copyright © 2008 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022660810873728
Publisher site
See Article on Publisher Site

Abstract

Purpose – The purpose of this paper is to derive a robust nonlinear attitude control law intended for practical application. Design/methodology/approach – The method of input/output feedback linearization is utilized for having a linear model and a recently developed almost disturbance decoupling (ADD) approach is adopted for designing a robust satellite attitude control (SAC) system. The kinematics of the satellite is modeled by modified Rodriguez parameters because of their continuous invertibility. The design is simulated on the model of a realistic satellite project (BILSAT‐I), which is developed by the Turkish Scientific and Technological Research Council. Findings – The torque requirement of the operation does not exceed the maximum limit provided by the actuator. The square error levels are staying under the boundary of final global attractor, which is one of the important proofs for the successful operation of the generated ADD control law. Originality/value – The ADD concept is investigated on SAC problem. By that way, simple control structures with known disturbance attenuation capability can be designed.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: May 16, 2008

Keywords: Systems and control theory; Space technology; Artificial satellites; Turkey

References