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High-precision controller using LMI method for three-axis flexible satellite attitude stabilisation

Published online by Cambridge University Press:  07 February 2023

B.J. Eddine Open the ORCID record for B.J. Eddine [Opens in a new window] ,
K. Boulanouar Open the ORCID record for K. Boulanouar [Opens in a new window]  and
B. Elhassen
B.J. Eddine*
Affiliation:
Centre de développement des satellites, Algerian Space Agency, Bir El Djir 31130 Oran, Algeria
K. Boulanouar
Affiliation:
Centre de développement des satellites, Algerian Space Agency, Bir El Djir 31130 Oran, Algeria
B. Elhassen
Affiliation:
Centre de développement des satellites, Algerian Space Agency, Bir El Djir 31130 Oran, Algeria
*
*Corresponding author. Email: [email protected]
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Abstract

This paper considers the problem of a three-axis flexible satellite attitude stabilisation subject to the vibration of flexible appendages and external environmental disturbances, which affect the rigid body motion. To solve this problem, a disturbance observer is proposed to estimate and thereby reject the flexible appendage vibration. Based on the H∞ and Linear Matrix Inequality (LMI) approach, a controller for spacecraft with flexible appendages is proposed to ensure robustness as well as attitude stability with high precision. Stability analysis of the overall closed-loop system is provided via the Lyapunov method. The simulation results of three-axis flexible spacecraft demonstrate the robustness and effectiveness of the proposed method.

Keywords

Flexible spacecraftDisturbance observerAttitude controlLinear matrix inequalitiesH∞ control
Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1314 , August 2023 , pp. 1308 - 1319
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Copyright
© The Author(s), 2023. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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