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Full Length Article | Open Access

Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method

Seyed Majid ESMAEILZADEH,( ), Mohammad Sadegh ZEYGHAMI
Department of Electrical Engineering, Iran University of Science and Technology, Narmak, Tehran 16846-13114, Iran

Peer review under responsibility of Editorial Committee of CJA.

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Abstract

A finite time attitude controller is designed for a flexible spacecraft based on a novel output redefinition method, in this paper. To make the flexible appendages vibration suppression effective, the appendage tip-point is selected as the output. First, a novel output redefinition method is proposed to overcome the non-minimum phase property of the dynamic model. The proposed method not only makes the system model minimum phase but also improves the attitude control system performance. Consequently, the precise attitude pointing and stabilization are achieved. Then, a nonlinear finite time H∞ controller is designed based on the backstepping approach. For the situation where the modal variables measurements are not available, a modal observer is also designed. The simulation results show the effectiveness of the proposed method in the presence of the model uncertainties and environmental disturbances.

Keywords

Attitude controlFlexible spacecraftRobustBacksteppingFinite timeOutput redefinitionH∞ control

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Chinese Journal of Aeronautics
Volume 36 Issue 11,
November 2023
Pages 373-385
DOI: 10.1016/j.cja.2023.08.001
Cite this article:
ESMAEILZADEH SM, ZEYGHAMI MS. Nonlinear finite time attitude control of flexible spacecraft based on a novel output redefinition method. Chinese Journal of Aeronautics, 2023, 36(11): 373-385. https://doi.org/10.1016/j.cja.2023.08.001

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Received: 06 November 2022
Revised: 25 December 2022
Accepted: 17 January 2023
Published: 09 August 2023
© 2023 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
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