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Attitude maneuver planning and robust tracking control for flexible satellite

Published online by Cambridge University Press:  18 March 2024

L. Sun Open the ORCID record for L. Sun [Opens in a new window] ,
S. Duan Open the ORCID record for S. Duan [Opens in a new window] ,
H. Huang ,
T. Zhang Open the ORCID record for T. Zhang [Opens in a new window]  and
X. Zhao
L. Sun*
Affiliation:
School of Astronautics, Beihang University, Beijing 100191, P.R. China
S. Duan
Affiliation:
School of Astronautics, Beihang University, Beijing 100191, P.R. China
H. Huang
Affiliation:
School of Astronautics, Beihang University, Beijing 100191, P.R. China
T. Zhang
Affiliation:
School of Astronautics, Beihang University, Beijing 100191, P.R. China
X. Zhao
Affiliation:
Institute of Remote Sensing Satellite, China Academy of Space Technology, Beijing 100191, P.R. China
*
Corresponding author: L. Sun; Email: sunliang@buaa.edu.cn
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Abstract

In this paper, we investigate the attitude manoeuver planning and tracking control of the flexible satellite equipped with a coilable mast. Due to its flexible beamlike structure, the coilable mast experiences bending and torsional modal vibrations in multi-direction. The complex nonlinear coupling and other external disturbances significantly impact the achievement of high-precision attitude control. To overcome these challenges, a robust attitude tracking controller is proposed for easy implementation by the Attitude Determination and Control System (ADCS). The controller consists of a disturbance compensator, feedforward controller and output feedback controller. The compensator, based on a Nonlinear Disturbance Observer (NDO), effectively compensates for the cluster disturbances caused by vibrations, environmental factors and parameter perturbations. The feedforward controller tracks the desired path in the nominal satellite model. Furthermore, the output feedback controller enables large-angle manoeuver control of the satellite and evaluates the suppression effect of the controlled output on the observation error of cluster disturbances used the ${L_2}$-gain. Simulation results demonstrate that the proposed controller successfully achieves high-precision attitude tracking control during large-angle manoeuvering.

Keywords

Flexible spacecraftAttitude maneuverNonlinear L2-gain controlSum of squares
Type
Research Article
Information
The Aeronautical Journal , Volume 128 , Issue 1328 , October 2024 , pp. 2374 - 2392
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Copyright
© The Author(s), 2024. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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