Nonsingular Integral Sliding Mode Attitude Control for Rigid-Flexible Coupled Spacecraft with High-Inertia Rotating Appendages

This study addresses the challenge of attitude tracking control for a rigid-flexible spacecraft with high-inertia rotating appendages. The Lagrange method was used to establish the kinematic and dynamic models of the spacecraft. The translation and rotation of the spacecraft, vibrations of solar pan...

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Published in:Complexity (New York, N.Y.) N.Y.), 2021, Vol.2021 (1)
Main Authors: Zhang, Gaowang, Chen, Xueqin, Xi, Ruichen, Li, Huayi
Format: Article
Language:English
Subjects:
Accuracy
Angular velocity
Appendages
Control algorithms
Control methods
Control theory
Controllers
Design
Dynamic models
Dynamical systems
Flexible spacecraft
Inertia
Integrals
Methods
Rotation
Sliding mode control
Solar panels
Spacecraft attitude control
Spacecraft tracking
Tracking control
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cited_by cdi_FETCH-LOGICAL-c403t-b7386e44474060a3a4db20fa7216f082b387eeffe46acfc6abb4390c10c399e73
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container_title Complexity (New York, N.Y.)
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creator Zhang, Gaowang
Chen, Xueqin
Xi, Ruichen
Li, Huayi
description This study addresses the challenge of attitude tracking control for a rigid-flexible spacecraft with high-inertia rotating appendages. The Lagrange method was used to establish the kinematic and dynamic models of the spacecraft. The translation and rotation of the spacecraft, vibrations of solar panels, and imbalance caused by the rotating appendages, which cause a complex control problem, were considered. To address the complex control problem, a novel, fast nonsingular integral sliding mode control method is proposed to perform the attitude tracking function of spacecraft. A sliding mode control law was established for the high-inertia appendages to maintain an appropriate angular velocity during rotation. Finally, the effectiveness of the proposed attitude control law was verified by numerical simulations for a spacecraft with high-inertia rotating appendages and symmetrical flexible solar panels.
doi_str_mv 10.1155/2021/8812187
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Finally, the effectiveness of the proposed attitude control law was verified by numerical simulations for a spacecraft with high-inertia rotating appendages and symmetrical flexible solar panels.</description><identifier>ISSN: 1076-2787</identifier><identifier>EISSN: 1099-0526</identifier><identifier>DOI: 10.1155/2021/8812187</identifier><language>eng</language><publisher>Hoboken: Hindawi</publisher><subject>Accuracy ; Angular velocity ; Appendages ; Control algorithms ; Control methods ; Control theory ; Controllers ; Design ; Dynamic models ; Dynamical systems ; Flexible spacecraft ; Inertia ; Integrals ; Methods ; Rotation ; Sliding mode control ; Solar panels ; Spacecraft attitude control ; Spacecraft tracking ; Tracking control</subject><ispartof>Complexity (New York, N.Y.), 2021, Vol.2021 (1)</ispartof><rights>Copyright © 2021 Gaowang Zhang et al.</rights><rights>Copyright © 2021 Gaowang Zhang et al. 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subjects Accuracy
Angular velocity
Appendages
Control algorithms
Control methods
Control theory
Controllers
Design
Dynamic models
Dynamical systems
Flexible spacecraft
Inertia
Integrals
Methods
Rotation
Sliding mode control
Solar panels
Spacecraft attitude control
Spacecraft tracking
Tracking control
title Nonsingular Integral Sliding Mode Attitude Control for Rigid-Flexible Coupled Spacecraft with High-Inertia Rotating Appendages
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