Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls

Rahul Misra; Rafał Wisniewski; Alexander Zuyev

doi:10.3390/aerospace9080444

Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls

Rahul Misra^*, Rafał Wisniewski, Alexander Zuyev

^*Corresponding author for this work

Research output: Contribution to journal › Journal article › Research › peer-review

5 Citations (Scopus)

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Abstract

We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such a satellite is not fully actuated, as the control torque is the cross-product of magnetic moment due to magnetorquers and the geomagnetic field. The aim of this work is to study whether oscillating controls can be designed such that a satellite actuated via magnetorquers alone can achieve full three-axis control irrespective of the position of the satellite. To this end, we propose considering oscillating feedback controls which generate the motion of the closed-loop system in the direction of appropriate Lie brackets. Simulation studies show that the proposed control scheme is able to stabilize the considered system.

Original language	English
Article number	444
Journal	Aerospace
Volume	9
Issue number	8
DOIs	https://doi.org/10.3390/aerospace9080444
Publication status	Published - Aug 2022

Bibliographical note

Funding Information:
The first and the second author were supported by the Poul Due Jensen Foundation (Grundfos Foundation) under the project SWIfT, and the third author was supported by the German Research Foundation (DFG) under Grant ZU 359/2-1.

Publisher Copyright:
© 2022 by the authors.

Keywords

Lie brackets
magnetorquers
oscillating controls
stabilization

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10.3390/aerospace9080444Licence: CC BY 4.0

Open Access articleFinal published version, 3.8 MBLicence: CC BY 4.0

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Cite this

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title = "Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls",

abstract = "We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such a satellite is not fully actuated, as the control torque is the cross-product of magnetic moment due to magnetorquers and the geomagnetic field. The aim of this work is to study whether oscillating controls can be designed such that a satellite actuated via magnetorquers alone can achieve full three-axis control irrespective of the position of the satellite. To this end, we propose considering oscillating feedback controls which generate the motion of the closed-loop system in the direction of appropriate Lie brackets. Simulation studies show that the proposed control scheme is able to stabilize the considered system.",

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note = "Funding Information: The first and the second author were supported by the Poul Due Jensen Foundation (Grundfos Foundation) under the project SWIfT, and the third author was supported by the German Research Foundation (DFG) under Grant ZU 359/2-1. Publisher Copyright: {\textcopyright} 2022 by the authors.",

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AU - Zuyev, Alexander

N1 - Funding Information: The first and the second author were supported by the Poul Due Jensen Foundation (Grundfos Foundation) under the project SWIfT, and the third author was supported by the German Research Foundation (DFG) under Grant ZU 359/2-1. Publisher Copyright: © 2022 by the authors.

PY - 2022/8

Y1 - 2022/8

N2 - We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such a satellite is not fully actuated, as the control torque is the cross-product of magnetic moment due to magnetorquers and the geomagnetic field. The aim of this work is to study whether oscillating controls can be designed such that a satellite actuated via magnetorquers alone can achieve full three-axis control irrespective of the position of the satellite. To this end, we propose considering oscillating feedback controls which generate the motion of the closed-loop system in the direction of appropriate Lie brackets. Simulation studies show that the proposed control scheme is able to stabilize the considered system.

AB - We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such a satellite is not fully actuated, as the control torque is the cross-product of magnetic moment due to magnetorquers and the geomagnetic field. The aim of this work is to study whether oscillating controls can be designed such that a satellite actuated via magnetorquers alone can achieve full three-axis control irrespective of the position of the satellite. To this end, we propose considering oscillating feedback controls which generate the motion of the closed-loop system in the direction of appropriate Lie brackets. Simulation studies show that the proposed control scheme is able to stabilize the considered system.

KW - Lie brackets

KW - magnetorquers

KW - oscillating controls

KW - stabilization

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ER -

Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls

Abstract

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Keywords

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Attitude Stabilization of a Satellite Having Only Electromagnetic Actuation Using Oscillating Controls

Abstract

Bibliographical note

Keywords

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AUB Link

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Fingerprint

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SWIFT

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