Quasi-static panel deployment and retraction using electromagnetic force in satellite missions

This paper proposes a novel control technique for a new panel quasi-static deployment and retraction method using electromagnetic force. This panel system is modeled as a multibody dynamic system which will be used for numerical simulations. Although the electromagnetic deployment has various benefi...

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Autores principales:	Masashi TOMOOKA, Takaya INAMORI, Yoshiki SUGAWARA, Yasutaka SATOU, Ryu FUNASE, Shin-ichi NAKASUKA
Formato:	article
Lenguaje:	EN
Publicado:	The Japan Society of Mechanical Engineers 2017
Materias:	space engineering deployable structure retraction quasi-static electromagnetic force Mechanical engineering and machinery TJ1-1570
Acceso en línea:	https://doaj.org/article/21596e6525344e59bde19b68143fac71
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spelling	oai:doaj.org-article:21596e6525344e59bde19b68143fac712021-11-26T07:06:29ZQuasi-static panel deployment and retraction using electromagnetic force in satellite missions2187-974510.1299/mej.17-00049https://doaj.org/article/21596e6525344e59bde19b68143fac712017-08-01T00:00:00Zhttps://www.jstage.jst.go.jp/article/mej/4/4/4_17-00049/_pdf/-char/enhttps://doaj.org/toc/2187-9745This paper proposes a novel control technique for a new panel quasi-static deployment and retraction method using electromagnetic force. This panel system is modeled as a multibody dynamic system which will be used for numerical simulations. Although the electromagnetic deployment has various beneficial points, it still has a major technical issue that vibration on panels continues for a certain time, and hence its motion does not converge quickly. To eliminate or damp these vibrations, we propose both feed-forward and feedback control methods using magnetism generated by electronic current. These methods can successfully reduce convergence time of deployment motion by at most 60 percents. Additionally, to realize feedback control, it is required to estimate the state variables of panels, that is, the angle between the panels. For that purpose, we introduce a new approach to determine these angles by sensing electromagnetic field generated by the deployment system with a magnetometer. This new method accomplishes the determination of the angles between the panels to an accuracy of at worst four degrees and one degree on average.Masashi TOMOOKATakaya INAMORIYoshiki SUGAWARAYasutaka SATOURyu FUNASEShin-ichi NAKASUKAThe Japan Society of Mechanical Engineersarticlespace engineeringdeployable structureretractionquasi-staticelectromagnetic forceMechanical engineering and machineryTJ1-1570ENMechanical Engineering Journal, Vol 4, Iss 4, Pp 17-00049-17-00049 (2017)
institution	DOAJ
collection	DOAJ
language	EN
topic	space engineering deployable structure retraction quasi-static electromagnetic force Mechanical engineering and machinery TJ1-1570
spellingShingle	space engineering deployable structure retraction quasi-static electromagnetic force Mechanical engineering and machinery TJ1-1570 Masashi TOMOOKA Takaya INAMORI Yoshiki SUGAWARA Yasutaka SATOU Ryu FUNASE Shin-ichi NAKASUKA Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
description	This paper proposes a novel control technique for a new panel quasi-static deployment and retraction method using electromagnetic force. This panel system is modeled as a multibody dynamic system which will be used for numerical simulations. Although the electromagnetic deployment has various beneficial points, it still has a major technical issue that vibration on panels continues for a certain time, and hence its motion does not converge quickly. To eliminate or damp these vibrations, we propose both feed-forward and feedback control methods using magnetism generated by electronic current. These methods can successfully reduce convergence time of deployment motion by at most 60 percents. Additionally, to realize feedback control, it is required to estimate the state variables of panels, that is, the angle between the panels. For that purpose, we introduce a new approach to determine these angles by sensing electromagnetic field generated by the deployment system with a magnetometer. This new method accomplishes the determination of the angles between the panels to an accuracy of at worst four degrees and one degree on average.
format	article
author	Masashi TOMOOKA Takaya INAMORI Yoshiki SUGAWARA Yasutaka SATOU Ryu FUNASE Shin-ichi NAKASUKA
author_facet	Masashi TOMOOKA Takaya INAMORI Yoshiki SUGAWARA Yasutaka SATOU Ryu FUNASE Shin-ichi NAKASUKA
author_sort	Masashi TOMOOKA
title	Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
title_short	Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
title_full	Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
title_fullStr	Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
title_full_unstemmed	Quasi-static panel deployment and retraction using electromagnetic force in satellite missions
title_sort	quasi-static panel deployment and retraction using electromagnetic force in satellite missions
publisher	The Japan Society of Mechanical Engineers
publishDate	2017
url	https://doaj.org/article/21596e6525344e59bde19b68143fac71
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_version_	1718409705271853056

Quasi-static panel deployment and retraction using electromagnetic force in satellite missions

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