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Fault-Tolerant Attitude Control System for a Spacecraft with Control Moment Gyros Using Multi-Objective Optimization
https://jaxa.repo.nii.ac.jp/records/22570
https://jaxa.repo.nii.ac.jp/records/22570e4312d5e-70a1-4884-bc4e-6c8a148e59e3
名前 / ファイル | ライセンス | アクション |
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PA1510073000.pdf (828.7 kB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-08-27 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Fault-Tolerant Attitude Control System for a Spacecraft with Control Moment Gyros Using Multi-Objective Optimization | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Control Moment Gyros | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Spacecraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Attitude Control | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Multi-objective Optimization | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
著者 |
Noumi, Ai
× Noumi, Ai× Haruki, Misuzu× Kanzawa, Takuya× Takahashi, Masaki |
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著者所属(英) | ||||||
en | ||||||
Keio University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Keio University | ||||||
出版者(英) | ||||||
出版者 | The Science and Information Organization (SAI) | |||||
書誌情報 |
en : International Journal of Advanced Computer Science and Applications(IJACSA) 巻 6, 号 1, p. 40-48, 発行日 2015 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Recent years have seen a growing requirement for accurate and agile attitude control of spacecraft. To both quickly and accurately control the attitude of a spacecraft, Control Moment Gyros (CMGs) which can generate much higher torque than conventional spacecraft actuators are used as actuators of the spacecraft. The drive on the motors is needed for rapid maneuverability, negatively affecting their life. Thus, in designing spacecraft the conflicting requirements are rapid maneuverability and reduced the drive on motors. Furthermore, the attitude control system needs to be fault-tolerant. The dominant requirement is different for each spacecraft mission, and therefore the relationship between the requirements should be shown. In this study, a design method is proposed for the attitude control system, using multi objective optimization of the skew angle and parameters of the control system. Pareto solutions that can show the relationship between the requirements are obtained by optimizing the parameters. Through numerical analysis, the effect with fault-tolerance and parameter differences for the dominant requirement are confirmed and the method to guide for determining parameters of the attitude control system is established. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 2158-107X | |||||
DOI | ||||||
関連タイプ | isIdenticalTo | |||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.14569/IJACSA.2015.060106 | |||||
関連名称 | info:doi/10.14569/IJACSA.2015.060106 | |||||
権利 | ||||||
権利情報 | ©2015 by the authors; licensee The Science and Information (SAI). This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution license (http://creativecommons.org/licenses/by/4.0/). | |||||
著者版フラグ | ||||||
出版タイプ | VoR | |||||
出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: PA1510073000 |