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Single-Gimbal CMGを用いた宇宙機の姿勢制御
https://jaxa.repo.nii.ac.jp/records/7392
https://jaxa.repo.nii.ac.jp/records/73925adfe5b8-a24e-4139-a112-dec7a65adf0c
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | Single-Gimbal CMGを用いた宇宙機の姿勢制御 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Spacecraft Attitude Control Using a Single-Gimbal CMG | |||||
著者 |
高塚, 直樹
× 高塚, 直樹× 山田, 克彦× Takatsuka, Naoki× Yamada, Katsuhiko |
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著者所属 | ||||||
名古屋大学大学院工学研究科航空宇宙工学専攻 | ||||||
著者所属 | ||||||
名古屋大学大学院工学研究科航空宇宙工学専攻 | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aerospace Engineering, Graduate School of Engineering, Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Department of Aerospace Engineering, Graduate School of Engineering, Nagoya University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
アストロダイナミクスシンポジウム講演後刷り集 en : Proceedings of 18th workshop on JAXA Astrodynamics and flight mechanics 巻 2008, 発行日 2009-03 |
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会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Symposium on Flight Mechanics and Astrodynamics 2008 (July 28-29, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 近年,地球観測衛星や科学観測衛星に対する高精度な高速姿勢マヌーバの要求を満たすため,コントロール・モーメント・ジャイロ(CMG)が注目されている.そこで今回の内容は一台のSingle-Gimbal CMGを用いて宇宙機の姿勢制御を行う.慣性空間における全角運動量が保存される拘束があるため任意の姿勢へ変更することはできない.しかしその拘束を満たせばある特定の姿勢へは変更可能である.そこで本稿ではその拘束についての考察を行ない,修正Rodriguezパラメータを用いた制御則を提案する. | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In order to satisfy the demand for precise and rapid attitude maneuver, Control Moment Gyros (CMGs) have attracted much attention in recent years. In this study, spacecraft attitude control using a singlegimbal CMG is considered. Because the total angular momentum of the spacecraft is conserved in the inertial space, an arbitrary attitude change cannot be achieved. However, some particular attitude changes are possible if the angular momentum constraint is satisfied. Therefore, we consider the possible attitude change of the spacecraft, and propose a simple control law using the modified Rodriguez parameters. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11567475 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064733018 |