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Design and functional model of CMG system for agile attitude maneuver of 20 kg-class microsatellite
https://jaxa.repo.nii.ac.jp/records/7597
https://jaxa.repo.nii.ac.jp/records/75974aad13b6-5fce-4dfe-9225-35105a59bd86
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Design and functional model of CMG system for agile attitude maneuver of 20 kg-class microsatellite | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | コントロールモーメントジャイロ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CMG | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 可変速度CMG | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | VS-CMG | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 小型化 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 姿勢制御 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超小型衛星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ジャイロスコープ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | リアクションホイール | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ジンバル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 制御系設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 光ファイバジャイロ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 地上実験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 制御シミュレーション | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | control moment gyro | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CMG | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Variable Speed CMG | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | VS-CMG | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | miniaturization | |||||
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 | microsatellite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | gyroscope | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reaction wheel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | gimbal | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | control system design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | fiber optic gyro | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ground experiment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | control simulation | |||||
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 | ||||||
その他のタイトル | 20kg級超小型衛星の迅速姿勢制御用CMGシステムの設計と試作 | |||||
著者 |
尾曲, 邦之
× 尾曲, 邦之× 臼田, 武史× 松永, 三郎× Omagari, Kuniyuki× Usuda, Takeshi× Matsunaga, Saburo |
|||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
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/ISAS) | |||||
書誌情報 |
第15回アストロダイナミクスシンポジウム講演後刷り集 2005 en : Proceedings of 15th Workshop on JAXA Astrodynamics and Flight Mechanics p. 204-209, 発行日 2006-03 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 小型衛星が持つ迅速姿勢制御の可能性をさらに強化するための姿勢制御装置として、コントロールモーメントジャイロ(CMG: Control Moment Gyro)を採用し、小型化に関する定量的な検討、および駆動則の設計を行った。20kg級超小型衛星による突発的な天文現象観測ミッションへの応用を目指し、ピラミッド型CMGクラスタの試験モデルを開発し、3次元姿勢動力学シミュレータを用いて地上実験を行った。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | For the agile maneuver missions of micro-satellites, Control Moment Gyros (CMGs) will meet the necessary requirements because a small gimbal torque input produces a large torque output. However, CMG has some difficulties in designing and control algorithm. Here, a simplified method to calculate appropriate output torque for 20 kg class astronomy satellite is introduced and experimentally evaluated using a test model of pyramid cluster of 4 CMGs and a 3-DOF (Degree Of Freedom) attitude dynamics simulator. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063480032 |