{"created":"2023-06-20T14:40:37.423722+00:00","id":7541,"links":{},"metadata":{"_buckets":{"deposit":"49a4fe0a-e027-4453-abb3-f73e15a1342b"},"_deposit":{"created_by":1,"id":"7541","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"7541"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00007541","sets":["1543:1544:1557","1887:1891"]},"author_link":["40327","40324","40328","40323","40325","40326"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"コントロール・モーメント・ジャイロ搭載衛星による高速多点指向ミッションのための姿勢制御則"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"236","bibliographicPageStart":"231","bibliographic_titles":[{"bibliographic_title":"第16回アストロダイナミクスシンポジウム講演後刷り集　2006"},{"bibliographic_title":"Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics","bibliographic_titleLang":"en"}]}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"観測衛星により多点指向制御を行う場合、姿勢変更の高速化と姿勢変更直後の高安定化の両性能が求められる。コントロール・モーメント・ジャイロ(CMG: Control Moment Gyro)は、大トルクを発生可能であることから高速姿勢変更に効果的である。しかし、多体系特有の干渉トルクやジンバルレート誤差による制御トルク誤差などが大きな外乱源となり、高安定化の妨げとなる。本論文では、CMGの角運動量制御型内力補償法を提案する。本手法は、通常のジンバル用サーボ系に、CMGの角運動量を制御するループを付加することにより、低計算負荷で効果的に内力補償を行うものである。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Both of high attitude maneuverability and stability are required for a spacecraft to realize a multitarget pointing mission. Control Moment Gyros (CMGs) are effective to obtain the high attitude maneuverability because they can generate large torques. On the other hand, the attitude stability is degraded by inner torques caused by the CMG particular dynamics such as multibody dynamics coupling, gimbal rate control error, and so on. In this paper, an angular momentum based inner torque compensation method is proposed. In this method, a CMG angular momentum control loop is added to the general gimbal servo system. As results, inner torques are compensated efficiently with low computation cost.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063481040","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構宇宙科学研究本部"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"愛媛大学"},{"subitem_text_value":"宇宙航空研究開発機構"},{"subitem_text_value":"慶應義塾大学"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Ehime University"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency"},{"subitem_text_language":"en","subitem_text_value":"Keio University"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"metadata only access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_14cb"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"谷脇, 滋宗"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"遠藤, 達也"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高橋, 正樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Taniwaki, Shigemune","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Endo, Tatsuya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takahashi, Masaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"姿勢制御","subitem_subject_scheme":"Other"},{"subitem_subject":"コントロール・モーメント・ジャイロスコープ","subitem_subject_scheme":"Other"},{"subitem_subject":"制御理論","subitem_subject_scheme":"Other"},{"subitem_subject":"衛星制御","subitem_subject_scheme":"Other"},{"subitem_subject":"変更性能","subitem_subject_scheme":"Other"},{"subitem_subject":"多点指向ミッション","subitem_subject_scheme":"Other"},{"subitem_subject":"CMG","subitem_subject_scheme":"Other"},{"subitem_subject":"制御則","subitem_subject_scheme":"Other"},{"subitem_subject":"角運動量","subitem_subject_scheme":"Other"},{"subitem_subject":"角速度","subitem_subject_scheme":"Other"},{"subitem_subject":"角加速度","subitem_subject_scheme":"Other"},{"subitem_subject":"ジンバル","subitem_subject_scheme":"Other"},{"subitem_subject":"制御シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"attitude control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control moment gyroscope","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control theory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"satellite control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"maneuverability","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"multitarget pointing mission","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CMG","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control law","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angular momentum","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angular velocity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angular acceleration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"gimbal","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Attitude control law of spacecraft with control moment gyros for rapid multitarget pointing mission","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Attitude control law of spacecraft with control moment gyros for rapid multitarget pointing mission","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1557","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"7541","relation_version_is_last":true,"title":["Attitude control law of spacecraft with control moment gyros for rapid multitarget pointing mission"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T07:37:54.806689+00:00"}