{"created":"2023-06-20T14:40:28.216506+00:00","id":7354,"links":{},"metadata":{"_buckets":{"deposit":"2e2f2fe7-f492-434f-91b6-36f3d6b91739"},"_deposit":{"created_by":1,"id":"7354","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"7354"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00007354","sets":["1543:1544:1554","1887:1891"]},"author_link":["38923","38921","38922","38920"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"オイラー角を用いた宇宙機の姿勢追従制御"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2010-03","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"2009","bibliographic_titles":[{"bibliographic_title":"アストロダイナミクスシンポジウム講演後刷り集"},{"bibliographic_title":"Proceedings of 19th workshop on JAXA Astrodynamics and Flight Mechanics","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"アストロダイナミクスシンポジウム (2009年7月30-31日. 宇宙航空研究開発機構宇宙科学研究本部))","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"Workshop on JAXA Astrodynamics and Flight Mechanics, 2009 (July 30-31, 2009. Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"目標姿勢運動と現在の姿勢運動との相対運動方程式をオイラー角により表現し，その安定化制御を行うことにより，衛星の姿勢制御を行う．原点周りの線形化方程式に関し，システム行列の固有値を求め，エネルギー零収束原点可制御性を示す．線形化方程式に基づく線形制御および非線形方程式を用いた非線形制御の応答を比較する．評価関数は入力トルクのL(sub 1)ノルムとする．","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In future missions such as inspection, repair or removal of disabled spacecrafts, control of spacecraft attitude becomes an important issue. In particular, it is necessary to construct a new control strategy whereby we use less amount of energy to control spacecrafts. First, we derive and linearize equations of relative motion between the desired attitude motion and the present attitude motion, which are based on the Euler angle representation. We then design linear feedback controllers based on the linearized equations and nonlinear feedback controllers based on the feedback linearization. We consider the L(sub 1) norm of the feedback controllers as the main performance index, because it is proportional to fuel consumption.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064734049","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)"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA11567475","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"京都大学大学院工学研究科航空宇宙工学専攻"},{"subitem_text_value":"京都大学大学院工学研究科航空宇宙工学専攻"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University"},{"subitem_text_language":"en","subitem_text_value":"Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto 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":"大橋, 初美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"市川, 朗"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ohashi, Hatsumi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ichikawa, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"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 of a Satellite Based on Euler Angle Reprensentation","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Attitude Control of a Satellite Based on Euler Angle Reprensentation","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1554","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"7354","relation_version_is_last":true,"title":["Attitude Control of a Satellite Based on Euler Angle Reprensentation"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T07:40:48.902013+00:00"}