{"created":"2023-06-19T12:46:35.137155+00:00","id":6599,"links":{},"metadata":{"_buckets":{"deposit":"c28b9597-be5f-4334-830c-3b3735984a98"},"_deposit":{"created_by":3,"id":"6599","owners":[3],"pid":{"revision_id":0,"type":"depid","value":"6599"},"status":"published"},"_oai":{"id":"oai:tokyo-metro-u.repo.nii.ac.jp:00006599","sets":["1647:634:635"]},"author_link":["21656","21652","21655","21653","21654"],"item_6_alternative_title_19":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"Optimal Two-impulse Reorientation of Spin-stabilized Asymmetric Spacecraft"}]},"item_6_biblio_info_7":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2016","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"4","bibliographicPageEnd":"214","bibliographicPageStart":"209","bibliographicVolumeNumber":"64","bibliographic_titles":[{"bibliographic_title":"日本航空宇宙学会論文集"}]}]},"item_6_creator_2":{"attribute_name":"著者(ヨミ)","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"コジマ, ヒロヒサ"}],"nameIdentifiers":[{"nameIdentifier":"21654","nameIdentifierScheme":"WEKO"}]}]},"item_6_creator_3":{"attribute_name":"著者別名","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Aoyagi, Yuki"}],"nameIdentifiers":[{"nameIdentifier":"21655","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Kojima, Hirohisa"}],"nameIdentifiers":[{"nameIdentifier":"21656","nameIdentifierScheme":"WEKO"}]}]},"item_6_description_4":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"In this paper, optimal attitude reorientation problems of spin-stabilized asymmetric spacecraft by impulsive thrust are studied. The spacecraft attitude is represented by two set of Euler angles to easily consider the goal attitude in the inertial frame. Two thrust impulses that are necessary to achieve the goal attitude are numerically analyzed by deriving analytical equations of the attitude expressed by elliptic integrals and Jacobi elliptic functions. Finally, Pareto optimal solutions with respect to total input and maneuver time are derived with setting the precession angle as the variable parameter.","subitem_description_type":"Abstract"}]},"item_6_publisher_33":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"日本航空宇宙学会"}]},"item_6_rights_13":{"attribute_name":"権利","attribute_value_mlt":[{"subitem_rights":"日本航空宇宙学会"},{"subitem_rights":"訂正原稿。Appendixに訂正が赤文字で記載されている。学会よりリポジトリで訂正原稿を出すよう指示あり。"}]},"item_6_source_id_10":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA11307372","subitem_source_identifier_type":"NCID"}]},"item_6_source_id_8":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"13446460","subitem_source_identifier_type":"ISSN"}]},"item_6_version_type_16":{"attribute_name":"著者版フラグ","attribute_value_mlt":[{"subitem_version_resource":"http://purl.org/coar/version/c_970fb48d4fbd8a85","subitem_version_type":"VoR"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"青柳, 祐基"}],"nameIdentifiers":[{"nameIdentifier":"21652","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"小島, 広久"}],"nameIdentifiers":[{"nameIdentifier":"21653","nameIdentifierScheme":"WEKO"}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2018-02-06"}],"displaytype":"detail","filename":"10942-001.pdf","filesize":[{"value":"1.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"10942-001.pdf","url":"https://tokyo-metro-u.repo.nii.ac.jp/record/6599/files/10942-001.pdf"},"version_id":"bbe8d653-33da-4269-b020-0f9ffe251303"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Spacecraft","subitem_subject_scheme":"Other"},{"subitem_subject":"Attitude Control","subitem_subject_scheme":"Other"},{"subitem_subject":"Euler Angles","subitem_subject_scheme":"Other"},{"subitem_subject":"Rigid Body Dynamics","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"スピン安定型非対称宇宙機の最適2インパルス指向制御","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"スピン安定型非対称宇宙機の最適2インパルス指向制御"}]},"item_type_id":"6","owner":"3","path":["635"],"pubdate":{"attribute_name":"公開日","attribute_value":"2018-02-20"},"publish_date":"2018-02-20","publish_status":"0","recid":"6599","relation_version_is_last":true,"title":["スピン安定型非対称宇宙機の最適2インパルス指向制御"],"weko_creator_id":"3","weko_shared_id":-1},"updated":"2023-06-19T16:36:02.585246+00:00"}