{"created":"2023-06-20T15:08:04.332043+00:00","id":37460,"links":{},"metadata":{"_buckets":{"deposit":"e57f21d0-bab0-48ac-8bad-3f7e50ee13de"},"_deposit":{"created_by":1,"id":"37460","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37460"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037460","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480889","480891","480892","480890"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"柔構造航空機力学のシミュレーション"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"184","bibliographicPageStart":"181","bibliographicVolumeNumber":"44","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","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":"航空宇宙技術研究所 16-18 Jun. 1999 東京 日本","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":"National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"SST実験機の遷音速領域でのフラッタの数値シミュレーションを報告する。航空機の翼と胴体の弾性は、構造方程式を解く際に24個の対称および非対称の自然モードを使用することによって考慮した。SSTの応答を見るために、オイラー方程式および構造方程式は同時に積分された。線形理論と同じように、補助翼のフラッタはこの形状では最も重要なものの1つであることが分かった。マッハ数0.6〜1.0の範囲で線形理論から予測されたフラッタの境界より低い値が推算された。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Numerical flutter simulation of the experimental SST in transonic region is presented. The elasticity of the aircraft's wing and fuselage is taken into account by utilizing 24 symmetric and anti-symmetric natural modes in solving structural equations. The Euler and structural equations were integrated simultaneously to obtain SST responses. The aileron flutter, like the linear theory, was found to be the most critical one for this configuration. The flutter boundaries are estimated lower than those obtained by the linear theory for the range of Mach number 0.6-1.0.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001961027","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-44","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"計算力学研究センター"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Research Center of Computational Mechanics Inc"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"ケイランディシュ, ハミド レザ"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中道, 二郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kheirandish, Hamid Reza","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakamichi, Jiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0044027.pdf","filesize":[{"value":"1.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0044027.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37460/files/nalsp0044027.pdf"},"version_id":"40b6ff79-79bd-456b-8994-47ce257ab9f1"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"数値シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"不規則振動","subitem_subject_scheme":"Other"},{"subitem_subject":"柔構造航空機力学","subitem_subject_scheme":"Other"},{"subitem_subject":"超音波航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"オイラー方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"構造方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"弾性","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速輸送","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flexible aircraft dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"super sonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Euler equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structual equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"elasticity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","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":"Simulation of a flexible aircraft dynamics","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Simulation of a flexible aircraft dynamics","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37460","relation_version_is_last":true,"title":["Simulation of a flexible aircraft dynamics"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:18:24.339519+00:00"}