{"created":"2023-06-20T15:11:43.480137+00:00","id":41439,"links":{},"metadata":{"_buckets":{"deposit":"b8667e9e-da7c-4102-af7e-10e454b64b72"},"_deposit":{"created_by":1,"id":"41439","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41439"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041439","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["490034","490033","490035","490036"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"数値的フラッタ・シミュレーション:SST実験機の主表面の構造設計への応用"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"182","bibliographicPageStart":"179","bibliographicVolumeNumber":"49T","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_3_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 17-19 Jan. 2000 東京 日本","subitem_description_type":"Other"}]},"item_3_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 17-19 Jan. 2000 Tokyo Japan","subitem_description_type":"Other"}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"非定常的に流体と構造物が結合した問題に関する数値シミュレーションのためのCFD(計算流体力学)コードを著者らはナビエ・ストークス/オイラー方程式に基づいて開発してきた。本報告では、NAL(航空技術研究所)の超音速輸送(SST)実験機の遷音速領域近傍における空力弾性応答の数値シミュレーションについて述べた。この計算は、流れ場を支配する非定常オイラー方程式と、構造物方程式のモーダル・アプローチ形式に基づいている。運動の構造方程式を、物体の変形は一般化変位を重率とする直交固有振動モードの重ね合せにより記述できるという仮定に基づいて導いた。このモデルの構造的動特性、固有モード形状および振動数を、NASTRAN(NASA Structural Analysis)を用いて見出した。フラッタ境界についてもまた線形理論を用いて遷音速領域を除いて決定した。マッハ数0.6〜1.0の領域に対して、フラッタ境界は線形理論で得た値より低いと評価した。線形理論と同じ様に、エルロン(補助翼)フラッタが最も不安定であることが分かった。このコードにより得たフラッタ速度は、マッハ数1.2を除いて、線形理論による値と良く一致しなかった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A CFD (Computational Fluid Dynamics) code for the numerical simulation of unsteady coupled fluid-structure problems has been developed based on Navier-Stokes/Euler equations. This report describes the numerical simulation of aeroelastic responses of the NAL (National Aerospace Laboratory) Supersonic Transport (SST) experimental aircraft around the transonic region. The computation is based on unsteady Euler equations for governing flow field and a modal approach form of equations for structures. The structural equations of motion were derived on the assumption that the deformation of the body can be described by superposing the orthogonal natural vibration modes weighted with generalized displacements. The structural dynamic characteristics, natural mode shapes and frequencies of this model were found using NASTRAN (NASA Structural Analysis). The flutter boundary was also determined except at transonic regions using linear theory. The flutter boundaries were estimated to be lower than those obtained by the linear theory for the range of Mach number 0.6 - 1.0. Like the linear theory, it was found that the aileron flutter was the most critical. The flutter speeds obtained by the present code did not agree well with those of linear theory except at Mach number 1.2.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028638023","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-49T","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_3_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_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 構造研究部　空力弾性研究室"},{"subitem_text_value":"計算力学研究センター 技術開発部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aeroelasticity Laboratory, Structures division"},{"subitem_text_language":"en","subitem_text_value":"Research Center of Computational Mechanics, Inc Technical Development"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"中道, 二郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kheirandish, Hamid Reza"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakamichi, Jiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kheirandish, Hamid Reza","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":"nalsp0049023.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0049023.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41439/files/nalsp0049023.pdf"},"version_id":"e44d772d-ba1a-41d9-a200-57a32c7461b5"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"フラッタ境界","subitem_subject_scheme":"Other"},{"subitem_subject":"数値シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ速度","subitem_subject_scheme":"Other"},{"subitem_subject":"SST実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"構造設計","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速領域","subitem_subject_scheme":"Other"},{"subitem_subject":"空力弾性応答","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常オイラー方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"線形理論","subitem_subject_scheme":"Other"},{"subitem_subject":"エルロンフラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter boundary","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter speed","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SST experimental aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structural design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic region","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aeroelastic response","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unsteady Euler equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"linear theory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aileron flutter","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"Numerical flutter simulation: Application to structural design of main surface of SST experimental aircraft","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Numerical flutter simulation: Application to structural design of main surface of SST experimental aircraft","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41439","relation_version_is_last":true,"title":["Numerical flutter simulation: Application to structural design of main surface of SST experimental aircraft"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:00:13.006309+00:00"}