{"created":"2023-06-20T14:39:14.771810+00:00","id":5957,"links":{},"metadata":{"_buckets":{"deposit":"c9bd1b28-3319-4264-a15f-3527252fab38"},"_deposit":{"created_by":1,"id":"5957","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5957"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005957","sets":["1887:1891","9:789:998:1024"]},"author_link":["29493","29494","29496","29495"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Comparison of structural model on aeroelastic computations of a transonic delta wing with large deformations"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2006-12-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"70","bibliographicPageStart":"65","bibliographicVolumeNumber":"JAXA-SP-06-010","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Aeroelastic computations of a transonic delta wing with large deformation were performed for the investigation of behavior of structural model. The structural models used for the comparison were the linear structural models including modal analysis and the geometrically nonlinear structural models with and without higher-order terms in the strain-displacement relationship. Navier-Stokes equations were applied through all the computations. On the flutter prediction, the linear and the nonlinear structural models indicated the almost same flutter dynamic pressure. Therefore, it made sure that the linear structural model was suitable for the prediction of flutter onset in accuracy. After the flutter onset, the difference of wing response between the linear and the nonlinear structural model grew up as the wing response became larger. All the linear structural models showed the limit cycle oscillation with well large amplitudes due to the unphysical stiffness. The number of selected structural mode had little effect on the wing response even with the large amplitude. On the other hand, the nonlinear structural model produced the limit cycle oscillation with relatively smaller amplitudes, which was closer to that observed in the experiment. The higher-order terms in the strain-displacement relationship gave less significant influence for the wing response over the present range of deformation. The present results indicated that the nonlinear structural model should be applied for the aeroelastic computation of the wing response with large deformation.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063154013","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: JAXA-SP-06-010","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"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-113X","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":"AA11984031","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"理化学研究所"},{"subitem_text_value":"理化学研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Institute of Physical and Chemical Research"},{"subitem_text_language":"en","subitem_text_value":"Institute of Physical and Chemical Research"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"寺島, 洋史"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小野, 謙二"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Terashima, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ono, Kenji","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":"2020-01-16"}],"displaytype":"detail","filename":"63154013.pdf","filesize":[{"value":"3.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63154013.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5957/files/63154013.pdf"},"version_id":"6578bbbd-3358-4650-88b1-52fb8810e1b2"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速","subitem_subject_scheme":"Other"},{"subitem_subject":"空力弾性","subitem_subject_scheme":"Other"},{"subitem_subject":"変形","subitem_subject_scheme":"Other"},{"subitem_subject":"リミットサイクル振動","subitem_subject_scheme":"Other"},{"subitem_subject":"LCO","subitem_subject_scheme":"Other"},{"subitem_subject":"構造モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"動圧","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"数値解析","subitem_subject_scheme":"Other"},{"subitem_subject":"計算格子","subitem_subject_scheme":"Other"},{"subitem_subject":"流体格子","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic speed","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aeroelasticity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"deformation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"limit cycle oscillation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"LCO","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structural model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"dynamic pressure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier-Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational grid","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fluid grid","subitem_subject_language":"en","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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"遷音速デルタ翼の大変形シミュレーションにおける構造モデルの影響","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"遷音速デルタ翼の大変形シミュレーションにおける構造モデルの影響"}]},"item_type_id":"5","owner":"1","path":["1024","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"5957","relation_version_is_last":true,"title":["遷音速デルタ翼の大変形シミュレーションにおける構造モデルの影響"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:05:16.547688+00:00"}