{"created":"2023-06-20T15:11:43.245300+00:00","id":41434,"links":{},"metadata":{"_buckets":{"deposit":"a9ba99c7-c059-4bc6-8fe7-759a8514fa91"},"_deposit":{"created_by":1,"id":"41434","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41434"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041434","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["490019","490017","490018","490016"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"完全な航空機形状のための空力-構造結合最適化法"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"152","bibliographicPageStart":"133","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":"本報では、空力-構造システム結合最適化のための新しい枠組みについて報告した。この枠組みは、空気力学および構造両方の高厳密度モデルの使用を可能にし、高厳密度の複合領域最適化能力の開発に向けた努力における最初のステップを示す。この手法は、空気力学および構造サブ問題解決のための効率的な研究方法、空力感度を得るための随伴式ソルバおよび多プロセッサ並列演算に基づいている。関心のある形態の外形枠線(OML)を表す幾何学的データベースをこの枠組みのコアにおいている。この幾何学的表現を用いて、各分野が個々にOMLデータベースと結合することにより、空気力学と構造との間の情報交換を達成する。また、本枠組みは熱伝達およびレーダ像など他の分野を後で比較的容易に取込むことができる。オイラーおよびレイノルズ平均ナビエ・ストークス(RANS)方程式にたいする有限体積法流れソルバと2種の異なった線形有限要素構造モデルとの結合による特有の結果を探究した。分野の結合においては、一致および保存スキームを達成するように留意した。空力弾性解の重要性を示すために、風洞試験データとの直接の比較した。さらに、簡単化した設計例を報告し、完全な航空機形状について空力性能と構造重量の間のトレードオフ評価における、この新しい空力構造設計法が持つ有利さを示した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"This paper presents a new framework for the coupled optimization of aero-structural systems. The framework permits the use of high-fidelity modeling of both the aerodynamics and the structures and represents the first step in an effort towards the development of a high-fidelity multidisciplinary optimization capability. The approach is based on efficient analysis methodologies for the solution of the aerodynamics and structures subproblems, an adjoint solver to obtain aerodynamic sensitivities, and a multiprocessor parallel implementation. A geometry database representing the Outer Mold Line (OML) of the configuration of interest is placed at the core of the framework. Using this geometry description, the information exchange between aerodynamics and structures is accomplished through an independent coupling of each discipline with the OML database. The framework permits the later inclusion of other disciplines, such as heat transfer and radar signatures, with relative ease. Specific results from the coupling of a finite volume flow solver for the Euler and Reynolds Averaged Navier-Stokes (RANS) equations with two different linear finite element structural models are explored. Care is taken in the treatment of the coupling of the disciplines such that a consistent and conservative scheme is achieved. Direct comparisons with wind-tunnel data are presented to demonstrate the importance of aeroelastic solutions. In addition, simplified design examples are presented to illustrate the possible advantages of the new aero-structural design methodology in evaluating trade-off between aerodynamic performance and structural weight for complete aircraft configurations.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028638018","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":"MCAT Institute"},{"subitem_text_value":"Stanford University"},{"subitem_text_value":"Stanford University"},{"subitem_text_value":"NASA Ames Research Center"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"MCAT Institute"},{"subitem_text_language":"en","subitem_text_value":"Stanford University"},{"subitem_text_language":"en","subitem_text_value":"Stanford University"},{"subitem_text_language":"en","subitem_text_value":"NASA Ames Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Reuther, James J.","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Alonso, Juan J.","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Martins, Joaquim R. R. A.","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Smith, Stephen C.","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":"nalsp0049018.pdf","filesize":[{"value":"1.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0049018.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41434/files/nalsp0049018.pdf"},"version_id":"8cb857de-213d-406a-9eb5-f2c9c4257735"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"航空機形状","subitem_subject_scheme":"Other"},{"subitem_subject":"空力・構造結合最適化法","subitem_subject_scheme":"Other"},{"subitem_subject":"空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"航空機構造","subitem_subject_scheme":"Other"},{"subitem_subject":"複合領域最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"効率解析法","subitem_subject_scheme":"Other"},{"subitem_subject":"外形枠線データベース","subitem_subject_scheme":"Other"},{"subitem_subject":"構造有限要素モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"空力・構造カプリング技術","subitem_subject_scheme":"Other"},{"subitem_subject":"感度解析","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"coupled aero structural optimization method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft structure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"multidisciplinary optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"efficient analysis methodology","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"outer mold line database","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structural finite element model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aero structural coupling technique","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sensitivity analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","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":"A coupled aero-structural optimization method for complete aircraft configurations","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"A coupled aero-structural optimization method for complete aircraft configurations","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":"41434","relation_version_is_last":true,"title":["A coupled aero-structural optimization method for complete aircraft configurations"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:00:18.672798+00:00"}