{"created":"2023-06-20T14:36:26.623717+00:00","id":2754,"links":{},"metadata":{"_buckets":{"deposit":"1912fc41-8324-4efe-9cda-c078deff3812"},"_deposit":{"created_by":1,"id":"2754","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2754"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002754","sets":["1887:1893","9:1090:1333:1337"]},"author_link":["8796","8795"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"NALで開発された数値空力弾性試験・評価プログラム"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-03-25","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RM-03-028E","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発資料"},{"bibliographic_title":"JAXA Research and Development Memorandum","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空機の空力弾性問題は、航空機の構造設計のみならず飛行力学の観点、さらには、高度な設計精度を要求される今日にいたっては、空気力学的な面からも重要視される、いわゆる多分野統合問題である。低速域、あるいは超音速域での空力弾性問題は、非定常空気力として古典的な揚力面理論を適用することで問題が解決する場合が多い。遷音速域においては周知のとおり翼面上の衝撃波、あるいはそれと境界層との干渉による剥離などに起因するいわゆるフラッタ境界の遷音速ディップが起こる。その結果、一般的には、超音速航空機においてもフラッタは遷音速域がクリティカルになることが知られている。航空宇宙技術研究所では、これらの観点から従来、空力弾性の研究、特に遷音速域における非定常空気力の計算法の研究、あるいはそれを用いたフラッタ計算プログラムの開発に努力を傾注してきた。これらの知的財産を統合化して、汎用かつ種々の航空機の空力弾性解析のためのコンピュータソフトの開発を計画した。これらのソフトは、航空機メーカに対して有料ではあるが設計ツールとして提供される。本、ソフトの特徴は1)揚力面理論、遷音速微少擾乱理論、フルポテンシャル理論、オイラー理論およびナビエ・ストークス理論による非定常空気力の適用が可能であること、2)したがって、ユーザーが、解析対象、目的、要求精度、計算時間(計算費用)の観点から、適切なモデルを選択しえること、3)基本的には、高度なモデルに対するデータおよび計算パラメターは、低次のモデルに対するそれらに自動的に変換可能であること、4)GUI(Graphical User Interface)で動作し、ユーザーと親密な関係で操作が可能なこと、5)UnixおよびWindowsの双方のOS上で動作が可能であることである。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Transonic flows are characterized by the presence of adjacent regions of subsonic and supersonic flows accompanied by shock waves. In the past, there have been many activities in the development of computational methods for the analysis of steady and unsteady transonic flow in the time-linearized frequency- and time-domain. These activities were motivated by the need to supplement expensive and time consuming wind tunnel tests subject to unsteady aerodynamics and aeroelasticity, especially, flutter, with an affordable and reliable alternative. In the present paper, the outline of the aeroelasticity analytical tool named as Numerical Aeroelasticity Testing and Assessment System (NATAS) developed at NAL is prescribed. This system consists of four modules; the Doublet Point Method module (The Linear Lifting Surface Theory), The TSD module (The Transonic Small Disturbance Theory), the FP module (The Full Potential Theory) and the EL/NS module (The Euler and Navier-Stokes' Theory). The prototypes of these codes were developed by the researchers at NAL of Japan. The NATAS uses GUI (Graphical User Interface) to interactively manage input, output and interlink among the modules, error processing and graphical results. The input data for the higher model can be automatically converted for the lower one. The user can choose the module depending upon the trade-off among the purpose of the calculation, the accuracy, the efficiency and the cost. There are still restrictions on the function of the NATAS at present stage. However, it continues to be evolving.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047423000","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: JAXA-RM-03-028E","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1121","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":"AA11983593","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"中道, 二郎"}],"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":"2020-01-15"}],"displaytype":"detail","filename":"47423000.pdf","filesize":[{"value":"3.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"47423000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2754/files/47423000.pdf"},"version_id":"d15b21be-12c3-4dcd-944e-12103166f57e"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"数値解析","subitem_subject_scheme":"Other"},{"subitem_subject":"空力弾性","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"計算機プログラム","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"衝撃波","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"設計ツール","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aeroelasticity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computer program","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unsteady aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shock wave","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design tool","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 aeroelasticity testing and assessment system developed at NAL of Japan","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Numerical aeroelasticity testing and assessment system developed at NAL of Japan","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1337","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2754","relation_version_is_last":true,"title":["Numerical aeroelasticity testing and assessment system developed at NAL of Japan"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:16:37.120938+00:00"}