{"created":"2023-06-20T15:07:30.847698+00:00","id":36880,"links":{},"metadata":{"_buckets":{"deposit":"da85449c-270e-42e0-b0bc-fefb085413bd"},"_deposit":{"created_by":1,"id":"36880","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"36880"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00036880","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["477990","477992","477988","477987","477989","477991"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Optimization of wing planform with structural constrains"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"118","bibliographicPageStart":"113","bibliographicVolumeNumber":"34","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 6-7 JUN. 1996 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 6-7 JUN. 1996 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空宇宙工学の分野では、航空機設計工程は概念設計、予備設計および詳細設計の3段階に分かれる。概念設計はミッション要求に基づき設計の方向を決定する第一段階である。この工程では、既存のデータベースや経験的方法から航空機の初期サイジングを算定する。空力、構造、燃料、ペイロードその他に対する種々の要求から、設計には多目的最適化が必要である。本論文ではこの段階での翼平面形状を設計するための最適化法を検討した。この作業では、翼平面形状最適化に、空力的性能、翼重量および燃料タンク容量の3つの目標を考慮した。空力的性能はCFD(数値流体力学)解析により評価し、翼重量と燃料タンク容量は経験式により概算した。問題を単純化するため、前縁スウィープ角度および翼中間部と翼端における2つの翼弦長だけを設計変数として用いた。翼の前縁は直線とした。後縁ねじれを持ったテーパ翼を設計した。最適化手法として、遺伝的アルゴリズム(GA)を使用した。GAは選択により進化をシミュレートする。GAはより大域的最適値を見つけ出すので、通常の傾斜法よりもうまく実行することが期待できる。GAの大きな弱点は要求される評価関数が多いことである。効率の点から、オイラーやナビエ・ストークス解法の代わりに完全ポテンシャル方程式に基づいたFLO-22コードを用いた。平面形状最適化問題を代表的亜音速航空機に対して考察した。設計結果は最適化による初期サイジングに対するアプローチ法の有用性を示した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In the field of aerospace engineering, the aircraft design process can be divided into three stages: conceptual, preliminary and detail designs. The conceptual design is the first stage to decide a direction of design from mission requirements. In this process, the initial sizing of the aircraft is estimated from existing database and empirical methods. Since there are various demands for aerodynamics, structures, fuel, payload, and so on, a multiobjective optimization is necessary for the design. Therefore, in this paper, an optimization method is investigated to design wing planforms for this stage. In this work, three objectives are considered for wing planform optimization: aerodynamic performance, wing weight, and fuel tank volume. Aerodynamic performance is evaluated by CFD (Computational Fluid Dynamics) analysis. Wing weight and fuel tank volume are estimated by empirical formulae. To simplify the problem, only the leading-edge sweep angle and two chord lengths at the midspan and wingtip are used as design variables. The leading edge of the wing is kept straight. Thus, a tapered wing with a trailing-edge kink will be designed. As an optimizer, Genetic Algorithm (GA) is employed here. GA simulates evolution by selection. Because GA can find a more global optimum, it is expected to perform better than the conventional gradient-based methods. Major drawback of GA is that it requires a large number of function evaluations. Thus, FLO-22 code based on the full potential equation is used because of its efficiency instead of Euler or Navier-Stokes solver. Planform optimization problems are considered for typical subsonic aircraft. The design results show the feasibility of the present approach for the initial sizing with optimization.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000685021","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-34","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":"東北大学 大学院"},{"subitem_text_value":"東北大学 工学部　機械航空工学科"},{"subitem_text_value":"東北大学 工学部　機械航空工学科"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tohoku University Graduate School"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Department of Aeronautics and Space Engineering, Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Department of Aeronautics and Space Engineering, Faculty of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山口, 義博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"大林, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中橋, 和博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamaguchi, Yoshihiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Obayashi, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakahashi, Kazuhiro","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":"nalsp0034021.pdf","filesize":[{"value":"1.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0034021.pdf","url":"https://jaxa.repo.nii.ac.jp/record/36880/files/nalsp0034021.pdf"},"version_id":"71fd96a3-210e-42a1-8c5f-c4c21fe77ce8"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"翼平面形状","subitem_subject_scheme":"Other"},{"subitem_subject":"評価関数","subitem_subject_scheme":"Other"},{"subitem_subject":"最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"完全ポテンシャル方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"初期サイジング","subitem_subject_scheme":"Other"},{"subitem_subject":"空力性能","subitem_subject_scheme":"Other"},{"subitem_subject":"翼重量","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料タンク容量","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"数値流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"FLO22コード","subitem_subject_scheme":"Other"},{"subitem_subject":"遺伝的アルゴリズム","subitem_subject_scheme":"Other"},{"subitem_subject":"wing planform","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"evaluation function","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"full potential equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"initial sizing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic performance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing weight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel tank volume","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"FLO22 code","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"genetic algorithm","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":"構造的制限を考慮した翼平面形状の最適化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"構造的制限を考慮した翼平面形状の最適化"}]},"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":"36880","relation_version_is_last":true,"title":["構造的制限を考慮した翼平面形状の最適化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:29:56.266935+00:00"}