WEKO3
アイテム
{"_buckets": {"deposit": "bf07f10a-2168-4d99-9c78-54dd3b6c2333"}, "_deposit": {"created_by": 1, "id": "3442", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "3442"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00003442", "sets": ["824", "1891"]}, "author_link": ["13627", "13630", "13633", "13631", "13628", "13629", "13632", "13634"], "item_5_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "2017-03-15", "bibliographicIssueDateType": "Issued"}, "bibliographicPageEnd": "466", "bibliographicPageStart": "457", "bibliographicVolumeNumber": "JAXA-SP-16-008E", "bibliographic_titles": [{"bibliographic_title": "宇宙航空研究開発機構特別資料"}, {"bibliographic_title": "JAXA Special Publication: Proceedings of the First International Symposium on Flutter and its Application", "bibliographic_titleLang": "en"}]}]}, "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": "First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan", "subitem_description_type": "Other"}]}, "item_5_description_17": {"attribute_name": "抄録(英)", "attribute_value_mlt": [{"subitem_description": "Recent commercial aircraft have high aspect ratio wings to improve the fuel efficiency. However, it is concerned that the margin of wing strength gets smaller, especially at the wing root. In order to deal with the problem, adaptive wing structure, which can change the lift-to-drag ratio in flight, is considered. By using the adaptive wing structure, the lift distribution can be modified so that the bending moment decreases. The purpose of this paper is to investigate the effectiveness of adaptive wing structure for reducing the bending moment and the stress. For this purpose, static aeroelastic analysis is conducted with a semispan wing model using MSC/NASTRAN. The model is composed of spars, ribs and skins, and has 4 flaps at each of its leading and trailing edges. The set of flap deflection angles is optimized to minimize the wing root bending moment in a 2.5 pull-up maneuver with Response Surface Methodology (RSM) using MATLAB. As a result, the wing root bending moment is successfully reduced by 10 approximately 35% in comparison to that of the original configuration whose flaps have 0 deg deflection angles.", "subitem_description_type": "Other"}]}, "item_5_description_18": {"attribute_name": "内容記述", "attribute_value_mlt": [{"subitem_description": "形態: カラー図版あり", "subitem_description_type": "Other"}]}, "item_5_description_19": {"attribute_name": "内容記述(英)", "attribute_value_mlt": [{"subitem_description": "Physical characteristics: Original contains color illustrations", "subitem_description_type": "Other"}]}, "item_5_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA1630046049", "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-16-008E", "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(JAXA)"}]}, "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_34": {"attribute_name": "メタデータ提供者", "attribute_value_mlt": [{"subitem_text_value": "メタデータ提供者: JAXA"}]}, "item_5_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: 特別資料"}]}, "item_5_text_36": {"attribute_name": "JAXAカテゴリ2", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ2: AP"}]}, "item_5_text_38": {"attribute_name": "NASA分類コード", "attribute_value_mlt": [{"subitem_text_value": "NASA分類コード: 08"}]}, "item_5_text_39": {"attribute_name": "NASA分類表目標", "attribute_value_mlt": [{"subitem_text_value": "NASA分類: Aircraft Stability and Control"}]}, "item_5_text_40": {"attribute_name": "jaxa出版物種類", "attribute_value_mlt": [{"subitem_text_value": "jaxa出版物種類: SP"}]}, "item_5_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 10"}]}, "item_5_text_6": {"attribute_name": "著者所属", "attribute_value_mlt": [{"subitem_text_value": "東京大学"}, {"subitem_text_value": "東京大学"}, {"subitem_text_value": "宇宙航空研究開発機構(JAXA)"}, {"subitem_text_value": "宇宙航空研究開発機構(JAXA)"}]}, "item_5_text_7": {"attribute_name": "著者所属(英)", "attribute_value_mlt": [{"subitem_text_language": "en", "subitem_text_value": "The University of Tokyo"}, {"subitem_text_language": "en", "subitem_text_value": "The University of Tokyo"}, {"subitem_text_language": "en", "subitem_text_value": "Japan Aerospace Exploration Agency (JAXA)"}, {"subitem_text_language": "en", "subitem_text_value": "Japan Aerospace Exploration Agency (JAXA)"}]}, "item_creator": {"attribute_name": "著者", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "藤井, 奏風"}], "nameIdentifiers": [{"nameIdentifier": "13627", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "横関, 智弘"}], "nameIdentifiers": [{"nameIdentifier": "13628", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "有薗, 仁"}], "nameIdentifiers": [{"nameIdentifier": "13629", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "玉山, 雅人"}], "nameIdentifiers": [{"nameIdentifier": "13630", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Fujii, Kanata", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "13631", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Yokozeki, Tomohiro", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "13632", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Arizono, Hitoshi", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "13633", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Tamayama, Masato", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "13634", "nameIdentifierScheme": "WEKO"}]}]}, "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", "download_preview_message": "", "file_order": 0, "filename": "AA1630046049.pdf", "filesize": [{"value": "3.7 MB"}], "format": "application/pdf", "future_date_message": "", "is_thumbnail": false, "licensetype": "license_free", "mimetype": "application/pdf", "size": 3700000.0, "url": {"label": "AA1630046049.pdf", "url": "https://jaxa.repo.nii.ac.jp/record/3442/files/AA1630046049.pdf"}, "version_id": "7b5653b6-40d8-48ce-bba0-d043960cd44a"}]}, "item_keyword": {"attribute_name": "キーワード", "attribute_value_mlt": [{"subitem_subject": "Adaptive wing", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Aeroelasticity", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Optimization", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Response surface methodology", "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": "conference paper", "resourceuri": "http://purl.org/coar/resource_type/c_5794"}]}, "item_title": "Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment", "item_titles": {"attribute_name": "タイトル", "attribute_value_mlt": [{"subitem_title": "Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment", "subitem_title_language": "en"}]}, "item_type_id": "5", "owner": "1", "path": ["824", "1891"], "permalink_uri": "https://jaxa.repo.nii.ac.jp/records/3442", "pubdate": {"attribute_name": "公開日", "attribute_value": "2017-04-27"}, "publish_date": "2017-04-27", "publish_status": "0", "recid": "3442", "relation": {}, "relation_version_is_last": true, "title": ["Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment"], "weko_shared_id": -1}
Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment
https://jaxa.repo.nii.ac.jp/records/3442
https://jaxa.repo.nii.ac.jp/records/34428c3a0b3e-cf48-44e6-af28-c843efeb334c
名前 / ファイル | ライセンス | アクション |
---|---|---|
AA1630046049.pdf (3.7 MB)
|
|
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2017-04-27 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Adaptive wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aeroelasticity | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Response surface methodology | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
著者 |
藤井, 奏風
× 藤井, 奏風× 横関, 智弘× 有薗, 仁× 玉山, 雅人× Fujii, Kanata× Yokozeki, Tomohiro× Arizono, Hitoshi× Tamayama, Masato |
|||||
著者所属 | ||||||
東京大学 | ||||||
著者所属 | ||||||
東京大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
The University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構(JAXA) | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料 en : JAXA Special Publication: Proceedings of the First International Symposium on Flutter and its Application 巻 JAXA-SP-16-008E, p. 457-466, 発行日 2017-03-15 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Recent commercial aircraft have high aspect ratio wings to improve the fuel efficiency. However, it is concerned that the margin of wing strength gets smaller, especially at the wing root. In order to deal with the problem, adaptive wing structure, which can change the lift-to-drag ratio in flight, is considered. By using the adaptive wing structure, the lift distribution can be modified so that the bending moment decreases. The purpose of this paper is to investigate the effectiveness of adaptive wing structure for reducing the bending moment and the stress. For this purpose, static aeroelastic analysis is conducted with a semispan wing model using MSC/NASTRAN. The model is composed of spars, ribs and skins, and has 4 flaps at each of its leading and trailing edges. The set of flap deflection angles is optimized to minimize the wing root bending moment in a 2.5 pull-up maneuver with Response Surface Methodology (RSM) using MATLAB. As a result, the wing root bending moment is successfully reduced by 10 approximately 35% in comparison to that of the original configuration whose flaps have 0 deg deflection angles. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA1630046049 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-16-008E |