{"created":"2023-06-20T15:12:33.940993+00:00","id":42419,"links":{},"metadata":{"_buckets":{"deposit":"ae8a25ee-0022-4d93-9d5c-cc09e8815381"},"_deposit":{"created_by":1,"id":"42419","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42419"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042419","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["458283","458286","458285","458284"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Basic aerodynamic characteristics of MuPAL's DLC-flaps derived from low-speed wind tunnel testing"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2001-02","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"756","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所で開発中の実験用航空機Dornier Do228-200型機を母機としたMuPAL (Multi-Purpose Aviation Laboratory:多目的実証実験機)と呼ばれるインフライト・シミュレータには、フラップ・イン・フラップ方式のDLC (Direct Lift Control:直接揚力制御)フラップが搭載される。このDLCフラップの空力的な性能(対称動作)やDLCフラップ故障時の安全性(非対称動作)を飛行シミュレーションなどで評価するために、航空宇宙技術研究所の大型低速風洞と1/6縮尺プロペラ付全機風洞模型とを用いてDLCフラップの静的な空力特性を取得する低速風洞試験を行った。その結果、飛行シミュレーション用数学モデルに反映するデータが得られるとともに、(1)DLCフラップにより得られる上下加速度は目標性能を満足すること、(2)DLCフラップ故障時の非対称動作は静的には飛行の安全にほとんど影響がないことが明らかとなった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Flap-in-flap type DLC (Direct Lift Control) flaps were installed on the MuPAL (Multi-Purpose Aviation Laboratory), an in-flight simulator now being developed by the NAL and based on a Dornier Do228-200. In order to evaluate the aerodynamic performance of DLC-flaps (symmetrical deflection) and flight safety in the event of malfunction (asymmetrical deflection), the static aerodynamic characteristics were investigated using the NAL low-speed wind tunnel and a 1/6-scale model with motor-driven propellers. As a result, data to be reflected in a mathematical model for flight simulation tests was derived and was proved that (1) vertical acceleration generated by the DLC-flaps could attain the target performance and (2) the asymmetrical deflection caused by malfunction of the DLC-flaps had only a minimal effects on flight safety.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0032238000","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 TM-756","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":"0452-2982","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":"AN00314334","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 飛行研究部"},{"subitem_text_value":"航空宇宙技術研究所 流体科学総合研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Flight Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"穂積, 弘毅"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"白井, 正孝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hozumi, Koki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shirai, Masataka","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":"2020-01-28"}],"displaytype":"detail","filename":"naltm0000756.pdf","filesize":[{"value":"1.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000756.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42419/files/naltm0000756.pdf"},"version_id":"a33df346-c440-44fb-a66f-cdfc99f48a88"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"数学モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行安全性","subitem_subject_scheme":"Other"},{"subitem_subject":"低速","subitem_subject_scheme":"Other"},{"subitem_subject":"偏向","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mathematical model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight safety","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"deflection","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"低速風洞試験によるMuPAL(多目的実証実験機)のDLCフラップ基本空力特性確認","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"低速風洞試験によるMuPAL(多目的実証実験機)のDLCフラップ基本空力特性確認"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"42419","relation_version_is_last":true,"title":["低速風洞試験によるMuPAL(多目的実証実験機)のDLCフラップ基本空力特性確認"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:23:43.426140+00:00"}