{"created":"2023-06-20T14:36:17.295589+00:00","id":2605,"links":{},"metadata":{"_buckets":{"deposit":"762b253d-ec3c-4fac-bdc7-99880df88245"},"_deposit":{"created_by":1,"id":"2605","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2605"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002605","sets":["1887:1893","9:1090:1241:1259"]},"author_link":["7716","7718","7714","7717","7715","7713","7720","7721","7722","7719"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Pressure measurement system for the 2nd supersonic flight test of the NEXST-1"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-08-29","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RM-08-001","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":"宇宙航空研究開発機構(JAXA)では小型超音速ロケット実験機(NEXST-1: National EXperimental Supersonic Transport-1)の抵抗低減空力設計コンセプトや最適空力設計ツールの妥当性を検証するため飛行実験を行った。この飛行実験では空力設計の妥当性検証に必要な多くの空力データを取得している。この空力データは大きく、機体周りの表面静圧分布、全機空気力、そして、主翼上面や前胴部の境界層遷移位置計測の3つに分けられ、本稿では表面静圧計測システムについてまとめる。飛行実験では高い信頼性、健全性をもつ計測システムを構築することが必要である。そのため、飛行実験において検証に必要な計測精度を明確にした上で、いくつかの工夫により必要計測精度を満たす圧力計測システムを構築した。さらに、飛行実験前まで徹底したシステムの健全性管理を行い、また、飛行実験後には再度計測システムの精度検証試験を行った。これにより高精度の飛行実験データを取得することができた。飛行実験で取得された表面静圧データを評価し、空力設計の妥当性を検証することができた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A flight test of a supersonic experimental airplane (NEXST-1: National EXperimental Supersonic Transport-1) was performed by Japan Aerospace Exploration Agency (JAXA) to demonstrate advanced aerodynamic design technologies for the next generation SuperSonic Transport (SST). Main issue of the aerodynamic design of the NEXST-1 is the drag reduction on the supersonic cruise conditions. Therefore, four aerodynamic design concepts were applied to the design of the NEXST-1. In the flight test, three kinds of aerodynamic data were obtained to validate the aerodynamic design concepts and design tools. The static surface pressure measurement systems, that is the one of the measurement items on the flight test were described in this report. Wind tunnel tests and functional tests were conducted to improve the accuracy of the measurement systems. Then, high quality pressure measurement system can be constructed on the NEXST-1. System checks were performed to maintain the high reliability before and after the flight test. Measured data from the flight test were also analyzed to confirm the measurement system reliability. From those results, high quality surface static pressure can be measured on the NEXST-1 flight test.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064091000","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-08-001","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 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"宇宙航空研究開発機構 研究開発本部　研究開発企画室"},{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"川崎重工業 航空宇宙カンパニー　技術本部"},{"subitem_text_value":"川崎重工業 航空宇宙カンパニー　技術本部"}]},"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 Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Research and Development Planning Office, Aerospace Research and Development Directorate"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries Ltd. Engineering Division, Aerospace Company"},{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries Ltd. Engineering Division, Aerospace Company"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Kwak, Dong-Youn"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"田中, 稔久"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"安藤, 敦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dong-Youn","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tanaka, Toshihisa","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ando, Atsushi","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":"64091000.pdf","filesize":[{"value":"5.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64091000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2605/files/64091000.pdf"},"version_id":"1b06e8c3-39ce-4d83-a079-82f39e1fdd7b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験","subitem_subject_scheme":"Other"},{"subitem_subject":"空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力測定","subitem_subject_scheme":"Other"},{"subitem_subject":"静圧","subitem_subject_scheme":"Other"},{"subitem_subject":"NEXST-1","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力センサ","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"static pressure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NEXST-1","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure sensor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","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":"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":"小型超音速実験機の第2回飛行実験における表面静圧計測システム","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"小型超音速実験機の第2回飛行実験における表面静圧計測システム"}]},"item_type_id":"3","owner":"1","path":["1259","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2605","relation_version_is_last":true,"title":["小型超音速実験機の第2回飛行実験における表面静圧計測システム"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:19:14.709926+00:00"}