{"created":"2023-06-20T15:11:29.650758+00:00","id":41164,"links":{},"metadata":{"_buckets":{"deposit":"e7b5ea77-85f3-462f-9e2f-56cc84e3771d"},"_deposit":{"created_by":1,"id":"41164","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41164"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041164","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["450881","450873","450868","450878","450866","450883","450871","450870","450872","450869","450867","450879","450874","450884","450882","450885","450876","450875","450880","450877"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Estimation of critical values and vibration characteristics on supersonic delta wings. Part 2: Locally-stationary time series analysis of nonstationary random responses"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-09","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"19","bibliographicPageStart":"1","bibliographicVolumeNumber":"1179","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速デルタ翼の固定条件を変えた翼模型を設計し、振動試験と風洞試験を実施した。風洞試験で取得した翼の不規則応答データを著者らが開発した時系列解析システムのフラッタ限界値推定法に適用し、複雑な翼の特性の推定を行った。試験においては片持ち固定したデルタ翼模型の固定部分の割合が50％C(％Cは完全固定を100とする翼の固定割合を表す)に近くなると、翼の破損を伴う困難な問題が発生した。この対策の1つとして翼模型衝撃防止装置を開発し試験に用いた。装置の効果は極めて有効で翼の破損を防止し、さらにフラッタ抑止にも機能した。ここで、デルタ翼模型のフラッタ限界値の推定は設定した試験動圧範囲をスィープする1RUNの非定常な風試で取得した不規則応答データを局所定常時系列解析システムに適用し、精度良く行うことができた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A locally-stationary time series analysis of nonstationary random responses in delta wings under supersonic conditions is presented. Since the partially supported cantilever delta wings failed during supersonic blowdown wind tunnel tests employing the injection and rejection systems, a safety device was introduced to prevent such failures. This enabled wing response data to be obtained from a test blow in which the dynamic pressure was increased at a constant speed with the Mach number being fixed. Estimated results indicated that the wing's critical values could be determined by applying the locally-stationary autoregressive process.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004194000","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 TR-1179","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"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 機体部"},{"subitem_text_value":"航空宇宙技術研究所 機体部"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所 構造力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Airframe Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Airframe Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Structural Mechanics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"峯岸, 正勝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"安藤, 泰勝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"松崎, 雄嗣"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"江尻, 宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"榊原, 盛三"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野田, 順一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石田, 清道"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"関根, 英夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"楯, 篤志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 光則"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Minegishi, Masakatu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ando, Yasukatu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Matsuzaki, Yuji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ejiri, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sakakibara, Seizo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noda, Jyunichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishida, Kiyomichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sekine, Hideo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tate, Atsushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Mitsunori","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01179.pdf","filesize":[{"value":"2.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01179.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41164/files/naltr01179.pdf"},"version_id":"761af5dc-d9ed-4228-a95b-afa9c523e1a2"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"フラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"空力弾性","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"振動特性","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ特性","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ模型","subitem_subject_scheme":"Other"},{"subitem_subject":"振動試験","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ限界推定","subitem_subject_scheme":"Other"},{"subitem_subject":"模型設計","subitem_subject_scheme":"Other"},{"subitem_subject":"保護装置","subitem_subject_scheme":"Other"},{"subitem_subject":"サブクリティカルフラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常不規則応答","subitem_subject_scheme":"Other"},{"subitem_subject":"時系列解析","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aeroelasticity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vibration characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vibration test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter boundary estimation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"model design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"protection device","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subcritical flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nonstationary random process","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 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