{"created":"2023-06-20T15:10:22.701010+00:00","id":39959,"links":{},"metadata":{"_buckets":{"deposit":"eb5a184c-3f1b-43cd-88ff-df60ca6f0aa0"},"_deposit":{"created_by":1,"id":"39959","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39959"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039959","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["445781","445780","445782","445783"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Estimation of aerodynamic derivatives of B-65 Queen Air by the equation error method"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"45","bibliographicPageStart":"1","bibliographicVolumeNumber":"1324","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":"方程式誤差法に分類される最小二乗法およびTLS法(全最小二乗法)を用いて、クインエア機の縦空力微係数を幾つかの操縦入力に対する飛行試験時歴より直接推定し、周波数応答法による推定結果と比較した。その結果、最小二乗法およびTLS法は、周波数応答法と比較して非常に少ない飛行試験時間で空力微係数を推定することが可能で、特別の入力装置も必要としないことが示された。推定した空力微係数によるシミュレーション計算では、周波数応答法による空力微係数と同程度もしくはそれ以上の精度で飛行運動を再現することができた。また、最小二乗法およびTLS法では、説明変数のそれぞれが十分変化し、かつ、互いに独立となるよう適当な入力波形を組合せ、データ処理において計測誤差をできる限り取り除くことが重要であることが分かった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The longitudinal aerodynamic derivatives of a B-65 were estimated directly from the time histories of several maneuvers by two types of equation error method: the conventional Least Squares (LS) method and the Total Least Squares (TLS) method. The estimated results were compared with those of the frequency response method. The LS and TLS methods can greatly reduce the time for flight tests without a special device to generate a specific shape of input. Compared with the frequency response method, the resultant derivatives of the LS and TLS methods can simulate the aircraft motion with more, or at least equal, accuracy. An appropriate combination of input shapes to produce a sufficient change and independency in explanatory variables and effective data processing to remove measurement noise are important for precise estimation.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001075000","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-1324","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 飛行実験部"},{"subitem_text_value":"航空宇宙技術研究所 飛行実験部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Flight Research Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Flight Research Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"増位, 和也"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"塚野, 雄吉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Masui, Kazuya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsukano, Yukichi","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":"naltr01324.pdf","filesize":[{"value":"2.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01324.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39959/files/naltr01324.pdf"},"version_id":"7e517eb1-53b3-4baa-855e-1c94054a5e88"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"クインエア航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"縦空力微係数","subitem_subject_scheme":"Other"},{"subitem_subject":"パラメータ推定","subitem_subject_scheme":"Other"},{"subitem_subject":"最小二乗法","subitem_subject_scheme":"Other"},{"subitem_subject":"全最小二乗法","subitem_subject_scheme":"Other"},{"subitem_subject":"TLS法","subitem_subject_scheme":"Other"},{"subitem_subject":"方程式誤差法","subitem_subject_scheme":"Other"},{"subitem_subject":"周波数応答法","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験データ処理","subitem_subject_scheme":"Other"},{"subitem_subject":"データ処理","subitem_subject_scheme":"Other"},{"subitem_subject":"インフライト・シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"モデル追従制御則","subitem_subject_scheme":"Other"},{"subitem_subject":"縦線形空力モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"誤差解析","subitem_subject_scheme":"Other"},{"subitem_subject":"Queen Air plane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"longitudinal aerodynamic derivative","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"parameter estimation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"least square method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"total least square method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"TLS method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"equation error method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"frequency response method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test data processing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"data processing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"inflight simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"model following control law","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"longitudinal linear aerodynamic model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"error analysis","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":"方程式誤差法によるクインエア機の空力微係数推定","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"方程式誤差法によるクインエア機の空力微係数推定"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"39959","relation_version_is_last":true,"title":["方程式誤差法によるクインエア機の空力微係数推定"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:17:49.728897+00:00"}