{"created":"2023-06-20T14:39:00.234973+00:00","id":5667,"links":{},"metadata":{"_buckets":{"deposit":"633e9f4d-dee0-480b-8d51-34e9caac8b14"},"_deposit":{"created_by":1,"id":"5667","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5667"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005667","sets":["1887:1891","9:789:972:991"]},"author_link":["27779","27778"],"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-02-29","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"130","bibliographicPageStart":"121","bibliographicVolumeNumber":"JAXA-SP-07-008E","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 Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The present paper treats the flutter suppression of composite plate wings with segmented piezoelectric sensors and actuators. First, fundamental mechanism of flutter suppression based on the measurement and control of specific vibration modes is examined for composite plate wings. Aeroelastic analysis of composite plates is based on the finite element method and the subsonic unsteady lifting surface theory. PolyVinyliDene Fluoride (PVDF) sensors are used as a modal sensor for measurement of specific modal displacements, which is constructed by optimizing the sensor gain distribution. Lead Zirconate Titanate (PZT) actuators are also used as actuators for flutter suppression, which generate the modal forces for specific modes with the pseudo-optimal output feedback control law based on the Linear Quadratic Regulator (LQR) control theory. The importance of the measurement and control of the first torsional vibration mode for the flutter suppression is clarified through the numerical examples. Next, validity of the flutter suppression based on the optimal placement of a limited number of sensors and actuators is examined for composite plate wings. Modal sensor for measurement of the modal displacement of the first torsional vibration mode is designed by the optimal placement of PVDF sensors based on the minimization criterion of observation spillover. Actuation system to generate the modal force for the first torsional vibration mode is designed by the optimal placement of PZT actuators based on the minimization criterion of control spillover. The effectiveness of optimal placement of sensors and actuators in the flutter suppression is clarified through the numerical examples.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063824012","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-07-008E","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"}]},"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_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東北大学 大学院工学研究科"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tohoku University Graduate School of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"亀山, 正樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kameyama, Masaki","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":"2020-01-16"}],"displaytype":"detail","filename":"63824012.pdf","filesize":[{"value":"1.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63824012.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5667/files/63824012.pdf"},"version_id":"e8af3849-95ed-4850-b3ab-21a73dcb8c57"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力弾性制御","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ解析","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速フラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"積層","subitem_subject_scheme":"Other"},{"subitem_subject":"圧電アクチュエータ","subitem_subject_scheme":"Other"},{"subitem_subject":"有限要素法","subitem_subject_scheme":"Other"},{"subitem_subject":"ねじり振動","subitem_subject_scheme":"Other"},{"subitem_subject":"フィードバック制御","subitem_subject_scheme":"Other"},{"subitem_subject":"チタン酸ジルコン酸鉛","subitem_subject_scheme":"Other"},{"subitem_subject":"翼振動","subitem_subject_scheme":"Other"},{"subitem_subject":"aeroelastic control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminate","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"piezoelectric actuator","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"finite element method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"torsional vibration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"feedback control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lead zirconate titanate","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing oscillation","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":"Aeroelastic control of composite plate wings based on the optimal placement of sensors and actuators","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Aeroelastic control of composite plate wings based on the optimal placement of sensors and actuators","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["991","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"5667","relation_version_is_last":true,"title":["Aeroelastic control of composite plate wings based on the optimal placement of sensors and actuators"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:09:42.725198+00:00"}