{"created":"2023-06-20T15:10:59.604837+00:00","id":40569,"links":{},"metadata":{"_buckets":{"deposit":"2b1da3d9-ae3a-4b89-80aa-35dc408a324d"},"_deposit":{"created_by":1,"id":"40569","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"40569"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00040569","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["448731","448732","448733","448729","448728","448730"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Feasibility study of lateral/directional control of winged re-entry vehicle with split elevons"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"24","bibliographicPageStart":"1","bibliographicVolumeNumber":"1379","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":"最近のいくつかの航空機では、垂直尾翼をなくし、ドラッグラダーなどを用いた能動的制御によって方向安定を得る試みがなされている。宇宙往還機でもこのような形態にすれば、特に構造上有利である。ここでは、宇宙開発事業団と航空宇宙技術研究所が共同研究している無人有翼往還機からティップフィンを除き、スプリットエレボンを付加した形態での風洞試験結果を用いてMDM/MDP(多数遅れモデル/多数設計点)法によって横/方向の飛行制御則を設計し、その評価を行う。ティップフィンをなくすことにより、機体の方向安定は悪化するが、スプリットエレボンを用いた制御によりある程度の安定性、制御性を得ることができる。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Recently, several aircraft which lack vertical tails have been developed, the so-called 'tailless aircraft'. For directional stability, these aircraft are actively controlled using devices such as drag rudders. In the case of winged reentry vehicles, it will be useful to apply this technology, especially from the structural viewpoint. In this paper, a tailless configuration of the HOPE-X (H-2 Orbiting Plane Experimental), a winged reentry vehicle being developed by the National Aerospace Laboratory and National Space Development Agency of Japan, was analyzed. Lateral/directional control laws were designed for this configuration using the MDM (Multiple Delay Model)/MDP (Multiple Design Point) approach. Though directional stability degenerated without fins, the vehicle was stabilized and controlled to a certain degree using split elevons.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001804000","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-1379","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 制御部"},{"subitem_text_value":"航空宇宙技術研究所 制御部"},{"subitem_text_value":"宇宙開発事業団"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Control Systems Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Control Systems Division"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"塚本, 太郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"柳原, 正明"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"水藤, 貴靖"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsukamoto, Taro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yanagihara, Masaaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Suito, Takanobu","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":"naltr0001379.pdf","filesize":[{"value":"420.2 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001379.pdf","url":"https://jaxa.repo.nii.ac.jp/record/40569/files/naltr0001379.pdf"},"version_id":"b7f6d97b-95b0-4b9e-bb5d-05ac38953dea"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"スプリットエレボン","subitem_subject_scheme":"Other"},{"subitem_subject":"有翼宇宙往還機","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行制御","subitem_subject_scheme":"Other"},{"subitem_subject":"ティップフィン","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行安定性","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞実験","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙往還技術試験機","subitem_subject_scheme":"Other"},{"subitem_subject":"垂直尾翼","subitem_subject_scheme":"Other"},{"subitem_subject":"制御系設計","subitem_subject_scheme":"Other"},{"subitem_subject":"計算機シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"姿勢制御","subitem_subject_scheme":"Other"},{"subitem_subject":"姿勢安定性","subitem_subject_scheme":"Other"},{"subitem_subject":"split elevon","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"winged reentry vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"tip fin","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight stability","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"H 2 Orbiting Plane Experimental","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vertical tail","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control system design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computer simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"attitude control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"attitude stability","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":"スプリットエレボンを用いた有翼宇宙往還機の横/方向制御の検討","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"スプリットエレボンを用いた有翼宇宙往還機の横/方向制御の検討"}]},"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":"40569","relation_version_is_last":true,"title":["スプリットエレボンを用いた有翼宇宙往還機の横/方向制御の検討"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:15:07.066034+00:00"}