{"created":"2023-06-20T14:36:05.371336+00:00","id":2390,"links":{},"metadata":{"_buckets":{"deposit":"fcebe15e-46b9-458e-820a-ae580d7065e0"},"_deposit":{"created_by":1,"id":"2390","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2390"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002390","sets":["1887:1893","9:10:309:362"]},"author_link":["5970","5971","5969","5968","5973","5972"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Guidance and control law design for High Speed Flight Demonstration Phase 2"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-10-29","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-04-006","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"高速飛行実証フェーズ2は宇宙往還機の遷音速領域での空力特性を取得するための飛行実験である。本実験においては、実験機は高層気球によって高度20から30kmに打ち上げられ、分離されて加速し、遷音速での滑空飛行を実現する。有用な空力データを取得するために誘導制御系に対しては実験機のマッハ数を一定に保ちつつ迎角を準静的に変化させることが要求される。また、データ取得後は、選択された回収目標点に適切な終端条件で到達するように実験機を誘導しなければならない。ここでは、このような要求を満足するための誘導制御系の設計について記述する。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The High-Speed Flight Demonstration Phase 2 is a flight experiment program to investigate the transonic aerodynamic characteristics of the HOPE-X winged re-entry vehicle. A vehicle based on a scaled HOPE-X configuration is lifted by stratospheric balloon to an altitude of 20 to 30-km, from where it will be released into free-fall and accelerate to transonic speeds. To acquire useful aerodynamic data, the guidance and control system must maintain the vehicle's Mach number at a constant value while varying its angle of attack quasi-statically. After data acquisition, the vehicle must be guided to a selected recovery point and attain suitable recovery parameters. In this paper, the design of a guidance and control law to achieve these requirements is described.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0048058000","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-RR-04-006","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":"1349-1113","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":"AA1192675X","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 総合技術研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"}]},"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 Institute of Space Technology and Aeronautics"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"塚本, 太郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"鈴木, 広一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"二宮, 哲次郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsukamoto, Taro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Suzuki, Hirokazu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ninomiya, Tetsujiro","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":"48058000.pdf","filesize":[{"value":"8.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"48058000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2390/files/48058000.pdf"},"version_id":"9b08a775-25b6-4989-bf5f-fc726bd4e95e"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"高速飛行実証","subitem_subject_scheme":"Other"},{"subitem_subject":"有翼再突入機","subitem_subject_scheme":"Other"},{"subitem_subject":"誘導","subitem_subject_scheme":"Other"},{"subitem_subject":"制御","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速飛行","subitem_subject_scheme":"Other"},{"subitem_subject":"仰角","subitem_subject_scheme":"Other"},{"subitem_subject":"気球","subitem_subject_scheme":"Other"},{"subitem_subject":"high speed flight demonstration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"winged reentry vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"guidance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic flight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angle of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"balloon","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":"高速飛行実証機フェーズ2の誘導制御則設計","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"高速飛行実証機フェーズ2の誘導制御則設計"}]},"item_type_id":"3","owner":"1","path":["362","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2390","relation_version_is_last":true,"title":["高速飛行実証機フェーズ2の誘導制御則設計"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:23:24.816641+00:00"}