{"created":"2023-06-20T14:53:31.563646+00:00","id":21709,"links":{},"metadata":{"_buckets":{"deposit":"df8375f1-5430-4f0e-a1a9-af6962cfcf68"},"_deposit":{"created_by":1,"id":"21709","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"21709"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00021709","sets":["1887:1888"]},"author_link":["203817","203812","203814","203816","203813","203815"],"item_7_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Multidisciplinary Vehicle Shape and Trajectory Optimization for a Hypersonic Flight Experiment Using a Sounding Rocket"}]},"item_7_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2016-06-05","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"3","bibliographicPageEnd":"188(44)","bibliographicPageStart":"182(38)","bibliographicVolumeNumber":"64","bibliographic_titles":[{"bibliographic_title":"日本航空宇宙学会論文集"},{"bibliographic_title":"Journal of the Japan Society for Aeronautical and Space Sciences","bibliographic_titleLang":"en"}]}]},"item_7_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A hypersonic flight experiment using an S-520 sounding rocket as a launch vehicle is planned in order to demonstrate integrated control technologies for vehicle attitude and propulsion. Its primary mission requirement is to achieve experimental conditions for the installed ramjet engines (constant 50kPa dynamic pressure at not less than Mach 4.0) for a sufficient duration. In this paper, a feasibility study of the flight experiment is conducted using a multidisciplinary design optimization technique. The experimental vehicle shape and the flight trajectory are simultaneously optimized so that the duration of the required experimental conditions is maximized. In particular, consideration is given to the trade-off between a longitudinal static margin and trimming capability since it is a major concern for flight control of winged suborbital re-entry vehicles. Gross mass and launch angle of the sounding rocket are varied to obtain vehicle shapes and associated trajectories that successfully satisfy the mission requirement.","subitem_description_type":"Other"}]},"item_7_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: 図版あり","subitem_description_type":"Other"}]},"item_7_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains illustrations","subitem_description_type":"Other"}]},"item_7_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: DS1640080005","subitem_description_type":"Other"}]},"item_7_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"Japan Society for Aeronautical and Space Sciences"}]},"item_7_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"日本航空宇宙学会"}]},"item_7_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1344-6460","subitem_source_identifier_type":"ISSN"}]},"item_7_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA11307372","subitem_source_identifier_type":"NCID"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"metadata only access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_14cb"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"藤川, 貴弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"土屋, 武司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"田口, 秀之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujikawa, Takahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsuchiya, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Taguchi, Hideyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Multidisciplinary Design Optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Hypersonic Flight Experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Sounding Rocket","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Suborbital Re-Entry","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":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"観測ロケット利用による極超音速飛行実験に向けた実験機形状・飛行軌道の複合領域最適設計","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"観測ロケット利用による極超音速飛行実験に向けた実験機形状・飛行軌道の複合領域最適設計"}]},"item_type_id":"7","owner":"1","path":["1888"],"pubdate":{"attribute_name":"公開日","attribute_value":"2016-06-17"},"publish_date":"2016-06-17","publish_status":"0","recid":"21709","relation_version_is_last":true,"title":["観測ロケット利用による極超音速飛行実験に向けた実験機形状・飛行軌道の複合領域最適設計"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T03:31:35.101453+00:00"}