{"created":"2023-06-20T15:13:37.510492+00:00","id":43557,"links":{},"metadata":{"_buckets":{"deposit":"08f85e03-dc7b-4782-b720-8744a1717588"},"_deposit":{"created_by":1,"id":"43557","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"43557"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00043557","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["464210","464215","464227","464236","464216","464231","464224","464230","464234","464225","464218","464233","464212","464226","464206","464235","464217","464205","464207","464208","464239","464209","464229","464238","464228","464240","464232","464237","464219","464222","464220","464223","464211","464214","464213","464221"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"ON THE HYPERSONIC FLIGHT EXPERIMENT (HYFLEX) PROJECT"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-09","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"60","bibliographicPageStart":"49","bibliographicVolumeNumber":"24","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory SP-24","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"小型の実験機を用いた極超音速飛行実験(HYFLEX)計画がHOPE開発研究の一環として航空宇宙技術研究所と宇宙開発事業団の協力の下で進められている。実験機は2段式のJ-1ロケットにより高度110km、速度約3.9km/sで分離され、滑空飛行中に空力加熱計測、熱防護系評価、誘導制御技術評価等のための飛行データを取得する。本論文は、実験計画の目的、概要、実験機の空力特性、サブシステム、誘導制御則、実験計測及び開発計画等について述べる。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A hypersonic flight experiment project of a lifting-body type vehicle named HYFLEX (Hypersonic Flight Experiment) is in progress by the National Aerospace Laboratory and the National Space Development Agency as a part of collaborative activities for the development of HOPE. The vehicle will be separated at a velocity of about 3.9km/s from the second stage of the J-I launcher and will acquire flight data during its glide descent. This paper describes the purpose and the outline of the experiment, aerodynamic characteristics, sub-components, and guidance and control of the vehicle, as well as onboard data acquisition. and schedule.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALSP0024005","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 SP-24","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 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