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高々度気球を用いた予冷ターボジェットエンジン飛行実証機の空力性能
https://jaxa.repo.nii.ac.jp/records/5426
https://jaxa.repo.nii.ac.jp/records/54260644628d-6d01-422d-94c8-d08212dcc193
名前 / ファイル | ライセンス | アクション |
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64303024.pdf (2.0 MB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 高々度気球を用いた予冷ターボジェットエンジン飛行実証機の空力性能 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Aerodynamics, Supersonic, Demonstrator, Turbojet Engine, High-altitude Balloon | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Aerodynamics of pre-cooled turbojet engine demonstrator using high-altitude balloon | |||||
著者 |
藤田, 和央
× 藤田, 和央× 宮路, 幸二× 沢井, 秀次郎× 小林, 弘明× 坪井, 伸幸× Fujita, Kazuhisa× Miyaji, Koji× Sawai, Shujiro× Kobayashi, Hiroaki× Tsuboi, Nobuyuki |
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著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
横浜国立大学 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Yokohama National University | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料: 第40回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2008論文集 en : JAXA Special Publication: Proceedings fo 40th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2008 巻 JAXA-SP-08-009, 発行日 2009-02-27 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第40回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2008. 会期: 2008年6月12日-6月13日. 会場: 東北大学片平キャンパス | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The Balloon-based Operation Vehicle (BOV) originally developed for the micro-gravity experiments is modified as a supersonic flight demonstrator of a sub-scale precooled turbojet engine developed in JAXA. In the supersonic flight demonstration, the vehicle is raised by a high-altitude balloon up to a 40 km altitude and dropped to accelerate the vehicle to a supersonic velocity. To extend the flight time for an engine combustion test in the supersonic environments, the vehicle is redesigned in a wing-body configuration with a main delta wing and movable vertical and horizontal tail wings so that it can be pulled out above an altitude of 5 km. As a result, the vehicle is capable of reaching the maximum flight Mach number of 2 with the dynamic pressure of 25 kPa at an altitude of 17 km, realizing the engine test time longer than 30 sec. The flight demonstration is currently scheduled in 2009. In this article, an overview of the aerodynamic characteristics of the flight demonstrator and the flight trajectory plan is presented. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064303024 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-08-009 |