WEKO3
アイテム
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火星探査機用回転翼の超低レイノルズ数空力特性
https://jaxa.repo.nii.ac.jp/records/14656
https://jaxa.repo.nii.ac.jp/records/14656ee5c4c63-b61b-4733-aa1c-6b577c7f9394
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 火星探査機用回転翼の超低レイノルズ数空力特性 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力特性 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超低レイノルズ数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 回転翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 火星探査機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前縁剥離渦 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ピッチ角 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Knudsen数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 翼素運動量理論 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic characteristic | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ultra-low Reynolds number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rotary wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mars exploration rotorcraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | leading edge vortex | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pitch angle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Knudsen number | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | blade element momentum theory | |||||
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 | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Experimental study on aerodynamic characteristics of rotary wings for a miniature Mars exploration rotorcraft at ultra-low Reynolds numbers | |||||
著者 |
都築, 範明
× 都築, 範明× 佐藤, 俊逸× 安部, 隆士× Tsuzuki, Noriaki× Sato, Shunichi× Abe, Takashi |
|||||
著者所属 | ||||||
東京大学 大学院 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo Graduate School | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) | |||||
書誌情報 |
宇宙航行の力学シンポジウム 平成15年度 en : Symposium on Flight Mechanics and Astrodynamics 2003 p. 39-42, 発行日 2004-05 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Understanding on an efficient small-scale hovering rotor is required to make a miniature rotorcraft probe to explore the Martian surface. For this purpose, an experimental measurement of the aerodynamic characteristics of a small-scale rotor at ultra-low Reynolds numbers (Re = 2,000, 4,000, 8,000) was performed. The experimental results show that the airflow around the rotor is subject to the leading-edge vortex (LEV) and that the Blade Element Momentum Theory (BEMT) is valid at moderate collective pitch angles and that the capability of the rotor required for the rotorcraft probe is within reach. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0047120011 |