WEKO3
アイテム
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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
https://jaxa.repo.nii.ac.jp/records/21709
https://jaxa.repo.nii.ac.jp/records/21709a51b385c-c91e-4246-b836-987f5fd8227a
Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2016-06-17 | |||||
タイトル | ||||||
タイトル | 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 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Multidisciplinary Design Optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Hypersonic Flight Experiment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Sounding Rocket | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Suborbital Re-Entry | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
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 | Multidisciplinary Vehicle Shape and Trajectory Optimization for a Hypersonic Flight Experiment Using a Sounding Rocket | |||||
著者 |
藤川, 貴弘
× 藤川, 貴弘× 土屋, 武司× 田口, 秀之× Fujikawa, Takahiro× Tsuchiya, Takeshi× Taguchi, Hideyuki |
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出版者 | ||||||
出版者 | Japan Society for Aeronautical and Space Sciences | |||||
出版者(英) | ||||||
出版者 | 日本航空宇宙学会 | |||||
書誌情報 |
日本航空宇宙学会論文集 en : Journal of the Japan Society for Aeronautical and Space Sciences 巻 64, 号 3, p. 182(38)-188(44), 発行日 2016-06-05 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 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. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: 図版あり | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains illustrations | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1344-6460 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11307372 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: DS1640080005 |