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アイテム
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ローリングのない三次元物体飛行や編隊飛行が可能なバリスティックレンジの開発
https://jaxa.repo.nii.ac.jp/records/16712
https://jaxa.repo.nii.ac.jp/records/16712c765f2b0-2d25-4841-b5be-28d32a9c4134
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 | ローリングのない三次元物体飛行や編隊飛行が可能なバリスティックレンジの開発 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Shock Wave, Ballistic Range, Sonic Boom, N-wave | |||||
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 | Development of ballistic range for rolling-less 3D projectile and formation flight, 2008 JAPAN | |||||
著者 |
菊池, 康介
× 菊池, 康介× 清水, 克也× 松田, 淳× 佐宗, 章弘× Kikuchi, Kosuke× Shimizu, Katsuya× Matsuda, Atsushi× Sasoh, Akihiro |
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著者所属 | ||||||
名古屋大学大学院 | ||||||
著者所属 | ||||||
名古屋大学大学院 | ||||||
著者所属 | ||||||
名古屋大学 | ||||||
著者所属 | ||||||
名古屋大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Graduate School, Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Graduate School, Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University | ||||||
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) | |||||
書誌情報 |
宇宙輸送シンポジウム: 講演集録 en : Proceedings of Space Transportation Symposium 巻 平成20年度, 発行日 2009 |
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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 | 平成20年度宇宙輸送シンポジウム(2009年1月19日-20日, 宇宙航空研究開発機構宇宙科学研究本部) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A squared cross section ballistic range has been developed. It prevents flying objects to roll in the tube. It consists of a highpressure chamber (1.5 m), acceleration tubes (3 m), a ventilation tube (1.8 m), a launching tube (1.4 m), and a test chamber (3.2 m). At the ventilation tube, the precursor shock wave that is generated by the sabot when it passes through the acceleration tube and the driver gas are vented. At the launching tube, only the sabot affected by fore shock wave pressure that cause decelerating. On the other hand, the drag to the projectile is negligible. Therefore, projectile is separated from sabot in the launching tube. With this ballistic range, supersonic flight experiment of various shapes projectiles have been conducted. | |||||
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 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10324301 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064292019 |