WEKO3
アイテム
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2段燃焼型ハイブリッドエンジンの検討
https://jaxa.repo.nii.ac.jp/records/17429
https://jaxa.repo.nii.ac.jp/records/17429e44e05c2-693e-476b-8911-d8f2c95dbdce
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 | 2段燃焼型ハイブリッドエンジンの検討 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ハイブリッドロケットエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 2段燃焼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 小型衛星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙機打上げ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 低高度地球周回軌道 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再利用型宇宙輸送システム | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hybrid rocket engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | two-stage combustion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | microsatellite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | spacecraft launching | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | low earth orbit | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reusable space transport system | |||||
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 | Preliminary assessment of staged-combustion hybrid rocket | |||||
著者 |
藤田, 和央
× 藤田, 和央× 野中, 聡× 小川, 博之× 中島, 俊× 秋葉, 鐐二郎× 山本, 洋一× 山本, 研吾× Fujita, Kazuhisa× Nonaka, Satoshi× Ogawa, Hiroyuki× Nakajima, Takashi× Akiba, Ryojiro× Yamamoto, Yoichi× Yamamoto, Kengo |
|||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
宇宙科学研究所 | ||||||
著者所属 | ||||||
無人宇宙実験システム研究開発機構 | ||||||
著者所属 | ||||||
アイ・エイチ・アイ・エアロスペース | ||||||
著者所属 | ||||||
アイ・エイチ・アイ・エアロスペース | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Astronautical Science | ||||||
著者所属(英) | ||||||
en | ||||||
Institute for Unmanned Space Experiment Free Flyer | ||||||
著者所属(英) | ||||||
en | ||||||
IHI Aerospace Co. Ltd. | ||||||
著者所属(英) | ||||||
en | ||||||
IHI Aerospace Co. Ltd. | ||||||
出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | The Institute of Space and Astronautical Science (ISAS) | |||||
書誌情報 |
宇宙輸送シンポジウム 平成13年度 en : Proceedings of Space Transportation Symposium FY2001 p. 1-4, 発行日 2002-04 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Preliminary assessment of a staged-combustion hybrid rocket engine is done, and its application to a micro-satellite launching rocket is studied. The staged-combustion hybrid engine is based on a new concept of two-stage combustion, which has advantages of propellant flexibility, low cost, operation safety, high performance, and low environmental pollution. A case study has shown that an SS520-class sounding rocket equipped with the staged-combustion hybrid engine for the 1st stage is capable of launching a 10-kg-class satellite to LEO. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0033392001 |