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低コスト燃料を用いたサブスケールハイブリッドロケットエンジンの燃焼特性
https://jaxa.repo.nii.ac.jp/records/16203
https://jaxa.repo.nii.ac.jp/records/16203ef97e5c1-a600-4523-8ac8-0513c59067a4
名前 / ファイル | ライセンス | アクション |
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61856067.pdf (371.3 kB)
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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 | 低コスト燃料を用いたサブスケールハイブリッドロケットエンジンの燃焼特性 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Low cost fuel | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Reusable Hybrid Rocket Engine | |||||
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 | Study of Electric-motor Turbo Pump for Reusable Hybrid Rocket Engine | |||||
著者 |
五十嵐, 真二
× 五十嵐, 真二× 福地, 亜宝郎× 山本, 研吾× Igarashi, Shinji× Fukuchi, Aporo× Yamamoto, Kengo |
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著者所属 | ||||||
株式会社IHIエアロスペース | ||||||
著者所属 | ||||||
株式会社IHIエアロスペース | ||||||
著者所属 | ||||||
株式会社IHIエアロスペース | ||||||
著者所属(英) | ||||||
en | ||||||
IHI AEROSPACE Co. Ltd. | ||||||
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 | 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS) | |||||
書誌情報 |
平成24年度宇宙輸送シンポジウム: 講演集録 en : Proceedings of Space Transportation Symposium: FY2012 発行日 2013-01 |
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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24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | A hybrid rocket engine is suitable for the reusable launch vehicle in low cost and safety. The authors study the hybrid rocket engine with a low cost fuel targeting the reusable launch vehicle like the Space Ship 2. For developing large-scale engines for the reusable launch vehicle, we conducted the hot firing tests of sub-scale hybrid rocket engines to obtain combustion characteristics of the low cost fuel. The fuel grains were multi-port type and wagon-wheel type, and the size of the grains was 160 mm in diameter and 350 mm in length, and the oxidizer was LOX. It was found that the ignition and combustion were very stable. We confirmed the burning time that more than 20-second duration was achieved. | |||||
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 | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: PDF | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: PDF | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0061856067 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: STCP-2012-067 |