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再使用型TSTO 軌道往還輸送システムのロケット推進系システム検討
https://jaxa.repo.nii.ac.jp/records/38600
https://jaxa.repo.nii.ac.jp/records/38600ade5fbe4-d2b1-4ad4-8d1a-681cd5a8e9a6
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 | 再使用型TSTO 軌道往還輸送システムのロケット推進系システム検討 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | TSTO System; Reusable Rocket Engine; System Study | |||||
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 | Study on Rocket Propulsion Systems for Reusable TSTO System | |||||
著者 |
木村, 俊哉
× 木村, 俊哉× 佐藤, 正喜× 吉田, 誠× 石本, 真二× Kimura, Toshiya× Sato, Masaki× Yoshida, Makoto× Ishimoto, Shinji |
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著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属 | ||||||
宇宙航空研究開発機構(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者 | ||||||
出版者 | 日本航空宇宙学会(JSASS) | |||||
出版者(英) | ||||||
出版者 | The Japan Society for Aeronautical and Space Sciences(JSASS) | |||||
書誌情報 |
第57回宇宙科学技術連合講演会講演集 en : Proceedings of 57th Space Sciences and Technology Conference 発行日 2013-10 |
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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 | 第57回宇宙科学技術連合講演会(2013年10月9日-11日. 米子コンベンションセンター(BiG SHiP)), 米子市, 鳥取県 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | As one of future space transportation systems, a fully reusable TSTO system to LEO has been studied in JAXA. Severalpossible combinations for vehicles and engines of this TSTO system have been under consideration, As a propulsionsystem, an ordinary rocket engine, an aerospike nozzle engine, and a RBCC (Rocket Based Combined Cycle) engine aremain candidates. In this paper, we report the present status of our system study for the first and second stages of the TSTOsystem using an ordinary rocket engine. The concept of TDM (Total design management) is applied in the design of theengines in order to make the study efficient and to avoid unnecessary works when the system requirements to the enginewill be changed. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AC1400016000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JSASS-2013-4274 |