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再使用観測ロケット主推進系の進捗状況
https://jaxa.repo.nii.ac.jp/records/16716
https://jaxa.repo.nii.ac.jp/records/16716d872ee53-e2aa-4312-97b6-5223886ccc26
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 | 再使用観測ロケット主推進系の進捗状況 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Space Transportation, Reusable Rocket Engine, Health management, Throttling | |||||
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 status of main engine of reusable sounding rocket | |||||
著者 |
吉田, 誠
× 吉田, 誠× 成尾, 芳博× 丹生, 謙一× Yoshida, Makoto× Naruo, Yoshihiro× Niu, Kenichi |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 | ||||||
著者所属 | ||||||
三菱重工業 | ||||||
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 | ||||||
Mitsubishi Heavy Industries | ||||||
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 |
|||||
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 40 kN rocket engine development has been initiated relating to the reusable sounding rocket, which is also developed in Japan. This rocket vertically takes off, reaches to 100 km altitude, lands vertically on the launch site and is launched again within several days. This rocket will provide observation mission chances with low cost and with quickness utilizing the advantages of reusability. This program has been authorized as a technology demonstration phase, and most of the technologies required for the vehicle are to be demonstrated in a few years. In order to realize this rocket concept, the engines installed on the rocket should have features of reusability, long life, deep throttling and health monitoring. Those have not yet been established in Japanese rocket engines. In this paper, development status of the engine is mentioned, including fundamental design and engineering tests of turbopump bearing and seal. Also program prospect relating with the other engine development programs in Japan are also presented. | |||||
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: AA0064292023 |