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長寿命ロケットエンジンのための機構要素研究
https://jaxa.repo.nii.ac.jp/records/16720
https://jaxa.repo.nii.ac.jp/records/16720ba42a930-67ec-4d08-9146-562eb30c18a9
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 | 長寿命ロケットエンジンのための機構要素研究 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Rocket Engine, Turbopump, Bearing And Axial Seal | |||||
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 | A study of mechanical elements for durable rocket engine | |||||
著者 |
高田, 仁志
× 高田, 仁志× 菊池, 正孝× 須藤, 孝幸× 渡辺, 義明× 吉田, 誠× Takada, Satoshi× Kikuchi, Masataka× Sudo, Takayuki× Watanabe, Yoshiaki× Yoshida, Makoto |
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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 | ||||||
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 | ||||||
宇宙航空研究開発機構 | ||||||
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) | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency (JAXA) | ||||||
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 | In JAXA, mechanical elements are studied for a reusable rocket engine. Especially, an accurate estimation of lifetime of a turbopump bearing and grasp of operational limit of a shaft seal are required. However, fundamental performances (maximum rotational speed, minimum flow rate, power loss, durability, etc.) of those components were not grasped. Purpose of this study is to grasp a critical performance of mechanical seals and hybrid ball bearings of turbopump. In this study, minimum flow rate of hybrid ceramic bearing was measured in liquid hydrogen. Normal operations of bearings are possible under conditions of more than 70,000 rpm of rotational speed and more than 0.2 liter/s of coolant flow rate. And it was found that mechanical seal nose wear rate was accelerated by the existence of wear powder on the contact surface, and the duration of the seal was not sufficient for reusable rocket engine. But a life cycle of mechanical seal extended drastically when a contact surface was cleaned up every 100 km of sliding distance. | |||||
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: AA0064292027 |