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Hot-Firing Test of Methane-Fueled Rocket Engine under High Altitude Condition
https://jaxa.repo.nii.ac.jp/records/38629
https://jaxa.repo.nii.ac.jp/records/386298cf4beda-ff4c-46eb-87b4-ecf23fade9f4
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Hot-Firing Test of Methane-Fueled Rocket Engine under High Altitude Condition | |||||
言語 | ||||||
言語 | eng | |||||
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 | |||||
著者 |
植田, 修一
× 植田, 修一× 冨田, 健夫× 小野寺, 卓郎× 久保田, 勲× Kano, Yasuhito× 宗永, 隆男× Ueda, Shuichi× Tomita, Takeo× Onodera, Takuo× Kubota, Isao× Kano, Yasuhito× Munenaga, Takao |
|||||
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 | ||||||
株式会社IHIエアロスペース | ||||||
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) | ||||||
著者所属(英) | ||||||
en | ||||||
IHI AEROSPACE Co.,Ltd. | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency(JAXA) | ||||||
出版者(英) | ||||||
出版者 | American Institute of Aeronautics and Astronautics(AIAA) | |||||
書誌情報 | 発行日 2013-07 | |||||
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 | Joint Propulsion Conferences, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference(July 14-17, 2013.), San Jose, California, United States. | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Fundamental research activities have been conducted on LOX/Methane rocket engine to achieve higher performance for upper stage system of a middle class launch vehicle. The effects of combustion chamber pressure and mixture ratio on engine performance were demonstrated using a subscale engine test model in the High Altitude Test Stand. Highly expanded nozzle, area ratio of 71 was used in the HATS test to obtain thrust increment generated in the nozzle part. The combustion chamber pressure was changed as a parameter from 1 MPa to 3 MPa, mixture ratio was changed as a parameter from 2.8 to 3.6. Test results shows that specific impulse and thrust performance are increasing with combustion chamber pressure. On the other hand, effects of mixture ratio were small within the test condition. | |||||
DOI | ||||||
識別子タイプ | DOI | |||||
関連識別子 | http://dx.doi.org/10.2514/6.2013-4056 | |||||
関連名称 | info:doi/10.2514/6.2013-4056 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AC1400050000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: AIAA2013-4056 |