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An Experimental Study of Spray Thruster
https://jaxa.repo.nii.ac.jp/records/31377
https://jaxa.repo.nii.ac.jp/records/3137707201149-c8a1-4fab-bd32-126d04902349
名前 / ファイル | ライセンス | アクション |
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SA0034977.pdf (2.9 MB)
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Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | An Experimental Study of Spray Thruster | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Spray thruster | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Evaporation process | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Relaxation phenomena | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Equilibrium flow model (EFM) | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Partially frozen flow model (PFFM) | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | departmental bulletin paper | |||||
著者 |
DOI, Takao
× DOI, Takao× YASUDA, Seiichi× AKIBA, Ryojiro |
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出版者 | ||||||
出版者 | 宇宙科学研究所 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science | |||||
書誌情報 |
en : The Institute of Space and Astronautical Science report 巻 613, p. 1-56, 発行日 1984-09 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The forced evaporation of liquid is employed to produce working fluid for a thermal thruster system called "Spray Thruster." The experimental model of spray thruster has been tested in the wide range of the mass flow rate using Ethyl Ether, Pentane and Furan. The spray thruster is operated well in a vacuum environment without any energy additions. The exhaust stream consists of vapor containing droplets, the mass fraction of which is in the range from 0.8 to 0.9. The Isp reaches 28 seconds at the propellant tank temperature of 20℃ for Ethyl Ether. The analysis of the nozzle flow shows that an equilibrium flow model and partially frozen flow model explain properly the measured thrust performance in the small and large mass flow rate operations, respectively. The effects of chemical properties of propellant, nozzle scale, propellant tank temperature and structural mass of the system on the thrust performance have been investigated in detail to obtain the fundamental design aspects. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0285-6808 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10632072 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0034977000 |