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自由飛行体発射装置とその特性に関する実験
https://jaxa.repo.nii.ac.jp/records/32266
https://jaxa.repo.nii.ac.jp/records/322668dd35a35-07ea-406c-a6f5-ed99cf4eb58b
名前 / ファイル | ライセンス | アクション |
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SA0125432.pdf (1.6 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 | ||||||
タイトル | 自由飛行体発射装置とその特性に関する実験 | |||||
言語 | ||||||
言語 | jpn | |||||
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 | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Free-Piston-Driven Range and its Characteristic Performance | |||||
著者 |
小口, 伯郎
× 小口, 伯郎× 船曳, 勝之× 佐藤, 俊逸× OGUCHI, Hakuro× FUNABIKI, Katsushi× SATO, Shun-ichi |
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著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属 | ||||||
東京大学宇宙航空研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
著者所属(英) | ||||||
en | ||||||
Institute of Space and Aeroautical Science University of Tokyo | ||||||
出版者 | ||||||
出版者 | 東京大学宇宙航空研究所 | |||||
書誌情報 |
東京大学宇宙航空研究所報告 巻 7, 号 2_B, p. 427-436, 発行日 1971-06 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | ピストン駆動方式による自由飛行体発射装置の機構,特性および基本的実験手法のいくつかについて報告されている.全長約19mで,高圧部,ピストン走行部および試験筒(50cmφ,10m長)よりなり,発射管は内径5,10,22.2mmの3種類が用意された.最高駆動圧は約400kg/cm2で,5mmφナイロン製球に対し最高到達速度は2.5 km/secであった.試験筒の内圧は常圧より10^<-5> Torrまで可変で所要の排気系をもっている.駆動圧の測定,模型の発射速度と飛行速度の測定がなされ,特に試験筒内圧の変化による,速度の減衰が明らかにされている.また影写真およびシュリーレン法により,平行平板間を飛行する球による流れの様模が観察されている. | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The present report is concerned with the characteristic performance of free-piston-driven range and some of the associated measurements. This facility consists of high pressure chamber (2.8 m long), free-piston barrel (5m long, 8cm in diam) and flight test chamber (10m long, 50cm in diam), which can be evacuated down to 10^<-5> Torr. An interchangeable use of different sizes of launchers is deviced to be made for various flight models. Maximum attainable pressure at the end of free-piston barrel is designed to be about 400kg/cm^2, and thus flight velocity is moderately ranged within about 3km/sec. The flight velocity at launcher exit and test sections is measured for cases of various test chamber pressures, and as a result the basic performance of the present facility is clarified. Moreover, an optical observation for the flow induced by a sphere flying between two parallel plates is made by means of both shadowgraph and Schlieren methods. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0563-8100 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN00161914 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA0125432000 |