@article{oai:jaxa.repo.nii.ac.jp:00032266,
 author = {小口, 伯郎 and 船曳, 勝之 and 佐藤, 俊逸 and OGUCHI, Hakuro and FUNABIKI, Katsushi and SATO, Shun-ichi},
 issue = {2_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Jun},
 note = {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., 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., 資料番号: SA0125432000},
 pages = {427--436},
 title = {自由飛行体発射装置とその特性に関する実験},
 volume = {7},
 year = {1971}
}