Institute of Space and Aeroautical Science University of Tokyo
Institute of Space and Aeroautical Science University of Tokyo
Institute of Space and Aeroautical Science University of Tokyo
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.
自由飛行体発射装置とその特性に関する実験
SA0125432.pdf
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