Accession Number : AD0668223

Title :   IMPLOSION DRIVEN HYPERVELOCITY LAUNCHER PERFORMANCE USING GASEOUS DETONATION WAVES,

Corporate Author : TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s) : Watson,John D.

Report Date : DEC 1967

Pagination or Media Count : 77

Abstract : An experimental investigation of the performance of an Implosion-Driven Hypervelocity Launcher was made in preparation for the investigation of launcher performance using explosive liners. Initial gaseous mixtures of stoichiometric hydrogen and oxygen diluted with hydrogen or helium in the initial pressure range from 100 psi to 500 psi were used. The detonation velocities and the subsequent trajectories of the reflected shock waves in the hemispherical combustion chamber were determined for the various initial mixtures. The measured detonation velocities in this high-pressure range agree very well with theory. Gun performance for the various reservoir conditions was investigated and the performance utilizing imploding shock waves is compared to the performance using deflagrating or constant volume combustion. (Author)

Descriptors :   (*HYPERVELOCITY GUNS, PERFORMANCE(ENGINEERING)), DETONATION WAVES, HYDROGEN, OXYGEN, HELIUM, HYPERVELOCITY PROJECTILES, SHOCK WAVES, COMBUSTION CHAMBERS, DEFLAGRATION, EXPLOSIVES, MIXTURES, CANADA

Subject Categories : Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE