Accession Number:

AD0631065

Title:

HYPERVELOCITY LAUNCHERS. PART 2: COMPOUND LAUNCHERS - DRIVING TECHNIQUES,

Descriptive Note:

Interim rept.,

Corporate Author:

TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s):

Report Date:

1965-12-01

Pagination or Media Count:

230.0

Abstract:

The critical survey of hypervelocity launchers and their research applications to reentry physics, hypervelocity impact, gasdynamics and aerodynamics, which was started in Part I AD-419 112 is continued in the present report. The various subsections consider the improvements that may be obtained over a simple launcher by using chambrage, combustion drivers, piston compressors, and electrical discharges. It is shown that although significant but modest improvements are obtained, these techniques do not appear to offer actual and startling increases in muzzle velocities. Consequently, novel methods will have to be employed in order to achieve the desirable current hypervelocities of integral aerodynamic shapes at 50,000 ftsec or greater. The application of implosion wave dynamics appears to offer such a possibility. Author

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE