Accession Number : ADA318744

Title :   Leeside Separation of Hypersonic Weapons,

Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH

Personal Author(s) : August, Henry ; Hardy, Frederick W. ; Wilcox, Floyd J., Jr. ; Pinney, Mark

PDF Url : ADA318744

Report Date : 1996

Pagination or Media Count : 23

Abstract : A cooperative effort between Hughes Missile Systems Company, NASA Langley Research Center and AF Wright Laboratory was performed to evaluate the adequacy of simplified aerodynamic predictive methods for estimating the leeside separation of weapons from a hypersonic air vehicle. Aerodynamic test results were obtained at the NASA Mach 6 wind tunnel facility (Reference 1), where typical store-shaped test models were traversed in the 'shielding' influence of an inclined flat plate. These data largely verify that aerodynamic predictive methods, based on Newtonian impact 'line-of-sight' approximation methods, yield representative force and moment characteristics acting on stores during their leeside carriage and upward eject launch. Based on these predicted data, simulated leeside launch trajectories of advanced submunition weapons show that they can be safely separated from a carriage vehicle at hypersonic speeds.

Descriptors :   *GUIDED MISSILES, *HYPERSONIC CHARACTERISTICS, *HYPERSONIC AIRCRAFT, TEST AND EVALUATION, WEAPONS, SIMULATION, METHODOLOGY, AIRCRAFT, PREDICTIONS, MOMENTS, RESEARCH FACILITIES, PLATES, LAUNCHING, SLOPE, SEPARATION, COMPANY LEVEL ORGANIZATIONS, VEHICLES, TRAJECTORIES, SIMPLIFICATION, HYPERSONIC VELOCITY, SUBMUNITIONS, HYPERSONIC VEHICLES, ADVANCED WEAPONS, AERODYNAMICS.

Subject Categories : Aerodynamics
      Aircraft
      Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE