Abstract: A nozzle assembly for a rocket type decoy used to protect aircraft from missile attack. The nozzle assembly includes an annular chamber and a mixing chamber which is spaced radially inward from the annular chamber. The chambers are separated by a wall and interconnected by multiple jet ports formed in the wall. The nozzle assembly is positioned adjacent to a conventional rocket combustion chamber such that when energetic compositions are reacted in the chamber, the combustion products flow into the annular chamber, radially inward through the multiple jet ports, and into the mixing chamber. Chaotic mixing of the combustion products occurs in the mixing chamber to improve combustion efficiency and reduce combustion products pass from the mixing chamber through the nozzle exit plane thus producing reduced thrust with enhanced radiation intensity.

Abstract: Controlled venting of combustion gases from an explosive material encased in a shell, as used in ordnance constructions such as rocket motors, warheads and bombs, is achieved by affixing a composite solid mass to the shell casing at a preselected location presenting low risk of damage to surrounding equipment or personnel. The solid mass is in two portions, the first being an ignition mix (in direct contact with the shell) which ignites at a temperature of 400.degree. F. to 600.degree. F. to react exothermally. The second is a reaction mix ignitable by the energy released by the ignition mix to itself release sufficient energy to degrade the metallurgical structure of the case. With the case thus weakened at a localized point, the case will rupture preferentially at that point upon an interior pressure buildup, and explosion of the entire case can be avoided.