US Government As Represented by the Secretary of the Army

Donald S Chiu

Sandor I Einstein

Joseph Hershkowitz

Alexander Colletti

Roderick King

Adriana Eng

A mortar system includes a launch unit that comprises a mortar ignition cartridge provided with a flashtube. The flashtube incorporates a ring-like nozzle that is positioned within the flashtube, which acts to restrain the motion of the black powder pellets as well as to choke the flow of the resultant combustion products. The nozzle separates the flashtube into two compartments: a flashtube venting chamber and a pellet combustion chamber. The mortar ignition cartridge combustion chamber acts as the product-gas venting area of the flashtube. The combustion of the black powder pellets essentially takes place in the pellet combustion chamber. The present design modification improves the overall performance of the mortar system.

Nozzled mortar ignition system for improved performance

A modular propellant charge for semi-fixed ammunition is disclosed. The propellant charge is disposed within an ammunition cartridge canister, and permits direct access to each charge increment. Further, the propellant charge comprises at least one charge increment comprising a rigid section of a cylindrical solid of rotation, and each charge increment has a length less than the central cavity of said ammunition canister.

Axial modular propulsion charge design for semi-fixed ammunition

An ignition tube for use with electrothermal chemical combustion ignition projectiles in guns, comprising a tube positionable in a combustion chamber for receiving plasma ignition from a plasma chamber. The tube is formed from high density polyethylene or other materials adapted to release plasma upon contact by plasma ignition electrical energy or pulses. The tube is specifically designed to provide an increasing exit area from the proximal end of the tube toward the distal so as to act upon the longitudinally attenuated plasma, thereby substantially decreasing the amplitude of any reflected shock in the plasma stream. The exit area comprises a plurality of radially extending orifices or holes that have a decreased angle of inclination to the longitudinal axis from proximal end to distal end, such that the orifices form a spiral pattern on the circumference of the tube. This pattern provides a uniform action of plasma on the propellant over the entire length of the ignition tube. A combination of spiral hole pattern and decreasing angle of inclination to the longitudinal axis facilitates exit of the plasma from the combustion chamber to act on the propellant and thus on the projectile. Simultaneously with this advantage is the creation of turbulence at the plasma-propellant interface to improve local site ignition.

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Fresh Meadows, NY, United States of America

Donald S Chiu