USA as Represented by Secretary of the Navy

David Reinaldo Gonzalez

Kevin Cochran

John E Hendershot

John Frederick Kunstmann

Daniel Corey Pines

Kyle Matthew Beckett

Xavier Omar Velez-Ocasio

Greg Young

Earle Monroe Sparks

Exemplary embodiments of an ignition apparatus are disclosed herein. Each ignition apparatus is configured for use in a projectile, such as an artillery projectile, rocket, missile, drone, and other similar projectiles. In each exemplary embodiment disclosed herein, the ignition apparatus initiates an ignition sequence that is the reverse of the ignition sequences implemented by conventional ignition devices that utilize pre-loaded or pre-compressed spring-operated firing pins. Each exemplary embodiment of the ignition apparatus disclosed herein utilizes the extreme axial acceleration of the projectile to arm and initiate the ignition sequence.

Ignition apparatus for projectile

A submunition delivery device including a master electronics module; a submunition module operatively connected to the master electronics module and including a plurality of submunition banks separated by bulkheads. Each of the submunition banks includes a plurality of submunitions; a base plug module operatively connected to the submunition module; and a distributed fuze module operatively connected to the master electronics module to limit a detrimental effect of the plurality of submunitions upon a collision by arming the plurality of submunitions before a dispense action.

Distributed fuze architecture for highly reliable submunitions

The present disclosure provides systems and methods to aid engineers and designers in pinpointing optimal aerodynamic designs given a target objective. Advantageously, the present invention allows a user to tackle shifts in requirements or to simply conduct preliminary design feasibilities, quickly and efficiently. The present invention includes: () a genetic algorithm-based optimizing routine; () an existing semi-empirical, aeropredictive code (APC); and () an interface between the two. The present invention defines bounds for an array of variables that define the overall aerodynamic geometry and performance measures of a device. The genetic algorithm-based optimizing routine interfaces with the APC to determine a design that best fits the requirements.

Systems and methods for optimization of missile and projectile aerodynamic configurations

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King George, VA, United States of America

David Reinaldo Gonzalez