Abstract: A computer-implemented method is provided for determining fratricide probability of projectile collision from a projectile launcher on a platform and an interception hazard that can be ejected or launched from a deployment position. The platform can represent a combat vessel, with the projectile launcher being a gun, the interception hazard being a missile, and the deployment position being a vertical launch cell. The projectile launcher operates within an angular area called the firing zone of the platform. The method includes determining the firing zone, calculating an angular firing area, quantifying a frontal area of the interception hazard, translating the resulting frontal area across a flight trajectory, sweeping the projectile launcher to produce a slew angle, combining the slew and trajectory, and dividing the combined interception area by the firing area. The firing and interception areas are calculated using spherical projection.

Abstract: A computer-implemented method is provided for determining fratricide probability of projectile collision from a projectile launcher on a platform and an interception hazard that can be ejected or launched from a deployment position. The platform can represent a combat vessel, with the projectile launcher being a gun, the interception hazard being a missile, and the deployment position being a vertical launch cell. The projectile launcher operates within an angular area called the firing zone of the platform. The method includes determining the firing zone, calculating an angular firing area, quantifying a frontal area of the interception hazard, translating the resulting frontal area across a flight trajectory, sweeping the projectile launcher to produce a slew angle, combining the slew and trajectory, and dividing the combined interception area by the firing area. The firing and interception areas are calculated using spherical projection.

Abstract: A cargo round (e.g., 155 mm high explosive projectile) is provided for dispensing submunitions. The round includes a nose tip, a casing attached thereto forming a chamber, a tail and a payload in the chamber between the tip and tail. The payload includes a plurality of axi-symmetric darts mounted on a plurality of front and rear tandem plates. Each dart has fore and aft ends along a polar axis. Each dart is shaped as a cone at its fore end and includes a cavity at its aft end. Each plate has a plurality of orifices arranged in a regular pattern. Each orifice receives a corresponding dart to protrude from both obverse and reverse sides of the plate. Each fore end of its dart in the rear plate inserts into the cavity of a counterpart dart in the front plate, and each plate shears apart on release of the payload to disperse the darts.