The present invention relates to longitudinally sectioned bullets and methods that pertain to a projectile structured to be discharged from a firearm and comprising at least two separable longitudinal body sections and at least one binding element that holds the at least two longitudinal body sections together, such as before impact with a target. Said projectile is thus capable of controlled fragmentation against a soft target. Said projectile is adapted to also contain at least one supplemental payload deliverable to a target to further damage said target.

Certain exemplary embodiments can provide a system, machine, device, manufacture, circuit, composition of matter, and/or user interface adapted for and/or resulting from, and/or a method and/or machine-readable medium comprising machine-implementable instructions for, activities that can comprise and/or relate to, providing a guided descent from a release zone and toward an entry zone.

The present invention relates to longitudinally sectioned bullets and methods that pertain to a penetrable projectile structured to be discharged from a firearm and comprising at least two separable and penetrable, non-fused individual longitudinal body sections and at least one exterior binding element, including at the frontal region of said penetrable projectile, that holds the at least two non-fused individual longitudinal body sections together until they rupture inside of a target, thereby causing the penetrable individual longitudinal body sections to separate away from each other inside of the target as the projectile penetrates the target. The penetrable projectile is thus capable of controlled fragmentation against a soft target, and is optionally adapted to deliver at least one supplemental payload to a target to further damage said target.

A projectile having a leading section and a trailing section coupled together to define a structure for delivering a plurality of flechettes. The trailing section includes aerodynamic control surfaces that are deployable to apply an aerodynamic braking force to the trailing section to separate the trailing section from the leading section. The flechettes surround an explosive charge in the leading section such that initiation of the explosive charge outwardly disperses the flechettes after the leading section and the trailing section have separated. The control surfaces optionally also may impart spin to the projectile to assist in dispersing the flechettes. Thus, aerodynamic force is employed to assist in removing the flechettes from their confining structure in the projectile before dispersing them.

A projectile having a leading section and a trailing section coupled together to define a structure for delivering a plurality of flechettes. The trailing section includes aerodynamic control surfaces that are deployable to apply an aerodynamic braking force to the trailing section to separate the trailing section from the leading section. The flechettes surround an explosive charge in the leading section such that initiation of the explosive charge outwardly disperses the flechettes after the leading section and the trailing section have separated. The control surfaces optionally also may impart spin to the projectile to assist in dispersing the flechettes. Thus, aerodynamic force is employed to assist in removing the flechettes from their confining structure in the projectile before dispersing them.

A missile for delivering a payload and having a longitudinal axis. The missile comprises a nonfragmenation multi-directional munition having a hollow collar. The hollow collar has an inner surface and an outer surface opposed thereto and a first plurality of ports extending therebetween in a substantially radial direction. An ammunition is disposed in each port of the first plurality of ports, oriented outwardly from the longitudinal axis with an ignition source for expelling such ammunition from the collar. The missile also has at least one flight control surface for controlling a trajectory of the missile during flight and a controller for controlling the flight of the missile and the ignition source.

A missile for delivering a payload and having a longitudinal axis. The missile comprises a nonfragmenation multi-directional munition having a hollow collar. The hollow collar has an inner surface and an outer surface opposed thereto and a first plurality of ports extending therebetween in a substantially radial direction. An ammunition is disposed in each port of the first plurality of ports, oriented outwardly from the longitudinal axis with an ignition source for expelling such ammunition from the collar. The missile also has at least one flight control surface for controlling a trajectory of the missile during flight and a controller for controlling the flight of the missile and the ignition source.

An elongate munition with a longitudinal axis and having a nonfragmenation hollow collar. The hollow collar has an inner surface and an opposed outer surface with a first plurality of ports extending through the collar in a substantially radial direction. The ports are spaced from adjacent ports in both circumferential and longitudinal directions. A first plurality of ammunitions is disposed in each port of the first plurality of ports and oriented outwardly from the longitudinal axis. An ignition source for expelling each ammunition outwardly from the collar responsive to an ignition signal is also provided.

An elongate munition with a longitudinal axis and having a nonfragmenation hollow collar. The hollow collar has an inner surface and an opposed outer surface with a first plurality of ports extending through the collar in a substantially radial direction. The ports are spaced from adjacent ports in both circumferential and longitudinal directions. A first plurality of ammunitions is disposed in each port of the first plurality of ports and oriented outwardly from the longitudinal axis. An ignition source for expelling each ammunition outwardly from the collar responsive to an ignition signal is also provided.

A submunition assembly to be stored and deployed from an aerial vehicle, particularly a supersonic vehicle, includes a container having at least first and second walls that are joined at one end by a hinge that together define a volume along an axis perpendicular to the hinge that contains a submunition. The submunition assembly is suitably axially-shaped with a rigid parachute panel positioned around the hinge to separate and deploy a parachute. The container may have an internal volume that is conformal to the submunition. The container may have an exterior shape that is either optimized for free-fall or has a portion that provides a conformal surface for the aerial vehicle. The submunition assembly may be configured so that all processing, memory and data resides with the submunition, which issues any and all commands to control the container including separation of the rigid parachute panel and opening of the container to release the submunition.