A multi-mission munition adapter for an aircraft may be configured to attach to a hardpoint and hold a plurality of munitions, such as missiles and bombs. A top of the multi-mission munition adapter may have suspension lugs configured to attach to a hardpoint on an aircraft. Sides of the multi-mission munition adapter may have one or more launcher attachment fittings configured to attach missile launchers. A bottom of the multi-mission munition adapter may have one or more munitions ejector hangers configured to attach air-to-ground munitions ejectors. The adapter may comprise an electrical system that permits an aircraft to communicate with and/or power all functions of the bomb rack, missile launchers, and the weapons employed.

Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator and a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly is to pivot relative to the actuator between a first position to retain a container and a second position to release the container. The swaybrace and retention assembly includes a swaybrace arm having a receptacle to engage a post of a container. The swaybrace arm to pivot between the first position to cause the receptacle to engage the post of the container to retain the container and the second position to cause the receptacle to disengage the post to release the container.

Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator and a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly is to pivot relative to the actuator between a first position to retain a container and a second position to release the container. The swaybrace and retention assembly includes a swaybrace arm having a receptacle to engage a post of a container. The swaybrace arm to pivot between the first position to cause the receptacle to engage the post of the container to retain the container and the second position to cause the receptacle to disengage the post to release the container.

A projectile delivery module to be mounted on an aerial vehicle includes a projectile delivery system including a kinetic projectile and a base system. The kinetic projectile includes a projectile body, an RF receiver, and an onboard steering system including: a steering mechanism operable to change an attitude, orientation, and/or direction of flight of the kinetic projectile; and a steering actuator. The base system includes: an RF transmitter to communicate with the RF receiver; a projectile holder; a target tracking system; and a projectile guidance system including a projectile tracking system and a projectile control system. The base system is configured to: release the kinetic projectile from the projectile holder such that the kinetic projectile is driven toward a target by gravity; track the target using the target tracking system; track the released kinetic projectile using the projectile tracking system; and automatically control the onboard steering system using the projectile control system to adjust a trajectory of the falling kinetic projectile to steer the kinetic projectile to the target.

A projectile delivery module to be mounted on an aerial vehicle includes a projectile delivery system including a kinetic projectile and a base system. The kinetic projectile includes a projectile body, an RF receiver, and an onboard steering system including: a steering mechanism operable to change an attitude, orientation, and/or direction of flight of the kinetic projectile; and a steering actuator. The base system includes: an RF transmitter to communicate with the RF receiver; a projectile holder; a target tracking system; and a projectile guidance system including a projectile tracking system and a projectile control system. The base system is configured to: release the kinetic projectile from the projectile holder such that the kinetic projectile is driven toward a target by gravity; track the target using the target tracking system; track the released kinetic projectile using the projectile tracking system; and automatically control the onboard steering system using the projectile control system to adjust a trajectory of the falling kinetic projectile to steer the kinetic projectile to the target.

A container suspension and release system provides at least one ejector assembly having a carry position and a deployed position. The ejector assembly includes an actuator configured to extend ejector assembly from the carry position to the deployed position, and a retention assembly. The retention assembly employs a bracket attached to the actuator and a fixed sway brace extending from the bracket. A left retention arm is pivotally attached to the bracket and a right retention arm is pivotally attached to the bracket, with the left and right retention arms configured to rotate in opposite directions. A rotation activation mechanism is provided to rotate the left and right retention arms in the deployed position. An energy source connected to the actuator to provides energy to actuate the at least one ejector assembly.

A system, method and computer program product for controlled drone descent, and deactivation, including a drone deactivation system; and a location system. The drone deactivation system calculates positioning, signal reception, signal strength, and signal identification parameters of a target drone from the location system, and determines an attack method based on the calculated parameters. The drone deactivation system employs the determined attack method against the target drone for forcing at least one of controlled drone descent, and deactivation of the target drone.

A system, method and computer program product for controlled drone descent, and deactivation, including a drone deactivation system; and a location system. The drone deactivation system calculates positioning, signal reception, signal strength, and signal identification parameters of a target drone from the location system, and determines an attack method based on the calculated parameters. The drone deactivation system employs the determined attack method against the target drone for forcing at least one of controlled drone descent, and deactivation of the target drone.

The present invention relates to a glide bomb and methods of use thereof for use with an unmanned or manned aerial vehicle or for operative deployment. In one form, the glide bomb is configured to be carried and released by an unmanned aerial vehicle (“UAV”) for flight towards a selected target. The glide bomb includes an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control.

Proposed are a shell launcher for a drone and a method of launching shells for a drone. According to the shell launcher for a drone and the method of launching shells for a drone, by launching shells such as EFPs using a drone, it is possible to use a drone as various weapon systems.