The present invention relates to a firearm projectile capable of releasing a secondary payload mid-flight through a pyrotechnic timing mechanism. Once the firearm is fired, the powder in the casing pushes out the projectile as a typical round. In addition, the powder ignites the delay column. The formulation and amount of delay pyrotechnics determines the delay time. When the delay column is burned, the final portion ignites an expelling charge. The expelling charge builds pressure in the projectile casing and separates the base plug from the main projectile housing. The expelling assembly pushes out the secondary payload out the rear of the projectile. Although the payload exits the rear of the projectile at minimum velocity, the net velocity of the payload is still in the forward direction.

The present invention relates to a firearm projectile capable of releasing a secondary payload mid-flight through a pyrotechnic timing mechanism. Once the firearm is fired, the powder in the casing pushes out the projectile as a typical round. In addition, the powder ignites the delay column. The formulation and amount of delay pyrotechnics determines the delay time. When the delay column is burned, the final portion ignites an expelling charge. The expelling charge builds pressure in the projectile casing and separates the base plug from the main projectile housing. The expelling assembly pushes out the secondary payload out the rear of the projectile. Although the payload exits the rear of the projectile at minimum velocity, the net velocity of the payload is still in the forward direction.

An autonomous weapon system for improved guidance of a projectile for homing a target includes a guided projectile including at least one sensor and a carrier projectile and at least one guidance and reconnaissance unit including a transmitter for communication via light. The system uses emitted light for both positioning and communication of target coordinates which provides an accurate and cost effective system for combatting point and surface targets by indirect fire.

A supercavitating cargo round comprises an energetic payload and an electronic payload. The electronic payload includes programmable circuitry suitable for implementing a digital delay of arbitrary length. The supercavitating cargo round is programmable while in a barrel or loader of a weapon.

According to a first aspect of the present invention, there is provided a reconnaissance and communication assembly, adapted to be launched from a gun barrel into the air. The assembly comprises a carrier (with a cavity) and a payload (within the cavity). The payload is arranged to be controllably expelled from the carrier and once expelled from the carrier, the payload transmits a signal.

A lethal projectile for immobilizing a target is capable of self-separating or otherwise opening after launch by a launcher and may release a payload prior to impact with a target. Opening may caused after an energy storage means of the projectile is charged beyond a threshold energy level. Charging of the energy storage means may be accomplished through dynamic induction when the projectile moves through a stationary magnetic field generated by a magnet of the launcher prior to launch, A control circuit can increase or decrease the magnetic field strength of the magnetic field in order to control the distance at which the projectile releases its payload, A rangefinder may provide distance information to the control circuit for charging the energy storage means to a specific energy level associated with the distance to a target.

A lethal projectile for immobilizing a target is capable of self-separating or otherwise opening after launch by a launcher and may release a payload prior to impact with a target. Opening may caused after an energy storage means of the projectile is charged beyond a threshold energy level. Charging of the energy storage means may be accomplished through dynamic induction when the projectile moves through a stationary magnetic field generated by a magnet of the launcher prior to launch, A control circuit can increase or decrease the magnetic field strength of the magnetic field in order to control the distance at which the projectile releases its payload, A rangefinder may provide distance information to the control circuit for charging the energy storage means to a specific energy level associated with the distance to a target.

A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

The present invention describes an air-burst projectile (100) and a system (200) for deploying the airburst projectile to counter an unmanned aerial vehicle (UAV) 10. Each airburst projectile includes one or more spinners (140, 140a-140d); each spinner has a sleeve or a tube (146), a number of radial partition plates (148, 148a-148d) extending from the sleeve/tube and an annular rear plate (144) connected to the sleeve. Adjacent partition plates thus form a compartment (150). Disposed in each compartment is a streamer or streamers (170,170a,170b), which are formed in a coiled-up state. When the airburst projectile is deployed into a flight path of a target UAV, the spinners (140, 140a-140d) are ejected and the streamers (170,170a,170b) are dispersed in the flight path to create a streamer cloud, so that a streamer may entangle with propellers of the UAV and bring down the UAV, or as a warning or fence marking shot.