A crowd control projectile includes a payload carrier, an incapacitating agent inside the payload carrier, and an activating mechanism for activating the incapacitating agent. The activating mechanism includes a sensor and a timer. The timer delays the activation until a predetermined delay after the sensor senses that the projectile has been launched. Alternatively, the activating mechanism includes a receiver for receiving an activation signal after the projectile has been launched. Preferably, the projectile has the shape of a clay pigeon. A launcher of such a projectile includes a communication mechanism for transmitting a timing signal or an activation signal to the projectile and an arm for launching the projectile by direct contact. To control a crowd, the projectile is launched over the crowd by direct contact with a solid arm and the activating mechanism is used to activate the incapacitating agent when the projectile is above the crowd.

A crowd control projectile includes a payload carrier, an incapacitating agent inside the payload carrier, and an activating mechanism for activating the incapacitating agent. The activating mechanism includes a sensor and a timer. The timer delays the activation until a predetermined delay after the sensor senses that the projectile has been launched. Alternatively, the activating mechanism includes a receiver for receiving an activation signal after the projectile has been launched. Preferably, the projectile has the shape of a clay pigeon. A launcher of such a projectile includes a communication mechanism for transmitting a timing signal or an activation signal to the projectile and an arm for launching the projectile by direct contact. To control a crowd, the projectile is launched over the crowd by direct contact with a solid arm and the activating mechanism is used to activate the incapacitating agent when the projectile is above the crowd.

Charged projectile assemblies include a housing and an electronic assembly configured to produce an electric field about at least a portion of the housing of the projectile. Cartridge assemblies for use with firearms include charged projectiles. Methods of charging a projectile include forming an electric field about at least a portion of a projectile and extending the electric field at least partially between a forward portion of the projectile and an aft portion of the projectile.

Charged projectile assemblies include a housing and an electronic assembly configured to produce an electric field about at least a portion of the housing of the projectile. Cartridge assemblies for use with firearms include charged projectiles. Methods of charging a projectile include forming an electric field about at least a portion of a projectile and extending the electric field at least partially between a forward portion of the projectile and an aft portion of the projectile.

An improved bullet disclosed includes a blend radius disposed between a first tangent thereof intersecting a shank of the bullet and a second tangent thereof intersecting one of a cone ogive and a boattail ogive of the bullet. The bullet also includes at least one dimple formed into a base of the bullet adjacent the boattail ogive, a curved segment joining the dimpled base and the boattail cone and a truncated cone ogive with a meplat end and a shank end, the truncated cone ogive adapted to produce less drag and friction in air than a secant or a tangent ogive. The improved bullet extends an effective flight range and a Coanda effect there around reducing air turbulence and drag on the bullet in flight. A cartridge adapted to receive the improved bullet is necked down and shortened for a COAL (cartridge overall length) nominally the same as conventional cartridges.

One aspect of the invention relates to chemiluminescent compositions comprising an oxalate composition, an activator composition and a H.sub.2O.sub.2-decomposition catalyst. Another aspect of the invention relates to chemiluminescent compositions comprising an oxalate composition, an activator composition and a peroxyoxalate catalyst. Another aspect of the invention relates to chemiluminescent systems comprising a chemiluminescent composition disclosed herein, wherein the oxalate composition and the activator composition are stored separately until activation. Another aspect of the invention relates to chemiluminescent systems comprising a chemiluminescent composition disclosed herein, wherein the oxalate composition, the activator composition, the peroxyoxalate catalyst, and/or the H.sub.2O.sub.2-decomposition catalyst are stored separately until activation. Another aspect of the invention relates to methods for initiating the chemiluminescent compositions and/or the chemiluminescent systems disclosed herein.

A fragmentation warhead with a flexible liner enables increased control of the warhead's fragmentation pattern. The flexible liner is fixed to a rigid portion of the warhead housing. Explosive material is contained in the housing. A fluid is disposed between the explosive material and the flexible liner to function as a shock transition material. The fluid is contiguous with and bears on an inner surface of the flexible liner. A plurality of rigid fragments or a plurality of explosively formed projectile (EFP) liners are fixed to an outer surface of the flexible liner opposite the fluid. Initiation of the explosive material propels the fragments or EFP liners in directions that may be varied by varying the shape of the flexible liner.

A method of deactivating an explosive composition provided in an explosive cartridge, which method comprises exposing the explosive composition to a deactivating agent that renders the explosive composition insensitive to detonation, wherein the deactivating agent is a chemical.

An adaptive electronically steerable array (AESA) system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of radio frequency (RF) transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an IR system for dual-mode operation.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) may capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, may land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC may include a parachute to slow the descent of the ADC. The ADC may also include tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images may be downloaded from the ADC.