A rocket motor for a gun-fired projectile is configured stiffen the burnable propellant in the rocket motor during burning and/or protect the rocket motor from the pressure that occurs during firing of the projectile from the gun. The rocket motor may include a rigid structure that is integrated into the burnable propellant grain to stabilize the burnable propellant grain during burning of the burnable propellant grain. The rigid structure has a matrix or truss-like shape that extends into the depth of the burnable propellant grain. The rocket motor may include a baffled end cap that covers a nozzle of the rocket motor. The end cap defines a baffled path through the end cap to dampen gas flow into the nozzle and prevent particles of the gun propellant from entering the rocket motor. A rocket motor may implement the rigid structure or the baffled end cap, or both structures.

A rocket motor for a gun-fired projectile is configured stiffen the burnable propellant in the rocket motor during burning and/or protect the rocket motor from the pressure that occurs during firing of the projectile from the gun. The rocket motor may include a rigid structure that is integrated into the burnable propellant grain to stabilize the burnable propellant grain during burning of the burnable propellant grain. The rigid structure has a matrix or truss-like shape that extends into the depth of the burnable propellant grain. The rocket motor may include a baffled end cap that covers a nozzle of the rocket motor. The end cap defines a baffled path through the end cap to dampen gas flow into the nozzle and prevent particles of the gun propellant from entering the rocket motor. A rocket motor may implement the rigid structure or the baffled end cap, or both structures.

A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

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 over a body of water. 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 is adapted to enter the water; and the payload transmits a signal after entering the water.

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 over a body of water. 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 is adapted to enter the water; and the payload transmits a signal after entering the water.

A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.