New projectiles specialized for creating and recovering trace evidence at a crime scene are provided. A wide variety of embodiments are provided, covering several use scenarios—including, but not limited to, home security devices, which may be built into an entryway or other building structure, and law enforcement guns. In some embodiments, a projectile within a projectile is provided, which fires in the direction of a primary impact. A sampler device is provided within some projectiles, which may comprise tracing barbs, containers for analytes and even a hypodermic extraction apparatus. In some embodiments, projectiles have rebounding devices, which may overlap with aspects of the sampler device, for developing distance from a criminal suspect. Other aspects, such as GPS, fasteners and defense mechanisms, are also disclosed, which encourage recovery by the authorized user and deter interception.

New projectiles specialized for creating and recovering trace evidence at a crime scene are provided. A wide variety of embodiments are provided, covering several use scenarios—including, but not limited to, home security devices, which may be built into an entryway or other building structure, and law enforcement guns. In some embodiments, a projectile within a projectile is provided, which fires in the direction of a primary impact. A sampler device is provided within some projectiles, which may comprise tracing barbs, containers for analytes and even a hypodermic extraction apparatus. In some embodiments, projectiles have rebounding devices, which may overlap with aspects of the sampler device, for developing distance from a criminal suspect. Other aspects, such as GPS, fasteners and defense mechanisms, are also disclosed, which encourage recovery by the authorized user and deter interception.

An extended range, enhanced lethality 40 mm ammunition round. The round features controlled guidance and camera front end, which can be fired as fin stabilized with no appreciable spin, from an M320 grenade launcher. The round has a launching sleeve with an oversized propellant cup, to essentially double or triple conventional range, with sharp accuracy provided by the guidance system.

An extended range, enhanced lethality 40 mm ammunition round. The round features controlled guidance and camera front end, which can be fired as fin stabilized with no appreciable spin, from an M320 grenade launcher. The round has a launching sleeve with an oversized propellant cup, to essentially double or triple conventional range, with sharp accuracy provided by the guidance system.

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.

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.

An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system. The system further comprises a controller (225, 250), arranged: —to compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; —for at least two time points, to compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; —for each of said at least two time points, to calculate a roll angle error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; —to calculate a roll angle error difference between said at least two time points; —to calculate the total roll angle subtended between said at least two time points; —to calculate a roll angle scale factor error based on said computed roll angle error difference and said total subtended roll angle and apply the calculated roll angle scale factor error to the output of the roll gyro.

An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system. The system further comprises a controller (225, 250), arranged: —to compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; —for at least two time points, to compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; —for each of said at least two time points, to calculate a roll angle error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; —to calculate a roll angle error difference between said at least two time points; —to calculate the total roll angle subtended between said at least two time points; —to calculate a roll angle scale factor error based on said computed roll angle error difference and said total subtended roll angle and apply the calculated roll angle scale factor error to the output of the roll gyro.

A method steers a missile towards a flying target. In order to permit precise flight to the target even under poor visibility conditions owing to the weather, a radar which is remote from the missile detects the target and transmits data relating to a first location area of the target to the missile. The missile determines, from the data of its own missile radar, a second location area of the target, processes both location areas to form a target area and flies to the target area.

A ball joint gimbal (BJG) seeker assembly is provided and includes a back shell, a retaining system disposed to urge the seeker ball toward the back shell and a piezoelectric ultrasonic motor and sensor system arrayed between the seeker ball and the back shell. The piezoelectric ultrasonic motor and sensor system is pre-loaded by the retaining system and configured to controllably drive an angular orientation of the seeker ball.