The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

A torpedo apparatus comprises a propulsion module operable to propel the torpedo apparatus through water and a steering module operatively coupled to the propulsion module. The steering module including a plurality of fins which are controllable for controlling a direction of travel of the torpedo apparatus through water. A plurality of head modules are removably and interchangeably attachable to the torpedo apparatus, wherein each of the head modules houses at least one guidance assembly and at least one utility assembly. A power supply module is configured to provide power to the propulsion module, the steering module, and an attached one of the head modules.

A system and method is provided for detecting the trajectory of multiple fragments through a conic or cylindrical section, such as the body of a missile. Three or more sensors are placed on the on the body of the object. Each of the sensors is constructed and arranged to measure signals to the sensor at from impacts on one or more locations on the body. The sensor then transmits a signal commiserate with the impact of a fragment thereon. A computer system is also provided to perform necessary calculations and, potentially, record the impact times and locations. When the body of the object is hit by fragments or shrapnel, a signal from one or more of the sensors is sent to the computer system. This operation is performed and constantly updated for all locations where a fragment is detected by one or more of the sensors. Waveforms of the impacts are recorded, but because multiple hits can occur, there can be superposition (or destruction) of the resulting waveform sent to the computer system. The computer system can interpret which superposition or destruction is indicative of another fragment strike, and filter out those additions or subtractions to the waveforms that could not possibly be from another fragment.

A target assignment system includes a sensor system which detects a position of a moving vehicle, an assigning section which determines the launcher system assigned with the moving vehicle in response to the position of the moving vehicle and generates a first display signal which shows the moving vehicle and a first launcher system, a display section which displays the moving vehicle and the assigned launcher system in real time in response to the display signal, and an input section which instructs a change of the assigned launcher system. The assigning section generates a second display signal in which the first launcher system is changed to a second launcher system, in response to an instruction of assignment change.

A simulator for simulating a use of a missile of an attacking system is proposed. The simulator comprises: a storage device for storing of a terrain model of a battle terrain and target object models of target objects; a sensing unit for sensing and tracking a defined target object of the target objects in the battle terrain; a transmitting unit for transmitting a coded laser signal to the defined target object; a receiving unit for receiving a response signal transmitted by the defined target object; a providing unit for providing a target object model for the defined target object in dependence on at least type information of the received response signal; and a visual means associated with the missile for outputting a current visual representation of the battle terrain by means of the terrain model, the provided target object model and the location information.

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.

A targeting system for guidance correction of a projectile along a flight path toward a target. The targeting system includes seeker/guidance system mounted on the projectile which controls guidance of the projectile along the flight path toward the target. A remote fire control system receives and displays a survey image of a battlefield and enables an operator to mark location coordinates of the target in the survey image. Based on the location coordinates, the fire control system defines a reference image and transmits the reference image and location coordinates to the seeker/guidance system for use in guiding the projectile toward the target. If the target moves as the projectile travels toward the target, the remote fire control system enables the operator to update the location coordinates and transmit only an offset of the coordinates to the seeker/guidance system which then adjusts or corrects the flight path of the projectile.

A flying vehicle is disclosed with a projectile module or component that contains a projectile for projecting at another flying device. The flying vehicle receives an identification of a target flying device and applies a projectile model which generates a determination that indicates whether a projectile, if fired from the projectile component, the projectile will hit the target flying device. The projectile model taking into account one or more of a wind modeling in an area around the flying vehicle based on an inference of wind due to a tilt of the flying vehicle, a projected path of the target device based on its identification and a drag on the projectile as it deploys from the projectile component. When the determination indicates that the projectile will hit the targeted device according to a threshold value, the flying vehicle fires the projectile at the targeted flying device.

A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

A launch control system relates to a method and apparatus for launch control packet processing that is provided in the launch control system and configured to allow interworking between a plurality of firing control systems and the launch control system. The launch control system comprises a plurality of operation equipments, a system control device, and control the plurality of operation equipments, a launch control packet processing unit, a control signal distribution device, and a status display device.