A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

The present invention relates to a semi-active laser seeker head for miniature, laser-guided missile systems comprising a housing (20) limiting an inner chamber (23); a lens element (40) that is seated in a gap (26) of the housing (20) reaching the inner chamber (23) so as to receive electromagnetic radiation. The laser seeker head comprises; a body (44) that has a convex surface (42) on which the lens element (40) gets completely seated in a gap (26) on one hand and that extends into the inner chamber (23) on the other hand; and a filter (52) that directly receives the electromagnetic radiation, which is focused by the convex surface (42), from the body (44) that lies before and selectively transfers it to a multi-channel sensor (56) arranged at the rear portion thereof based on a predetermined wavelength threshold.

An apparatus includes at least one memory configured to store map data. The apparatus also includes at least one processor configured to segment one or more objects from one or more environment surfaces in the map data. The at least one processor is also configured to determine an offset based on a projectile drift. The at least one processor is further configured to generate a safety bounding box around each of the one or more objects using the offset.

A battlefield weapon system is proposed to counter the threat posed by small drones. The main system element is an aerodynamically guided missile that is compatible with existing multipurpose shoulder launched weapon systems. The system is fully portable for dispersed deployment among infantry.

A method for automatically generating a three-dimensional reference model as terrain information for a seeker head of an unmanned missile. A three-dimensional terrain model formed from model elements obtained with the aid of satellite and/or aerial reconnaissance is provided. Position data of the imaging device at least at one planned position and a direction vector from the planned position of the imaging device to a predetermined target point in the three-dimensional terrain model are provided. A three-dimensional reference model of the three dimensional terrain model is generated that incorporates only those model elements and sections of model elements from the terrain model, which in the viewing direction of the direction vector from the planned position of the imaging device, are not covered by other model elements and/or are not located outside the field of view of the imaging device.

The system and method of projectile flight management using a combination of radio frequency orthogonal interferometry for the long range navigation and guidance of one or more projectiles and a short range navigation and guidance system to provide for more accurate targeting, especially in GPS-denied and GPS-limited environments.

Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.

The system and method of a dual mode semi active laser seeker and imaging system using pulse detection and angle determination as applied to quad detectors to properly identify a correct designator spot. The angle performance is driven by the field of view of the imaging system. The imaging system resolution provides the required angle accuracy for guidance as cued by pulse detection apertures. The imaging system eliminates the need to designate until impact thus eliminating exposure to counter fire against the designator. The elimination of designation until impact also opens up the opportunity rapid engagement of multiple targets from a single designator.

A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

In a guiding device, a communication device receives a signal containing detection data of a target, and a processing unit. In the processing unit, a course setting section sets a flight course for a lofted flight based on the detection data, and a guiding section determines a progressing direction based on the flight course and outputs a guidance signal containing the progressing direction. The course setting section sets a first flight course when the flying object is launched. Also, the course setting section changes the first flight course to a second flight course based on the detection data after launching of the flying object.