The neutralisation system (1) comprises a drone (2) configured to be able to fly close to a target and transmit at least position information concerning the position of the target, the neutralisation system (1) also comprising at least one missile (6) capable of being guided towards the target in order to neutralise it and at least one control station (8), the control station (8) comprising a receiving unit (9B) capable of receiving at least the position information transmitted by the drone (2) and a display unit (10A) capable of displaying this information to an operator, the missile (6) being configured to be able to be guided towards the target by means of the position information received by the control station (8).

The target marking device (1) comprises a drone (2) which is provided with at least one transmitter (4), the transmitter (4) comprising an activation element (10) for activating it so that it transmits at a given time a signal (S) which represents a position information item, the transmitter (4) being configured to transmit at least one of the following signals: an infrared signal, a light signal, a sound signal, a signal generated by a chemical substance, the target marking device (1) being part of a target tracking system (6) and/or a target processing system which is provided with movable machinery (7).

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.

An optical radiation-collecting assembly includes a convex mirror, a concave mirror with a central opening and a window, arranged such that light passes through the opening in the concave mirror, is reflected first by the convex mirror and then by the concave mirror, and subsequently passes through the window. The optical assembly is suitable for use in a homing device for guiding a rocket, preventing an optical input component of such a device from being damaged and rendered inoperative from abrasion when exposed to a high-speed air flow containing dense particles. The optical assembly also includes an image-forming function.

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.

An optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.

The present invention relates to a method of marking and identifying a target, and in particular, a method of using a Directed Energy Weapon (DEW) to heat a target without damaging it so that the target may be clearly identified by detectors and systems using thermally sensitive imaging.

An imaging and asynchronous laser pulse detector (ALPD) device, imaging cell of the imaging and ALPD device and method of use is disclosed. A detector generates an electrical signal in response to receiving an optical signal, wherein a frequency of the electrical signal is indicative of a frequency of the optical signal. A first detection/readout circuit is sensitive to a first frequency range, and a second detection/readout circuit is sensitive to a second frequency range. The first detection/readout circuit allows the electrical signal to pass from the first detection/readout circuit to the second detection/readout circuit.

A Semi-Active Laser sensor for determining a line-of-site to a target includes: a receiver for receiving a plurality of target pulses; a processor for starting a target track for pulses that cross a noise threshold opening a pulse gate within the target track; and for every laser pulse received within the pulse gate crossing the noise threshold, determining a time index relative to the pulse gate center; and a memory for storing the pulses that cross the noise threshold and their respective time index, wherein the processor further temporally offsets the stored pulses based on their corresponding time indexes, sums the offset pulses together to generate a summed pulse signal, and determines the line-of-sight error to the target from the summed pulse signal.

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.