Abstract: 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).

Abstract: The invention relates to a method of determining the relative positions of components of a munitions system, the munitions system comprising a first component (331) and at least one second component (333). The method comprises monitoring the output of a resonant circuit (305) provided on a first component (331), the resonant circuit (305) having a resonant frequency, detecting a change in the output due to a change in the resonant frequency caused by a change in the relative positions of the first component (331) and the at least one second component (333), and using the detected change to determine that the at least one second component (333) has moved relative to the first component (331).

Abstract: A device for detecting the absence of a mechanical barrier for a missile comprises a rod constrained by a first elastic element and a free end capable of coming into contact with the mechanical barrier and a cam constrained by a second elastic element. The rod can assume one or more of the following positions: an initial entry position wherein the rod is held in a stable position between the cam and the mechanical barrier, an extended position wherein the cam moved the rod in the direction of the free end, and a final entry position wherein the rod is acted upon by the first elastic element after the rod has been released by the cam once the rod has completely entered the missile in the final entry position so as to no longer present a danger to its environment or a hindrance to the proper functioning of the missile.

Abstract: An acousto-optic device is disclosed. The device comprises: an optically transmissive element to receive a beam of light at an input surface, the beam being received from a direction defining an optical axis; a set of acoustic transducers spaced around the element; and a controller operable to activate the transducers to generate an acoustic wave travelling through the device to intersect with the optical axis. The controller is further operable to selectively activate a first subset of the set of transducers such that the acoustic wave propagates in a selected direction. Each of the set of acoustic transducers is differently orientated such that the selected direction is controllable through the selection of first subset of transducers from the set of transducers, and the device is thereby operable to control the direction in which the beam of light is deflected in two dimensions. A method of operating the device is also disclosed.

Abstract: An imaging device includes: an array of liquid crystal cells, each liquid crystal cell providing a respective phase shift to electromagnetic radiation passing through the liquid crystal cell; control electronics for controlling the phase shifts provided by each of the liquid crystal cells; a detector; and an image processor for generating an image from electromagnetic radiation detected by the detector. The array of liquid crystal cells form a plurality of patches; and the control electronics is configured to control the phase shifts of the cells of each patch to form each patch into a respective lens that focuses electromagnetic radiation towards the detector such that the plurality of patches form an array of lenses.

Abstract: There is disclosed a device for determining a strength of an oscillating electric field. The device comprises an absorber to absorb radiation at the frequency of the oscillating electric field, and a thermal insulator transparent to radiation at the frequency of the oscillating electric field, which thermal insulator is arranged to thermally insulate the absorber. The device also comprises a first temperature sensor arranged to measure the temperature of the absorber, and a second temperature sensor arranged to measure the temperature external to the thermal insulator. Methods of measuring electric field using such a device, and methods of calibrating such a device, are also disclosed.

Abstract: Method of and system for monitoring mechanical fatigue of a complex weapon system. First, data representing a movement of the complex weapon system is acquired. On the basis of the acquired data, a measure of mechanical fatigue damage to the complex weapon system arising from the movement is calculated. On the basis of that calculated measure, a cumulative total of the mechanical fatigue damage accrued by the complex weapon system is updated to account for the mechanical fatigue damage arising from the movement.

Abstract: A method of actuating an article using a servo actuation system is disclosed. The system comprises a motor, a controller and an inverter. The controller comprises a position controller, a velocity controller and a current controller; the position controller outputs velocity demands to the velocity controller, the velocity controller outputs current demands to the current controller, and the current controller outputs voltage demands to the inverter. The inverter outputs inverted voltage demands to the motor. The method comprises: determining a parameter downstream of the inverter; calculating a limiting value from the parameter and a defined supply power limit; and applying the limiting value in the controller to ensure that the power drawn by the servo actuation system remains within the defined supply power limit.

Abstract: A capture system (1) includes a drone (4) with a capture device (3) having a net (5) and a shank (6) configured to form a closed line. The shank (6) defines a leading face (6A) and a trailing face (6B). The net (5) has a maximum diameter that is greater than a maximum diameter of the shank (6), and is attached to the shank (6) on the side (7) of the trailing face (6B). A strip (8) attaches completely around the shank (6) outside of the net (5) on the side (7) of the trailing face (6B). Holding wires (9) attach to the shank (6) on the side (10) of the leading face (6A) for towing by the drone (4). The assembly formed by the shank (6) and the strip (8) enabling the capture device (3) to be held in an optimum position for capturing a flying craft (2).

Abstract: A safety assembly for use with a laser-directed energy weapon is disclosed. The assembly comprises a control system comprising a photodetector and a processing unit; and an optical device configured to attach to a target such that, when attached, the optical device provides a light beam to the photodetector. The processing unit is arranged to compare the received light beam against one or more predetermined attributes, and to permit the laser-directed energy weapon to fire only when the received light beam is determined to have the one or more attributes.

Abstract: A cooling device uses an endothermic chemical reaction for cooling. The cooling device includes a sealed casing with at least two reagents that generate an endothermic chemical reaction when they come into contact. The cooling device further includes a separating membrane separating the reagents in a storage position; a contact-making system which can be activated and configured to bring the reagents into contact with one another when activated, an interface element for activating the contact-making system; and a thermal interface with a thermally conductive metal base plate. One of the surfaces of the base plate is subjected to the endothermic chemical reaction, and the other surface of the base plate is accessible from outside the cooling device.

Abstract: The present disclosure comprises an evaporative cooling assembly (200) for cooling an apparatus (220), and a method for cooling an apparatus (220). The evaporative cooling assembly comprises a refrigerant tank (202), the refrigerant tank (202) containing refrigerant (204). The apparatus also comprises a first evaporator (210) configured to be positioned proximal to the apparatus (220), and a second evaporator (216) positioned to cool the refrigerant tank (202). Each of the first evaporator (210) and the second evaporator (216) are in fluid communication with the refrigerant tank (202), and the second evaporator (216) is positioned downstream of the first evaporator (210). The method for cooling a heated apparatus (220) comprises passing a refrigerant (204) from a refrigerant tank (202) to a first evaporator (210), which is located proximal to the apparatus (220).

Abstract: A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.

Abstract: The deployment device may include a support piece, the deployable element, in particular a handle, may be rotatably mounted on said support piece and being connected by means of an elastic element to the support piece. The deployable element may include at least one pin capable of being moved along a curved guide of the support piece and adopting one or both of the two stable positions, respectively, in two housings provided in the support piece. The stable positions may respectively correspond to a stowed position and a deployed position of the deployable element. The guide and the elastic element may be configured to generate an automatic deployment of the deployable element to the deployed position as soon as the deployable element is subjected by an operator to a rotation having an angle greater than or equal to an unlocking angle.

Abstract: A method of controlling a self-propelled flying device that seeks a target. A desired time to reach the target is obtained. The position of the target is acquired. A bias value is calculated, and the flight of the device towards the target is adjusted for a period of time using the bias value. The bias value is calculated so that the device reaches the target at the desired time.

Abstract: A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

Abstract: The device (1) for estimating the distance between an observer (2) and a target (4) using at least one image generated by a digital image generator (6) from the position (P1) of the observer (2) comprises a detection and identification unit configured to detect and identify a target (4) in the image at least from a predetermined list of known targets, an orientation estimation unit configured to determine the orientation of the identified target in the image, and a distance estimation unit configured to measure, in the image, the length of at least one characteristic segment of the target and to calculate the distance from said measured length, an actual length of the segment on the target taking into account the orientation of the target, and the spatial resolution of the digital image generator (6).

Abstract: The device (1) for estimating the distance between an observer (2) and a target (4) using at least one image generated by a digital image generator (6) from the position (P1) of the observer (2) comprises a detection and identification unit configured to detect and identify a target (4) in the image and define an imaged representation of the target (4), and a distance estimation unit configured to perform, on the image, multiple different projections of a three-dimensional model of the target (4) to obtain projected representations of the target (4) and to select the projected representation most similar to the imaged representation, the distance associated with the selected projected representation representing the estimated distance (D) between the position of the observer (2) and the target (4).

Abstract: A method and device for determining the distance between an airborne receiver and a stationary ground transmitter are disclosed. A digital terrain model is implemented to determine a range of distance values containing the transmitter. A receiver distance is found and, with the range of values, a plurality of theoretical distances is calculated, to each of which a corresponding azimuth angle and elevation angle are associated. The thus calculated azimuth and elevation angles are compared to the measured azimuth and elevation angles of the line of sight under which the receiver observes the transmitter.

Abstract: There is disclosed a missile comprising an outer skin, an electronics unit, and a thermal link between the electronics unit and the outer skin. The thermal link comprises a jumping drop vapour chamber arranged such that, when the outer skin is at an elevated temperature relative to the electronics unit, the electronics unit is thermally insulated from the outer skin; and such that, when the outer skin is at a lower temperature relative to the electronics unit, the electronics unit is thermally linked to the outer skin.