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: 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: 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 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 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: 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: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

Abstract: Missile balancing assemblies include two balancing rings configured for mounting on a missile, each balancing ring having a ballast. Each balancing ring is configured to be rotated and rotationally fixed, and may include materials having different densities at different locations. Each balancing ring may further include an angular graduation.

Abstract: A prediction device includes a data input assembly, a modelling unit, a resolution unit, an interpretation unit, and an information transmission unit. The data input assembly is configured to enter attacker data relating to attack models, and defender data relating to ground a zone to be defended and to available defense means. The modelling unit is configured to generate a game tree evaluated on the basis of input data, based on game theory. The resolution unit is configured to define a game balance based on game theory, the game balance defining an attacker strategy and defender strategy pair. The interpretation unit is configured to determine, on the basis of the game balance, an optimum attack solution, as well as an optimum defense solution that is best suited to the optimum attack solution.

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 invention relates to an electromagnetic assembly of polyphase structure, said assembly including: a yoke comprising an electromagnetic body; a plurality of spaced-apart blocks that protrude with respect to one of the carrier faces of the yoke and that are arranged, consecutively, along the periphery of the carrier face of the yoke; and at least one winding that is associated with the blocks, wherein there is only one yoke, the plurality of blocks is arranged in at least two groups of blocks (A, B, C) in which two consecutive blocks of a given group of blocks (A, B, C) are spaced apart by an inter-block distance (E), and each group of blocks (A, B, C) is separated from the adjacent group of blocks (A, B, C) by an inter-group distance (D) that is different from the inter-block distance (E).

Abstract: A method for fabricating a part by selective melting or sintering of powder beds by high energy beam, the method including a) providing a material in the form of powder particles; b) depositing a first powder layer on a support; c) scanning a region of the first layer with the beam to heat the powder locally to a temperature higher than the powder sintering temperature, such that the powder particles as melted or sintered form a first single-piece element; d) depositing a second powder layer on the first powder layer; e) scanning a region of the second layer with the beam to heat the powder to a temperature higher than the powder sintering temperature, so that the particles of powder as sintered or melted form a second single-piece element; and f) repeating d) and e) for each new powder layer laid over a preceding layer until the part is formed.

Abstract: A device is configured for deflecting a stream of particles for a projectile guided by a link wire, the projectile having a fuselage and an engine capable of producing a propulsive jet containing the stream of particles. The device includes a device support including an inner surface configured to attach the device support to the fuselage of the projectile, and a deflector strip assuming at least an unfolded position in which the deflector strip forms an angle with the device support in order to deflect the stream of particles.

Abstract: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

Abstract: A method of fabricating a part includes: a) supplying powder particles; b) melting a first quantity of power with a beam and forming, on a support, a first pool including the melted powder and a portion of the support; c) forming a second pool by melting a second quantity of powder on the support; d) repeating c) to form a first layer; e) heating an [n]th quantity of the powder, and forming an [n]th pool above the first layer; f) heating an [n+1]th quantity of the powder, and forming an [n+1]th pool downstream from the [n]th pool above the first layer; g) repeating f) to form a second layer above the first layer; and h) repeating e) to g) until the part is constructed. The powder particles reaching each pool are at a temperature well below the pool temperature.

Abstract: An actuation device for ejecting a removable part of a missile includes a pyrotechnic actuator having a pyrotechnic charge configured to generate an overpressure and a piston configured to act on the removable part of the missile, at least one retaining rod, and at least one thermal insulation element configured to thermally insulate at least the pyrotechnic charge. The pyrotechnic actuator is configured to break the retaining rod.

Abstract: The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant so mixture into the detonation chamber (3) at at least one segment of the injection base (10).

Abstract: A flexible cover includes a main layer made of a first composite material that includes a first woven material and a first elastomer. The flexible cover also includes an auxiliary layer made of a second composite material that includes a second woven material and a second elastomer. The auxiliary layer is secured to a face of the main layer and includes petal-shaped regions that are separated from one another by weakening lines.