Abstract: A device (1) for coating a substrate (4) with nanometric sized particles, wherein the device comprises: a plurality of aerodynamic lenses able to product a jet (3) of nanometric sized particles, each of the aerodynamic lenses having a longitudinal axis, the aerodynamic lenses being arranged so that the various longitudinal axes are parallel and oriented in a first direction (X) defining the direction of propagation of the jet and in the form of at least two columns (9, 10) offset from each other in a second direction (Y) orthogonal to the first direction, where the first and the second column each comprise at least one of the aerodynamic lenses, the at least one of the aerodynamic lenses of the first column also being offset relative to the at least one of the aerodynamic lenses of the second column in a third direction (Z) that is both orthogonal to the first direction and to the second direction.

Abstract: The invention relates to a nuclear fuel cladding comprising: i) a substrate containing a zirconium-based inner layer, optionally coated with at least one intermediate layer formed by at least one intermediate material selected from among tantalum, molybdenum, tungsten, niobium, vanadium, hafnium or the alloys thereof; and ii) at least one protective outer layer placed on the substrate and formed by a protective material selected from either chromium or an alloy of chromium. The nuclear fuel cladding produced using the method of the invention has improved resistance to oxidation/hydriding. The invention also relates to the method for the production of the nuclear fuel cladding by ion etching of the surface of the substrate and deposition of the outer layer on the substrate with a high power impulse magnetron sputtering method (HiPIMS), as well as to the use thereof to protect against oxidation and/or hydriding.

Abstract: A device (1) for coating a substrate (4) with nanometric sized particles, wherein the device (1) comprises: a plurality of means (2a, 2b, 2c, 2d) called production means, each able to product a jet (3) of nanometric sized particles, each of said production means having a longitudinal axis, the production means being arranged so that the various longitudinal axes are parallel and oriented in a first direction (X) defining the direction of propagation of the jet and in the form of at least two columns (9, 10) offset from each other in a second direction (Y) orthogonal to the first direction (X), where the first (9) and the second column (10) each comprise at least one production means, said at least one production means (2a, 2b, 2c, 2d) of the first column (9) also being offset relative to said at least one production means (2a, 2b, 2c, 2d) of the second column (10) in a third direction (Z) that is both orthogonal to the first direction (X) and to the second direction (Y).

Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: The invention relates to a nuclear fuel cladding comprising: i) a substrate containing a zirconium-based inner layer, optionally coated with at least one intermediate layer formed by at least one intermediate material selected from among tantalum, molybdenum, tungsten, niobium, vanadium, hafnium or the alloys thereof; and ii) at least one protective outer layer placed on the substrate and formed by a protective material selected from either chromium or an alloy of chromium. The nuclear fuel cladding produced using the method of the invention has improved resistance to oxidation/hydriding. The invention also relates to the method for the production of the nuclear fuel cladding by ion etching of the surface of the substrate and deposition of the outer layer on the substrate with a high power impulse magnetron sputtering method (HiPIMS), as well as to the use thereof to protect against oxidation and/or hydriding.

Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: The member bearing electromagnetic decoys comprises a sliding member (23 to 27) having an open major face closed by a cover of which an extension projects opposite an opening (21A) in a compartment (21) provided for a pyrotechnic portion. When the pyrotechnic charge there disposed has caused ejection of the decoy-bearing sliding member, and after a given delay, it will act on the extension of the cover in order to remove the latter and thereby release it from the electromagnetic decoys. This ensures that the decoys are deployed at the end of a given delay after ejection of the decoy-bearing member from the aircraft.

Abstract: Method for self-stabilizing deposition of a stoichiometric compound by reactive sputtering using a cold plasma. A reactive gas is supplied to a target, the instantaneous power applied to the target is cyclically reduced and increased at a frequency sufficiently low that a reaction between the target material and the reactive gas takes place on the surface of the target, and the product of the reaction is then sputtered off the surface of the target and onto a substrate. The alternating decrease and increase of the instantaneous power applied to the target at low frequency provides for self-stabilizing deposition of the reaction product on the substrate.

Abstract: A rope is pulled between an end member such as a parachute forming a sail with regard to the wind and a main floating anchor located at the other end. This rope is connected at chosen intervals to captive-balloons, each associated with secondary floating anchors. The captive-balloons are chosen to be sensitive to the wind in order to incline themselves with respect to the floating anchor and to respectively support decoys formed by sets of retroreflective trihedrons. Advantageously, the decoys are individually connected in their lower part to floating bodies such as slightly inflated and loaded balloons. The invention has application, in particular, to the simulation of large surface ships.

Abstract: A cartridge for launching electromagnetic decoys with multiple charges comprises an elongated tube having an open upper end and a closed lower end, in which a plurality of flat holders, containing electromagnetic decoys are stacked over the length of the tube. At least one of the upper and lower surfaces of each flat holder is a conical surface in the shape of a flattened cone and each flat holder is provided in its lower part with a pyrotechnic charge able to project it upwards and to disperse the decoys. Each charge is connected to an adjacent charge by a pyrotechnic retarder and the upper most charge of the stack is provided with at least one pyrotechnic initiator, such that the arrangement formed by the initiator, the chargers and the retarders forms a continuous pyrotechnic chain, in order to allow, after detonation of the initiator, the successive ejection of the flat holders in a predetermined timed sequence.

Abstract: Located below an aircraft is a support rod (1) provided with female engagement members (10). Standard missile launcher modules are provided on their flat upper wall with counterpart male engagement members (20). The engagement members (10 and 20) cooperate in the manner of dovetails and for each module location, they are separated from each other according to the same geometric progression along the support rod (1) and the upper wall of the module (2). A device comprising a cam (27) and lever (273) makes it possible to ensure at the same time the translation necessary for locking of the dovetail, as well as the making of contact between the electrical connector members.

Abstract: In an ejection cavity defined by walls such as (753 and 754), an open decoy support body (70) in the form of a slide is placed, and equipped with a pyrotechnic ejection charge (709) and a transmitter (761) for igniting the ejection charge on command. In addition to the stopper (755) which closes the ejection orifice of the cavity, a retaining member (750) is provided, comprising along its edge V-shaped clips (751), whereof the point is directed towards the inside of the decoy launching cavity and keeps the decoys in place despite the high accelerations and vibrating stresses encountered in an aircraft. At the time of deployment of the decoy, the sliding of the slide will disengage the V-shaped clips (751), which allows a slow departure of the decoy support member.

Abstract: An infrared decoy member is provided with a pyrotechnic chain for ejection and ignition incorporated in a unit. The ejection charge is mounted to slide in a cavity which allows the ejection of the unit as well as of adjacent infrared charges. A slide, which can be released when an acceleration threshold is crossed and on condition of ejection could ensure the transmission of fire to a transverse channel leading to useful charges. A second fire-transmitting chain which is independent, makes it possible to excite previously a similar decoy member located below.

Abstract: A standard launcher module for various missiles, in particular flares, comprises a flat wall forming a base, provided with male engagement members. In the position engaged on the support incorporated in the aircraft, a connector is active. Provided in a central groove is a series of electrical initiators connected selectively to the connector and located opposite counterpart relay channels which lead respectively to the useful charges. A sliding bar located in the groove has orifices, located according to the working geometry of the initiators. Finally, a motor connected to the connector allows the movement of the bar between a safety position and an armed position.

Abstract: The present invention relates to pyrotechnic flares. A hollow support structure (1) receives a first pyrotechnic composition (2) with a delay action internally and axially, whereas it receives a second pyrotechnic composition (4) which is slower than the first, in holes (101 to 151), arranged radially and of decreasing length. An initiator (3) initiates the composition (2) on the side where the radial through-holes are longest. Located outside is an illuminating composition (5), which may thus be illuminated virtually at the same time over the entire length of the product.Application in particular as an optical or infra-red counter-measure.

Abstract: This invention relates to the safety of ammunitions.The projectile of a cartridge has a base which houses a safety stop consisting of a transversely slidable valve. A device ensures that the valve cannot be released until the projectile has been subjected to a powerful acceleration. Another safety device very advantageously ensures that the pyrotechnical chain inserted in the base functions only when the pressure of the ejection charge has been able to release a sealing-block.In particular, the invention may be applied to infra red window releasing cartridges.