Abstract: A method for operating a frost treatment system including a first heating mat, covering a first zone and an intermediate zone of a second zone, operating alternately at a first energy level adjusted to maintain a first positive temperature on the first zone and a negative temperature on at least a part of the intermediate zone and at a second energy level adjusted to generate a positive temperature on the intermediate zone, a second heating mat covering the second zone apart from the intermediate zone and ensuring the defrosting function for the zone. This solution makes it possible to reduce the energy consumption of the first heating mat by reducing the energy level at which it is powered for most of the time. Also, an outer wall of an aircraft is provided including at least one frost treatment system operating according to this method.

Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.

Abstract: A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.

Abstract: A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.

Abstract: A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.

Abstract: An aircraft sound diagnostic method includes a step of measurement of acoustic signals by a plurality of microphones mounted at different positions inside the aircraft, a step of recording of the measured acoustic signals, a computation step which generates a sound mapping on the basis of the measured acoustic signals, a step of comparison of the sound mapping and a reference mapping and a step of transmission of the comparison to a user device. The method makes it possible to track the trending of an abnormal noise or of an abnormal noise level and assist in determining the context thereof. An aircraft sound diagnostic device for implementing the method is also described.

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

Abstract: A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.

Abstract: An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: A system for protection of at least one aircraft door sill, including a rigid panel having shape and dimensions configured to cover and to protect the sill at least partially having an attachment face oriented toward the sill of the aircraft and configured to come to rest on the latter and a step face oriented in the direction away from the attachment face. The panel includes, on one transverse side, at least one cavity forming a housing and, on the other side, an arrangement for removably fixing to the sill. The protection system equally includes at least one bar having a shape at least partially complementary to the cavity to assure the nesting thereof. In this way the panel protects the sill and can easily be replaced: the sill is provided with a rapidly interchangeable protection system.

Abstract: An assembly for an aircraft. The assembly comprises a frame, an instrument panel fixed to the frame, a support system with an arm bearing a tray in which the arm positions the tray behind the instrument panel, and in which the tray comprises a first attachment arrangement, and a support comprising a second attachment arrangement which cooperates with the first attachment arrangement to removably fix the support onto the tray. The support also comprises a fixing system which ensures the removable fixing of a touch tablet onto the support. With such an assembly, the touch tablet is held without the aid of the pilot and it is positioned in front of him or her for easy access.

Abstract: A method for producing an alveolar soundproofing structure in which a portion of a membrane of a diaphragm including an acoustic outlet is inserted into a hole of a perforated membrane which covers a cell of the alveolar structure, and the diaphragm is pressed into the cell with the perforated membrane becoming deformed and is fixed at that location. It also relates to the alveolar structure. Such a method enables different types of diaphragms to be inserted into different configurations of cells and enables the diaphragm to be fixed therein, in accordance with the sound frequencies to be processed.

Abstract: A method for manufacturing a soundproofing assembly involving providing a first panel of honeycomb structure, fastening an intermediate plate against a second face of the first panel, adhesive-coating a layer of adhesive on the intermediate plate, providing a second panel of honeycomb structure, bonding the first face of the second panel to the layer of adhesive, and perforating the intermediate plate and the layer of adhesive through the cells of the first panel or the cells of the second panel at the bonding zone of the second panel. Such a method makes it possible to save time by dispensing with additional preparation steps.

Abstract: A system for assisting in the landing of an aircraft including a processing unit configured to: during a first phase of a landing runway approach procedure, when the aircraft flies above a predetermined height with respect to a landing runway threshold, determine a bias of position and speed information from an inertia unit of the aircraft, as a function of the merged position and speed information determined as a function of information from a receiver of ILS guidance signals and of information from a signal receiver of a satellite navigation system, then, during a second phase of the approach procedure, when the aircraft flies below the predetermined height, determine so-called adjusted aircraft position and speed information by applying, to information from the inertial unit, a correction corresponding to the bias determined during the first phase of the approach procedure.

Abstract: A device for measuring the accretion of ice on a studied surface. The device has two arms, a first arm and a second arm, the second arm forming an enclosure for housing an image acquisition system disposed to acquire, through an orifice, images of a part of the studied surface located on the first arm. The device thus makes it possible to dissociate the support of the image acquisition system from that of the studied surface on which ice accumulates. Consequently, it is possible to place the second arm in the direction of the flow of the stream of air flowing along the aircraft while the first arm passes through the stream.

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.

Abstract: A display system comprising a bell with a lateral wall and a ceiling, delimiting between them an internal volume with an opening opposite the ceiling, a depressurizing arrangement configured to produce a depressurization in the internal volume, an image capturing device at the ceiling, a display screen, and a processing unit receiving an image from the image capturing device and sending the image to the display screen.

Abstract: To bring an aircraft in flight to a runway, an automatic trajectory generation system obtains a procedure, called STARI procedure, which provides a final trajectory flyable by the aircraft to land on the runway, such that from the entry point of the final trajectory or from any point above it, a holding loop pattern of a predefined shape is flyable in order to dissipate energy if necessary. The automatic trajectory generation system then computes a lateral trajectory, avoiding any terrain relief, meteorological obstacles and military zones, between the current position of the aircraft and the entry point or a point above it, based on performance adapted to an operational state of the aircraft. An overall trajectory is thus obtained, by linking the computed lateral trajectory and the final trajectory of the STARI procedure, including iterations of the holding loop pattern if necessary.

Abstract: A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.