Abstract: An aircraft turbine engine assembly including a nacelle structure with a strut attachment zone, a first cover forming an air intake lip, a hinged cover arranged on the nacelle upper portion, between the first cover and the attachment zone, a hinge system of the cover comprising, on either side of a mid-plane of the nacelle, a front rod and a rear rod that are one in front of the other. The two ends of each rod are co-planar, parallel to the mid-plane. A first end of each rod is hinged on the cover. A second end of each rod is hinged on the structure. A locking system is actuatable from the outside of the nacelle between a locked and an unlocked positon. The nacelle comprises at least one cylinder with a first end mounted hinged on the structure and the other end mounted hinged on the cover.

Abstract: A primary structure of an aircraft pylon, which comprises upper and lower spars, right-hand and left-hand lateral panels, transverse reinforcers that are disposed in transverse planes and, each have a square or rectangular contour and at least one sole to which the upper and lower spars and the right-hand and left-hand lateral panels are fastened. At least one of the transverse reinforcers of the primary structure has first and second link rods that are oriented along diagonals of the transverse reinforcer, and connecting systems that each connect first and second ends of the first and second link rods to the sole or to one of the soles.

Abstract: A turbomachine assembly for an aircraft comprising a nacelle with a nacelle structure, cowls attached to the structure to create an aerodynamic surface, an articulated cowl, comprising four edges, in the upper portion of the nacelle, an articulation at a first edge of the articulated cowl attached between the articulated cowl and the nacelle structure allowing the articulated cowl to move between a closed and an open position, a locking system at a second edge of the articulated cowl, opposite the first edge. The locking system comprises a handle actuable from the exterior of the nacelle, between a first position and a second position, a locking device movable between a locking position and an unlocking position, and a transmission system that moves the locking device from the locking position to the unlocking position when the handle passes from the first position to the second position, and vice versa.

Abstract: A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.

Abstract: The system for collecting and analyzing data relating to safety and comfort criteria of an aircraft comprises an acquisition unit for acquiring basic aircraft information before a flight of the aircraft and values of flight parameters during the flight, the basic information and the flight parameter values forming a first set of digital data, a measurement unit for measuring values of environmental parameters during the flight and for storing, in a suitable digital format, a second set of digital data representative of the environmental parameter values, an analysis unit for analyzing the first and second sets of digital data, and radio communication systems for transmitting sets of digital data between the different units, the system allowing for a rapid collection and analysis of the digital data.

Abstract: A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.

Abstract: A method for edge-to-edge welding of a first sheet metal panel to a second sheet metal panel on a bearing structure. The method comprises positioning and fixing the first panel to the bearing structure, positioning and fixing the second panel to the bearing structure with the second panel overlapping a raw edge of the first panel, jointly cutting the first panel and the second panel in the overlap area to form a connection edge of the first panel and a connection edge of the second panel, withdrawing scrap cuttings from the first panel and scrap cuttings from the second panel, and friction stir welding the connection edges.

Abstract: A turbomachine comprising an engine body and an annular nacelle. The nacelle has an air intake comprising an outer skin, an inner skin, an air intake lip connecting the outer and inner skins together, and an annular frame connecting the outer and inner skins together. The turbomachine comprises a system for de-icing the air intake having an air bleeding port for bleeding a flow of hot air from the engine body, and two interconnected heating systems. An inner skin heating system receives the hot air flow to heat, by means of a gas-liquid heat exchanger, a heat transfer liquid contained in a hydraulic circuit arranged in part in the heat exchanger and in the inner skin. An air intake lip heating system diffuses the flow of hot air, once it has passed through the inner skin heating system, through the annular frame to heat the air intake lip.

Abstract: A frost protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel and an air intake lip forming a leading edge of the nacelle. The protection system comprises a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the at least one acoustic panel.

Abstract: A turbofan comprising a motor and a nacelle, surrounding the motor, where a duct for a bypass flow is delimited between the nacelle and the motor and in which a flow of air flows. The nacelle comprises reverser flaps where each one is articulated between a stowed position in which it is not in the bypass duct and a deployed position in which it is across the bypass duct. The turbofan has at least one reverser flap with at least one leakage window configured to allow airflow in the deployed position. The at least one reverser flap has at least one fin extending across the leakage window.

Abstract: An assembly method for an air intake of a jet engine of an aircraft, comprising providing an acoustic panel, an outside panel, flanges and a collar, arranging a rear edge of the acoustic panel on an assembly chassis. The flanges and the collar are attached at the rear edge of the acoustic panel. A rear edge of the outside panel is attached to the attached collar. A first set of geometric data of a front edge of the acoustic panel is measured and a second set of geometric data of a front edge of the outside panel is measured. A U-shaped lip as a single element is produced based on the two sets of geometric data. An inside leg of the lip is attached to the front edge of the acoustic panel and an outside leg of the lip is attached to the front edge of the outside panel.

Abstract: A bypass turbojet nacelle comprising a fixed structure, a fixed cowl and a cowl movable in translation between advanced and withdrawn positions by a ram with a reverser flap movable thereon, and a deployment system comprising a first slider integral with the movable cowl, a first groove comprising a first part and a curved, second part integral with the fixed structure, a second slider movable in translation in the second groove part, a first connecting rod rotatable on the first slider and on the second slider, and a second connecting rod articulated on both the first connecting rod first end and the reverser flap. The ram rod is articulated on the first connecting rod. Moving the first slider from the advanced to the withdrawn position moves the second slider along the first part and, when the first slider reaches the withdrawn position, the second slider moves along the second part.

Abstract: An acoustic panel (1) includes a plate (2) made of an acoustic absorbing material (3), as well as a resistive skin (4) and a backing skin (6) arranged respectively on both sides of the plate (2), the acoustic panel (1) including acoustic elements (8) able to carry out an acoustic absorption, each of them being arranged in a housing (7) provided in the plate (2) with an opening (9) in front of the resistive skin (4). The combination of the plate (2) and the acoustic elements (8) allows to combine the sound attenuation properties of these two types of elements and to increase the frequency range of sounds that can be attenuated by the acoustic panel (1), without increasing the dimension.

Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Abstract: A nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.

Abstract: A turbofan having a nacelle including a slider mobile in translation between advanced and retracted positions to open a window between a duct and the exterior, a plurality of blades, each being mobile in rotation on the slider between stowed and deployed positions, and a maneuvering system that moves each blade and includes, for each blade, a shaft mobile in rotation on the slider and on which the blade is fixed, an arm having a first end fixed to the shaft and a second end, an arc which is coaxial with the longitudinal axis and is rotatably mounted on the slider, about the longitudinal axis, a lever mounted in articulated fashion between the arc and the second end of the arm, and an actuation system which rotates the arc in one direction and in the other.

Abstract: A pivoting-connection device connecting at least two components and comprising a clevis having first and second branches, an arm positioned between the first and second branches of the clevis, a cylindrical pin connecting the clevis and the arm, at least one guide ring which has a flange configured to bear against an interior face of the first branch, an immobilizing system configured to occupy a free state and a blocked state in which the cylindrical pin and the guide ring are immobilized with respect to one another in the longitudinal direction, in both senses of that direction, and a blocking system configured to occupy an unfitted state and a blocked state in which the blocking system is in contact with the exterior face of the first branch.

Abstract: A monitoring device comprising at least one measurement module for measuring at least one physiological parameter of the crew member, at least one consolidation module for consolidating the measured physiological parameter or parameters, a fusion module for fusing the consolidated physiological parameter or parameters in order to detect at least one physiological status of the crew member, a filtering module for filtering the physiological status or statuses, a determination module for determining a level of incapacity of the crew member, a transmission module for transmitting a signal indicative of the level of incapacity of the crew member to a user device.

Abstract: A system including at least one image acquisition module to acquire images of the environment of the aircraft and of the runway, a module to recognize in the images at least one element representative of at least one contaminant likely to influence the state of the runway, a module to determine at least one property of the contaminant or contaminants and a module to transmit to a user device the property or properties of the contaminant or contaminants. The system allows contaminants to be identified and to be located on the runway or in the environment of the aircraft.

Abstract: A turbofan having a nacelle comprising a slider being mobile in translation between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one being mobile in rotation on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade. The maneuvering system comprises, for each blade, a shaft being mobile in rotation on the slider and on which the blade is fixed, a toothed sector being fixed to the shaft, a toothed arc being mobile in rotation on the slider, and having a bearing face, a threaded rod mounted fixed on the fixed structure, a cam having a tapped hole screwed onto the threaded rod and mounted fixed in translation with respect to the slider, and a return arrangement that presses the bearing face against the cam outer surface.