Abstract: A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.

Abstract: An acoustic absorption structure includes: at least one acoustic element which has at least one cavity delimited by at least one enclosure comprising at least one first drainage orifice passing through the enclosure, and a rotational indexing system making it possible to position the acoustic element so that at least one first drainage orifice is positioned in proximity to or at a lowest point of the cavity. An aircraft propulsion assembly including such an acoustic absorption structure is also described.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: A device for an aircraft having at least one first communication with an air traffic control center. The device establishes a second communication with a remote assistance center and performs a first mixing of audio signals from the first communication or communications and of audio signals from the second communication and transmits the result to the pilot. The device also performs a second mixing of audio signals from the first communication or communications and of audio signals from the pilot and transmits the result to the remote assistance center by using the second communication. The device performs a relaying of commands received via the second communication to devices of the aircraft. An operator in the remote assistance center listens to the exchanges between the pilot and the air traffic control center and can exchange with the pilot and relieve him or her of certain tasks.

Abstract: In order to bring the primary structure of an engine mounting pylon of an aircraft as close as possible to a wing box: —an aircraft wing includes a wing box made partly by a front spar and an intermediate spar; —a mounting pylon including a primary structure in the form of a box having transverse reinforcement ribs; and —attachment means for attaching the primary structure of the mounting pylon on the wing box. These attachment means include a row of bolts along which each bolt passes through a structural part of the pylon on one hand, and on the other hand a fitting attached to one of the front and intermediate spars.

Abstract: An acoustic absorption structure includes: a porous layer in contact with a medium through which the sound waves travel, a cellular layer including a plurality of cells, which has at least one exterior annular canal open towards the porous layer, and a reflective layer. An aircraft propulsion system having at least one such acoustic absorption structure is also described.

Abstract: A device for coordinated movement and/or orientation of a tracking tool relative to a portable tool handled by an operator on a production station allows a tracking tool to track the movements of a portable tool handled by an operator, without the intervention of an additional operator. Also described is a smoothing method using the device, as well as a smoothing station for implementing the method.

Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

Abstract: A slide includes a carriage, a guide, and interposed pads allowing the carriage to be moved in translation in a longitudinal direction by relative sliding of the pads on contact surfaces distributed symmetrically on both sides of two planes: a horizontal plane parallel to the longitudinal direction and the transverse direction and a median plane parallel to the longitudinal direction and the vertical direction. The contact surfaces are oriented so as to form with the horizontal plane an angle between 30° and 70° inclusive. This allows a more homogeneous distribution of contact pressures, which tends to center the carriage in its guide, and the wear of the pads is more even between the pads. Such a slide also has an important advantage for the control and monitoring of the wear of the pads.

Abstract: In an aircraft including a cockpit, a unit for monitoring the situation of the aircraft and a radio communication unit, the device for aiding the ground rolling is configured to: acquire, from the monitoring unit, information the situation of the aircraft and determine predicted positions of the aircraft for a set of future instants, and for each vehicle of a set of other vehicles situated on the surface of the airport: acquire, from the radio communication unit, information regarding the situation of the vehicle, which information is transmitted by this vehicle, determine predicted positions of the vehicle and calculate a distance between the predicted position of the aircraft and the predicted position of the vehicle for each instant of the set of future instants and compare this distance with a predetermined distance threshold and, emit an alert in the cockpit if this distance is less than this distance threshold.

Abstract: A test bench for generating aerodynamic loads on an actuator to be tested includes a force actuator configured to generate at least one dynamic load, the test bench being configured to transmit the dynamic load produced by the force actuator to the actuator to be tested, and a controller for controlling the dynamic load generated by the force actuator depending on a pressure, measured by a pressure sensor, inside one of the chambers of the force actuator.

Abstract: A device for an aircraft powerplant de-icing system making it possible to reduce or eliminate a tonal noise generated by a flow of air along a surface having an orifice opening into a cavity extending on the side opposite this surface, the orifice having a downstream edge relative to the direction of flow of the air, includes a deflector positioned next to the downstream edge, extending towards the inside of the cavity, and oriented perpendicularly to the direction of flow of the air to divert towards the outside of the orifice vortices formed in the shear layer due to the flow of the air along the surface over each orifice. The deflector at the downstream edge of each exhaust orifice of the de-icing system makes it possible to redirect the vortices outside the cavity while preventing them from being greatly deformed when they pass over the downstream edge.

Abstract: An aircraft including a wing, a fuselage and at least one brace extending between the wing and the fuselage. The brace houses at least one fluid transfer line between the wing and the fuselage, such as an engine air bleed line, a hydraulic line or a fuel pipe. Use in particular to equip high-winged aircraft.

Abstract: The device for assisting the landing of an aircraft in a phase of descent for the purpose of a landing on a runway with the help of an instrument landing assistance module includes an image capturing module for capturing a sequence of successive images of the ground, an image processing module, a monitoring module for detecting on the processed images at least one visual characteristic corresponding to a runway, a computation module for computing a current position of the aircraft and a comparison module for comparing the computed current position with a signal representative of a current position of the instrument landing assistance module, a go-around warning being transmitted to a display unit, if the current positions are not substantially identical.

Abstract: A method for mounting an aircraft pylon connected to a wing includes: a step of pre-positioning first and second contact surfaces respectively provided on the wing and the pylon, a step of installing and tightening temporary connection elements, so as to keep the first and second contact surfaces clamped against one another, a step of installing and expanding at least one radially expandable element in at least one pair of first and second receptacles respectively provided on the wing and the pylon, a step of installing and tightening final connection elements connecting the pylon and the wing in the mounted state, a step of removing the radially expandable element(s) and the temporary connection elements, and of installing the remaining final connection elements and shear pin(s).

Abstract: An anterior zone of an aircraft, having a fuselage with frames, includes a cockpit, arranged partly above a front landing gear compartment, and a service area. The floor includes: a rear main crossbeam which extends in the plane of a frame situated in the service area and which is fixed to said frame, a port main spar and a starboard main spar, the rear ends of which are fixed to the rear main crossbeam, one or more secondary crossbeams, fixed to the port and starboard main spars, and one or more auxiliary spars. The number of crossbeam/frame attachments is reduced. The dimensioning of the principal beams of the floor is optimised; the result thereof is a weight saving.

Abstract: A central fairing of a pylon of an aircraft including: at least one opening to allow access to beneath the central fairing, an articulated panel that is able to move between a closed position in which the articulated panel blocks the opening and an open position in which the articulated panel at least partially frees the opening, at least one articulation for permanently connecting the articulated panel to at least one fixed element, and—at least one locking system for holding the articulated panel in the closed position. Since the articulated panel is always connected to the aircraft, it can be made larger since it is no longer carried by the operator. Consequently, the opening can be blocked with a single articulated panel.

Abstract: A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.

Abstract: An electronic device for detecting an air flow includes at least one sensor having a pair of platelets, each platelet having an RTD and having one end fixed, the other end being free and overlapping the free end of the other platelet. A platelet is flexible so as to form a switch for an electrical circuit. An air flow with a speed higher than a predetermined speed makes the sensor go from a first state, corresponding to a closed switch, in which the free ends of the platelets are in contact, to a second state, corresponding to an open switch, in which said contact is broken. A detection module allows, for each sensor, a resistance of the electrical circuit to be measured, the resistance corresponding to the RTDs being connected in parallel when the switch is closed or to one of the RTDs when the switch is open.

Abstract: A simple device for accurately measuring real-time air flows along a wall, and relating to a measuring device including an optical sensor configured to measure an illuminance distribution on a free surface of the optical sensor. A mobile member movably is mounted on the light sensor by partially covering its free surface, the mobile member being adapted to be freely directed by a local air flow pattern, thus, modulating the illuminance distribution on the free surface so as a current illuminance distribution measurement by the optical sensor indicates the current direction of the mobile member representing the current air flow pattern.