Abstract: This control system takes into account the thermomechanical aspects of materials to quickly and easily determine optimal cutting conditions and to automatically control machining to preserve the integrity of the workpiece. This system includes an acquisition module configured to acquire values of a set of input parameters relating to cutting conditions and material properties of the piece, and a microprocessor configured for determining at least one operating cutting parameter representative of a cutting signal from the machining apparatus using a set of output parameters of an integrity model previously constructed during a learning phase. The integrity model connects the set of input parameters to the set of output parameters comprising specific cutting coefficients representative of the material integrity of the piece, and establishes at least one fatigue threshold of the at least one cutting operating parameter. The fatigue threshold allows control of the progress of cutting operations.

Abstract: A system for assisting the maintenance of an aircraft is configured for implementing the following steps in an iterative manner determining a spectral power density of the position of a control surface over a time window; when the spectral power density corresponds to an amplitude of oscillations of the control surface upwardly crossing this predetermined threshold, storing an excess amplitude start time; and when the spectral power density corresponds to an amplitude of oscillations of the control surface downwardly crossing this predetermined threshold: determining a time interval between the excess amplitude start time and an excess amplitude end time, during which the amplitude of oscillations of the control surface has remained above the predetermined threshold; and determining an indicator representative of the energy corresponding to these oscillations during the time interval.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.

Abstract: A method and a system for detecting leak noise in an aircraft, making it possible to perform ground tests in complete safety and over an entire cabin pressurization range, thus avoiding having to resort to a plurality of in-flight tests. The system includes: at least one acquisition device configured to be installed in at least one area of interest of the aircraft, the acquisition device being configured to acquire data in relation to current noise in the area of interest and data in relation to a current pressure gradient between the cabin of the aircraft and the outside, and a monitoring device configured to control the acquisition of the data by the at least one acquisition device and to receive the acquisition data in order to detect any leak noise in the at least one area of interest.

Abstract: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.

Abstract: An electric generator including a number of electric accumulators and at least one heat-sink device using a phase-change material configured to pick up the excessive thermal energy produced by one of the electric accumulators and change phase in order to absorb a large quantity of thermal energy in the form of latent heat.

Abstract: An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

Abstract: A device for electrically connecting cables where a change of direction occurs. The device includes at least two busbars as well as a plate having independent internal ducts in which the busbars are located, each duct being electrically insulated from the other ducts, the busbars ensuring electrical conduction from one open end of a duct to the other end. The cables are fastened at these open ends and thus do not undergo any deformation, the change of direction taking place inside the plate with the aid of the busbars.

Abstract: A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

Abstract: A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.

Abstract: The system includes a unit for surveying the airfield to detect, by an optical detection, one or more characteristic elements corresponding to a mandatory characteristic element corresponding to a stop marking on the ground, a taxi-holding position of a runway of the airfield, to determine a current relative position of the aircraft with respect to a taxi-holding position for which at least the mandatory characteristic element has been detected and to detect a future entry onto the runway of the airfield by the aircraft, a unit for deducing a future incursion if this future entry is not cleared and a unit for implementing an action intended to assist in avoiding, the future incursion, the system being configured to provide assistance to the aircraft pilot by improving awareness concerning a possible incursion onto a runway, by alert or ground navigation assistance messages and by providing protection via automatic braking.

Abstract: A method and system for assisting a pilot of an aircraft when the aircraft is taxiing on a traffic lane of an airport are described. The system includes a unit for receiving at least a part of a path (TR) to be followed by the aircraft (AC) on the airport, a unit for surveying the airport so as to be able to detect a characteristic element of a traffic lane taken by the aircraft (AC), to determine a current relative position of the aircraft (AC) with respect to the characteristic element detected and to deduce therefrom at least one assistance information item, and a unit for assisting the pilot of the aircraft (AC) when taxiing on the airport by taking into account at least this assistance information item, this assistance being able to be implemented according to a plurality of different, more or less automated, assistance modes.

Abstract: The system for assisting the avoidance of an excursion by an aircraft from a runway or taxiway of an aerodrome includes a unit for monitoring the aerodrome so as to allow the detection, by optical detection, of a characteristic element of a pathway, for determining a current relative position of a landing gear of the aircraft (AC) with respect to the detected characteristic element, and for detecting a future excursion from the pathway of the aerodrome by the aircraft (AC) on the basis of at least this current relative position, and a unit for assisting the implementation of an action for assisting the avoidance of said future excursion. The system is configured for providing assistance to the pilot of the aircraft by improving his awareness of a potential excursion, by warning and/or ground navigation aid messages, and by providing protection of last resort via automatic braking.

Abstract: The system includes a unit for monitoring the aerodrome so as to be able to detect at least one obstacle to determine a current relative position and a current relative speed of the aircraft (AC) with respect to the detected obstacle, and to detect a future or potential collision of the aircraft (AC) with the obstacle according to at least this current relative position and this current relative speed. The system also includes a unit for, in the event of detection of a future collision, implementing at least one action intended to help to avoid this future collision. The system is configured to provide assistance to the pilot of the aircraft by improving his awareness of the future collision, by means of warning messages and/or ground navigation aids, and by providing protection of last resort in the form of an automatic avoidance maneuver.

Abstract: A cellular sound insulation structure and associated aircraft, a cell of which is provided with a diaphragm which includes a membrane having at least one orifice passing through a thickness of the membrane, and at least one tube surmounting the orifice and extending from a face of the membrane into one compartment of the cell, the tube comprising a free end, forming an acoustic outlet, which is positioned at a distance (p) from the base cross section of the cell. Also, a method for manufacturing such a cellular sound insulation structure, as well as to a tool for inserting a diaphragm into a cell. Such a cellular structure makes it possible to treat a wider acoustic frequency spectrum, and its acoustic dimensioning as well as its manufacture are simplified.

Abstract: A human-machine interface system enables interactions between aeronautical applications and aircraft control and display instruments. The human-machine interface system comprises an interface server communicating, by virtue of a common core protocol, with the aeronautical applications and control and display managers performing an abstraction of control and display instruments. The human-machine interface comprises application extension libraries providing an implementation of the common core protocol dedicated to each aeronautical application, as well as a display window definition dedicated to each aeronautical application. The human-machine interface comprises at least one control and display utility extension library providing an implementation of the common core protocol dedicated to the control and display managers. Hence, a flexible, portable and reusable architecture with easy extension and scalability opportunities is provided.

Abstract: A method for manufacturing a cellular structure having first and second faces, rows of cells each alternatingly having first cells, which are open in the direction of the first face, second cells, which are open in the direction of the second face, and also third cells formed between each row of cells, each row of cells comprising first and second strips of material placed against one another. The first and second strips of material are shaped by bending. By contrast to plastic deformation, shaping by bending makes it possible to expand the choice of materials and thicknesses for the first and second strips of material. An advantageous cellular structure is thus obtained as well as an acoustic absorption coating comprising such a cellular structure.

Abstract: An aircraft propulsion assembly including a front engine mount including a transverse beam which is connected to the engine via first and second convergent connection rods. This transverse beam includes an upper extension which is at least partially positioned opposite a front transverse reinforcement of the primary structure and which is connected thereto via at least one first connection element and right and left lateral extensions which are positioned at one side and another of the upper extension, each of them being connected via a least one second fixing element to a first wing of a right or left bracket, a second wing of the right or left bracket being connected via at least one third connection element to the primary structure.

Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.