Abstract: A fixing element for components of an assembly, comprising a rod which is formed by a cylindrical shaft and an end, the rod being a metal component which is at least partially surface-treated by means of anode oxidation and coated over at least a portion of the cylindrical shaft with a lubricating coating. Such a fixing element enables the electrical continuity to be ensured with the components during mounting with moderate interference in the assembly.

Abstract: A system comprising a discharge valve that allows some of the fluid generated by a fluid generating source and intended for a drive torque generating member for a rotary element of a mechanical device to be removed so as to limit the corresponding rotational speed, this being done for a length of time that allows a thermal gradient to be reduced sufficiently that a phenomenon of deformation of said rotary element can be prevented.

Abstract: A device for positioning a first piece relative to a second piece. The first piece comprises a free end with a first bore and the second piece comprises an engagement part with a second bore intended to come into correspondence with the first bore. The first and second bore are drilled to the definitive diameter thereof prior to the relative positioning thereof. The device comprises one or more positioning elements, which are able to position the first bore relative to the second bore along at least one of three geometric axes.

Abstract: A method for treatment of two surfaces, each surface belonging to a metal part which is designed to be painted, the two surfaces being secured adjacent to one another or one on top of the other. The treatment method comprising a sandblasting step during which each surface is subjected to sandblasting, a projection step during which each surface thus sandblasted is subjected to thermal projection of an aluminum alloy, such as to compensate for the divergences between the two surfaces, and a finishing step during which the layer of aluminum alloy thus projected is subjected to mechanical finishing, such as to constitute a coating with a homogeneous surface.

Abstract: A method for supporting aircraft maintenance, performed in a system comprising a display selection device and a portable device with a camera and an augmented reality display. The method comprises the steps of acquiring images of an equipment of the aircraft with the camera, and sending them to the display selection device; identifying the equipment present in these images with the display selection device and determining the identifier thereof, referred to as the useful identifier; on the basis of the useful identifier, sending maintenance assistance data with the display selection device to the augmented reality display; in response, displaying, in augmented reality, images corresponding to the data with the augmented reality display device. The method also comprises steps for displaying guidance data guiding towards one equipment in particular. A device for implementing such a method is also disclosed.

Abstract: A detection device comprising a first data processing unit configured to determine a first trend of the control surface control order as a function of time, the first trend being defined according to a reference parameter, a second data processing unit configured to determine at least one second trend of the control surface position value as a function of time, the second trend being also defined according to the reference parameter, and a monitoring unit configured to compare the first and second trends in order to verify the existence of a correlation between these first and second trends so as to detect an oscillatory failure as soon as a loss of correlation between the first and second trends appears, if necessary.

Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.

Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

Abstract: A system for electrically connecting a piece of cabin equipment of an aircraft to a control system and to at least one electrical power supply source of the aircraft. The connection system comprises a host interface module to which the control system and the at least one electrical power supply source are connected. The host interface module ensures the conversion of data signals originating from the control system and a transfer of voltages of the at least one power supply source to power supply/data signals that conform to a given protocol. An interface module integrated in the cabin equipment ensures the conversion of the power supply/data signals conforming to the given protocol to data signals for controlling at least one electrical service element of the cabin equipment and the transfer of the voltages of the at least one power supply source to the at least one electrical service element.

Abstract: A method for predicting temperatures tolerable by a component, a piece of equipment or a vehicle structure. This method includes the steps of determining, for each piece of equipment, component or structure of the vehicle, such as an airplane, a temperature spectrum depending on a plurality of extrinsic parameters measured during a full operating cycle of the airplane, by taking into account, for each piece of equipment, component or structure, possible combinations of the extrinsic parameters and setting aside unlikely combinations of the extrinsic parameters, determining, for each piece of equipment, component or structure, the probability of occurrence of the spectrum during the full airplane operating cycle, and defining a database including the temperature spectra so as to predict the lifetimes of the piece of equipment, component or structure and redefine weather and operational standards indicating extreme temperatures and their probability of occurrence obtained with the measured extrinsic parameters.

Abstract: A communication network on board a vehicle is a deterministic switched Ethernet network using virtual links, which includes a set of links, a set of subscribers and at least one switch containing a static configuration table that can be configured according to virtual links passing through this switch. This switch is integrated in a subscriber from the set of subscribers and is connected to the subscriber so as to enable communications between the subscriber and at least one other subscriber of the communication network. The switch includes at least three external communication ports (PE1, PE2, PE3) and the communication network is configured according to a mesh topology such that this switch is connected to at least three other entities corresponding to subscribers and/or switches of the communication network.

Abstract: A joining part with a wing comprises a through bore defining a fastening direction perpendicular to the wing. The wing comprises at least one non-through pocket configured to reduce the stress gradient in a peripheral zone of the through bore and/or at least one relief configured to reduce the stress gradient in a peripheral zone of the through bore, the non-through pocket forming a cavity in the thickness of the wing and comprising a curved side at a distance from the peripheral edge of the through bore. The joining part may be part of a lug, such as, for an aircraft fitting.

Abstract: A system including a load factor control module for calculating a deflection order on manual actuation of a control column by a pilot of the aircraft and transmitting that deflection order to at least one elevator of the aircraft, a longitudinal attitude control module for maintaining the longitudinal attitude of the aircraft at a target attitude in the event of absence of manual actuation of the control column by the pilot during a flight, and a transition management module for determining and storing a present longitudinal attitude value of the aircraft at a recording moment and transmitting that longitudinal attitude value to the longitudinal attitude control module for the longitudinal attitude control module to use the longitudinal attitude value as the target attitude.

Abstract: A method for controlling the machining of a part by a portable automatic machining apparatus. A machining tool configured to machine the part under the action of a pressurized fluid feeding the apparatus, and following a machining cycle, comprising a number of phases and a machining support equipment item. The machining support equipment item cooperates with the machining tool during the machining of the part. The method comprises the steps of measuring the pressure of the fluid at the outlet of the apparatus, analyzing the measured pressure to detect at least one phase of the cycle of machining of the part by the machining tool from the duly measured pressure, and controlling the machining support equipment item as a function of the phase of the machining cycle which has been detected.

Abstract: An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.

Abstract: A turbojet comprising a low-pressure compressor, a high-pressure compressor and a bleeding system configured to bleed air in the turbojet and to deliver the air to an air system. The bleeding system comprises a first air intake configured to bleed air at low pressure, a second air intake configured to bleed air at high pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to an outlet of the second valve, a high-pressure valve connected to the second air intake, a control valve connected to the air system, and a controller to control opening and closing of the valves depending on a pressure at the first air intake.

Abstract: A thrust reverser for an aircraft engine assembly, comprising two sub-assemblies configured to surround an engine, each of the sub-assemblies comprising an inner fixed structure, a translating cowl, a torque box, a substantially vertical 12 o'clock bifurcation, and a substantially vertical 6 o'clock bifurcation. At least one of the sub-assemblies comprises at least one separating partition extending between the inner fixed structure, the translating cowl and the torque box of the sub-assembly, the separating partition being rigidly fixed to the inner fixed structure and the torque box, and connected to the translating cowl via a sliding connection.

Abstract: A device, intended to be fixed on a wall, for absorbing electromagnetic waves. The absorption device comprises a metal plate intended to be fixed on the wall, a dielectric panel at a distance from the metal plate and delimiting, with the metal plate, a volume between the metal plate and the dielectric panel, an array of resistive dipoles, all the resistive dipoles being fixed on the same face of the dielectric panel, and each comprising two metal platelets at a distance from one another and a resistor arranged between the opposing edges of two neighboring metal platelets.

Abstract: Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role.

Abstract: An antifreeze system for a pipework, the antifreeze system comprising a framework configured to be fixed to the pipework, and at least one thermally insulating sleeve maintained around the pipework by the framework. Each sleeve is configured so that a space is produced between the sleeve and the pipework. The framework has an inlet and an outlet which are configured to produce a fluid communication between the outer side of the antifreeze system and the space. The inlet is fluidly connected to a source of hot air. Such an antifreeze system thus enables a flow of hot air around the pipework which thus prevents the liquid which flows therein from freezing.