Abstract: An electrical power supply system and method for an aircraft. The system includes an electrical network including primary generators powering the electrical distribution channels, and an homopolar generator making it possible to create an artificial neutral.

Abstract: The invention relates to an interface device (1) between an injection tube (2) and a mold (3) provided with an injection hole (4), characterized in that the interface device (1) comprises a terminal element for an injection tube, comprising an end piece (5a, 5b) inserted into one end of the tube (2) and a sealing ring (6) that slides onto the tube, and a means (7, 8) for holding and clamping the terminal element. Said means (7, 8), which is to be screwed into a mounting (9) that is rigidly connected to the mold and is arranged around the injection hole (4), forms a seal between an injection end of the end piece and a sealing surface (10, 11) of the mold at the injection hole. The dismantlable assembly comprises a screw-on socket (7) that has a supporting surface (7a) for the sealing ring (6).

Abstract: An electrical energy generating device for a propfan-type aircraft propulsion unit rotor. The propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit. The turbomachine generates a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown, and includes, within the moving annular part, a mechanism to transform thermal energy into electrical energy, preferably by thermal diodes. Such a device, as an example, can find application to a device for controlling a pitch of rotors of a propfan-type propulsion unit.

Abstract: A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of the outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular hot vein, which is concentric with the moving annular crown, and defined for part of its surface by an inner wall of the moving annular crown. The deicing device includes: a mechanism transforming thermal energy into electrical energy, within the moving annular part; a mechanism transferring the generated electrical energy towards the rotor blades; and a mechanism transforming the electrical energy into thermal energy onto at least a part of the surface of the blades.

Abstract: An aircraft turbomachine propeller including multiple blades assembled on a hub rotating around an axis of rotation of the propeller, that can reduce risks of loss of the blade following impact of a foreign body. At least one blade includes a recess opening radially towards the inside in the area of the base of this blade. A retaining device includes a moving retaining mechanism positioned in the recess and configured to be moved from a retracted position to a deployed blade-retaining position, and vice versa.

Abstract: An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).

Abstract: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: A method and device for loading and executing a plurality of instructions in an avionics system including a processor including at least two cores and a memory controller, each of the cores including a private memory. The plurality of instructions is loaded and executed by execution slots such that, during a first execution slot, a first core has access to the memory controller for transmitting at least one piece of data stored in the private memory thereof and for receiving and storing at least one datum and an instruction from the plurality of instructions in the private memory thereof, while the second core does not have access to the memory controller and executes at least one instruction previously stored in the private memory thereof and such that, during a second execution slot, the roles of the two cores are reversed.

Abstract: A device for processing faults, that detects and identifies faults, including, for at least part of the identified faults: a mechanism storing a log of occurrences of faults having a same identification, in a course of a plurality of flights; a mechanism determining an impact of each identified fault, on availability of aircraft in a predetermined duration, a mechanism associating a hierarchical attribute with each fault detected in a course of a flight, the hierarchical attribute being dependent on the log and on the impact; and a mechanism displaying identified faults associated with part of the hierarchical attributes. The device enables, in particular, maintenance operations or operations preparatory to maintenance to be better scheduled by virtue of hierarchization of faults displayed.

Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.

Abstract: An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly.

Abstract: An aircraft engine assembly including an annular load-transfer structure surrounding the central casing and being mechanically connected to a plurality of substantially planar structures arranged externally with respect to the plurality of substantially planar structures, and biasing it at a plurality of load application points. At least one connecting rod is associated with each of the load application points, the connecting rod being positioned tangentially with respect to the casing, and including an inner end connected to this casing, and an outer end connected to the structure so that it has extending through it an imaginary plane in which the annular structure is located and extends through the load application point.

Abstract: A system for communicating between a commercial aircraft and the base of the airline that chartered the same when the aircraft is itself located on the ground during the flight preparation phases and before unloading the commercial freight or passengers. A method implements such a communication system by the commercial flight staff and/or the aircraft captain to prepare a flight and the commercial freight unloading phase.

Abstract: The floor section for a vehicle cabin consists of a juxtaposition of profiled elements (9) of identical cross section. Each profiled element comprises: a mainly planar elongated cross member (10), positioned in a transverse vertical plane, this cross member (10) being designed to be attached at its two extremities to a frame (3) of the shell structure (1) of the vehicle. a generally flat elongated panel (11), positioned in a horizontal plane and comprising a region of overlap (15) along one of its longitudinal edges and a bearing region (16) along the other longitudinal edge. The region of overlap (15) and the bearing region (16) are of similar width and of total thickness less than or equal to the mean thickness of the panel (11). The panel (11) is perpendicular to the cross member (10), secured on one face, known as the underside, at least two points to the cross member (10) substantially in line with the middle of the bearing region (16).

Abstract: An electronic circuit, and a system including such a circuit, for determining a datum representative of a parameter of air surrounding an aircraft, including: a mechanism receiving, from a plurality of sources, a plurality of respective measurement data representative of a measured value of the parameter; a mechanism determining the datum representative of the parameter based on the measurement data; and a mechanism transmitting the datum representative of the parameter to a computer associated with an aircraft engine.

Abstract: An aircraft seat assembly structure (4) comprises at least one seat structure (5) that supports at least one seat, with which seat assembly structure is associated a reference frame that is defined by a longitudinal X-axis according to which the seat structure (5) comprises a front part and a rear part, by a Y-axis that is perpendicular to the X-axis, and that forms with said X-axis a horizontal XY plane when at least one seat is horizontal, and by a Z-axis that is perpendicular to the XY plane. In the front part, the seat structure (5) comprises a torsion bar (50) that is essentially parallel to the Y-axis that is equipped at a first lateral end (502) with a front lateral fastening device (500) that is designed to be made integral with lateral attachment means (26) of a shell structure (2) of an aircraft.

Abstract: The invention relates to a drilling system, in particular for two assemblies on which it is mounted. It makes it possible to drill holes through an overlap area, made using a drilling tool passing through a locking orifice formed on a tool holder of the drilling system, the drilling tool comprising a bearing mandrel as well as an expandable ring closely fitting the mandrel along a tapered contact surface and adapted so that a relative movement along a tapered contact surface. According to the invention, a relative movement is applied between the expandable ring and the mandrel so as to create, following locking of the ring in the locking orifice, a displacement of the mandrel bearing against the overlap area, through the locking orifice and towards said overlap area in order to exert pressure thereon, by displacement of said drilling tool relative to the tool holder via a sliding connection.

Abstract: A rear part of an aircraft, including a support structure for supporting engines, extending through the fuselage, through two openings distributed on either side of a vertical median plane of the aircraft. The support structure includes a first half-structure and a second half-structure respectively extending through the first and second fuselage openings, the first and second half-structures being joined to each other so that they can be disassembled in an inside space defined by the fuselage.

Abstract: A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Abstract: A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure.