Abstract: An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment.

Abstract: An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system.

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 an 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 vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades.

Abstract: An aircraft fuselage structure including at least a first and a second panel made of composite materials, placed side by side along a juncture and assembled with one another through at least one longitudinal joint. The longitudinal joint includes a double ? stringer including: a first and a second ? element each including a head and two cores, a first side base-plate situated in continuity of the first core of the first ? element, a second side base-plate situated in continuity of the last core of the second ? element, and a central base-plate connecting the second core of the first ? element with the first core of the second ? element and covering the juncture between the two panels.

Abstract: An aft part of an aircraft, including at least one engine assembly including a turbine engine and a turbine engine mounting pylon. A rigid structure of the mounting pylon includes a longitudinal central box and a connection box carried by the box and projecting from the box. The aircraft structure includes a fuselage lateral extension projecting from it, and the connection box is pressed into contact with the fuselage extension, below it, an attachment mechanism being arranged between these two entities.

Abstract: An installation of systems in aircraft fuselages such as thermophonic insulation mattresses and devices such as onboard systems, and bundles of electric wires or fluid ducts (air, water, oxygen, hydraulic fluid). A structure for fastening onto an aircraft fuselage includes at least frames and stringers, the structure further including: fuselage stabilizers connecting the frames and stringers, wherein two stabilizers of two consecutive frames face each other between the two consecutive frames; and a strip board connecting the two stabilizers and including a fastening mechanism arranged so as to receive corresponding fastening mechanisms of the insulation mattresses and the devices.

Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: A device and method for coupling two parts of a dc network, in which at least two capacitors respectively are installed, particularly onboard an aircraft. The device includes at least one static converter including at least one electronic coupling device, including at least one transistor and one diode, associated with an inductance, arranged between these at least two capacitors.

Abstract: An equipment burn-in method, which includes the equipment undergoing treatment in an oven, the oven undergoing cycles including at least one temperature-rise and/or temperature-fall transition, for which ventilation of the equipment is cut off during at least part of a temperature transition of the oven.

Abstract: A method for attenuating effects of turbulence on an aircraft, and a device to implement the method, the method including: using at least one signal on a wind profile signal, along an excitation direction, representing, at a given moment in an aircraft referential, a component along the excitation direction of the wind speed at a front of the aircraft according to a distance along a longitudinal direction of the aircraft; carrying out a frequency determination, in which the wind profile signal is processed to determine a frequential content; and selecting a control strategy to be adopted according to the previously determined frequential content, the strategy enabling at least one applicable control law to be identified.

Abstract: An engine unit for an aircraft including an engine, a device for hooking the engine, and a nacelle surrounding the engine and provided with fan cowls, the device for hooking including a rigid structure and a front aerodynamic structure whereon the fan cowls are articulated, the front aerodynamic structure including a cradle with a rear mechanism of hooking mounted on the rigid structure. The cradle also includes a front mechanism of hooking mounted on an air inlet of the nacelle.

Abstract: An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure.

Abstract: A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend.

Abstract: A method of fitting-out of an aircraft by laying of a floor, particularly in a cockpit of an aircraft, and such a fitted-out aircraft. The aircraft includes a fuselage part defining an interior volume and at least one internal on-board structure, the on-board structure being secured to the fuselage part and configured to accept a floor module. The method then involves introducing the floor module into the volume and attaching the floor module to the on-board structure.

Abstract: A front aircraft landing gear built into an electric control including: a landing gear leg to be pivotably mounted on a structure of the aircraft between a retracted position and an extended position; an actuating cylinder moving the landing gear leg from the retracted position to the extended position; a strut that maintains the landing gear leg in the extended position thereof; an uplock housing that maintains the landing gear leg in the retracted position thereof; an uplock housing an operating mode control and a backup mode for the same housing; and four stress-adding points adding stress to the aircraft structure, namely two points for the pivotal movement of the landing gear leg and two points for the pivotal movement of the strut.

Abstract: A method of manufacturing a blank made from thermoplastic composite material, in which a pressure and temperature cycle is applied by pressing on top of a compacting plate that is itself on top of a stack of fibers including continuous fibers pre-impregnated with a thermoplastic resin, which stack has been previously placed on a board with the film enveloping the stack being brought into contact with fixing blocks arranged at the periphery of the board, and by heating the stack so as to reach at least the melting temperature of the resin while leaving the film infusible and smooth, and allowing the gas(es) present in the stack to escape through at least one opening left in the enveloping film and then through at least one emerging channel formed in the compacting plate and/or in the board and/or in the fixing blocks.

Abstract: A frame switching device for an AFDX network, the device including a first port, configured to be connected to a frame switch of the network or else to a terminal, for example a computer, and a plurality of second ports configured to be respectively connected to on-board pieces of equipment. Each frame incident on the first port is replicated on each of the second ports. The second ports are periodically polled in turn, each frame present on a second polled port being transferred onto the first port.

Abstract: A compact device for ejecting a fluid including two chambers separated by a separating element of piston type. One of the chambers contains the fluid intended to be ejected, the other chamber is a pressurization chamber, the pressurization of which can cause translational movement of the separating element and ejection of the fluid. The pressurization chamber includes a thimble capable of sealably separating the inside of the pressurization chamber from the side walls of the reservoir. Thus, a seal between two chambers is perfect and durable without degrading slidability of the piston.