Abstract: A supply system for an aircraft, wherein the supply system has a supply module with outlet pipes, feed pipes connected to dihydrogen tanks, and means for channeling the dihydrogen in the feed pipes towards the outlet pipes, a distribution module having introduction pipes connected to the outlet pipes via heaters, distribution pipes connected to an engine, and means for channeling the dihydrogen in the introduction pipes towards the distribution pipes, and a control unit which commands the means of the supply module and of the distribution module depending on the information provided by the detection means. Also an aircraft with such a supply system.

Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.

Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

Abstract: A propulsion assembly for an aircraft, which has a propulsion system with a combustion chamber surrounded by a casing, a supply pipe that conveys dihydrogen to the combustion chamber through the casing via injectors, and a housing fastened to the casing in a sealed manner around the latter, wherein the supply pipe has a downstream part housed inside the housing and wherein the injectors are also housed inside the housing.

Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective cylinder fastened to the frame or to the casing by fastening means and positioned around the casing and between the supply pipe and the turbine. With such an arrangement, if a blade of the turbine became detached it would meet the protective cylinder blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

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: A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.

Abstract: A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

Abstract: A structure for an aircraft is disclosed including comprising at least one node which having first and second plates which are pressed against two opposite faces of a first reinforcement, and to which upstream and downstream reinforcements positioned on either side of the first reinforcement are connected. A connection system connecting the first and second plates is disclosed including at least one boss projecting from a surface of one of the plates pressed against the first reinforcement, for each boss, a housing recessed relative to a surface of the other plate pressed against the first reinforcement, configured to house the boss, and at least one fastening element, passing through the first reinforcement, connecting the first and second plates and spaced apart from the boss.

Abstract: An aircraft propulsion assembly including at least one first support that supports an electric propulsion system, at least one first attachment configured to connect the first support and a support structure of an aircraft, at least one second support distinct from and dissociated from the first support supporting a source of electrical energy configured to supply the electric propulsion system with electrical energy, as well as at least one second attachment configured to connect the second support and the support structure. An aircraft may include at least one such propulsion assembly. Given that the second support is distinct from and dissociated from the first support system, vibrations generated by the electric propulsion system are not transmitted to the source of electrical energy.

Abstract: A casing system mounted between an upstream solenoid valve of an upstream pipe and a downstream solenoid valve of a downstream pipe and which has a casing divided by a separation wall into a first volume which is placed under reduced pressure and a second volume, a heat exchanger which is fixed inside the casing with a first inlet which is arranged in the first volume and which is connected to the upstream pipe and a first outlet which is arranged in the second volume and which is connected to the downstream pipe, and a control unit which closes the solenoid valves if the deviation between two successive values of the pressure in the first volume or in the second volume is greater than a threshold.

Abstract: An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

Abstract: A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

Abstract: A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.