Abstract: A method for producing a component with a surface that is suitable for plastic welding or adhesive bonding of two parts is provided. As a preparation step prior to joining, a filler sheet comprising a thermoplastic material or adhesive is arranged on a first surface of a first component and a structuring tool is arranged on the filler sheet. Mechanical force is applied to the structuring tool and heat is applied to the filler sheet such that the filler sheet is attached to the first surface of the first component and such that the structuring tool is partially embedded in the filler sheet. The structuring tool is subsequently removed from the filler sheet to produce a plurality of protrusions in the outer surface of the filler sheet. After surface structuring the first and second components are joined using any type of welding technique or joined using of adhesive bonding.
Type:
Grant
Filed:
January 24, 2023
Date of Patent:
February 11, 2025
Assignees:
Airbus Operations GmbH, Airbus Operations SAS
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 DC electrical network intended to supply electricity to an electrical load via an electric power source. A first pole of the electric power source is linked to first ends of two first electrical lines, second ends of which are linked to one another, and also to a first pole of the electrical load via two stages of a contactor. A second pole of the electric power source is linked to first ends of two second electrical lines, second ends of which are linked to one another, and also to a second pole of the electrical load via two other stages of the contactor. The electrical network further comprises a processing unit configured to control the contactor to open if current measurements correspond to currents flowing in opposite directions through the two first electrical lines or through the two second electrical lines.
Abstract: A tank system comprising a tank, a drainage line fixed in the bottom part of the tank and having a drainage port at each end and, for each drainage port, a funnel having a wall through which at least one window passes, a body that can move in translation, for each funnel, a plug that is secured to the body and arranged to be able to move inside said funnel between an open position and a closed position, and an arm, a first end of which is mounted in an articulated manner to the top part of the tank and a second end of which is mounted in an articulated manner on the body.
Type:
Grant
Filed:
June 22, 2023
Date of Patent:
January 28, 2025
Assignees:
Airbus Operations SAS, Airbus SAS
Inventors:
Thomas Andrieu, Jérôme Milliere, Julien Laverne, Jonathan Landolt
Abstract: An automatic trajectory generation system bringing a flying aircraft from a current position to a destination which: obtains polygons representing obstacles potentially encountered, each polygon associated with an altitude layer; defines two first tangential circles relative to a current direction of the aircraft flight, centered on the right and the left, relative to the aircraft current position; defining two second circles tangential relative to a direction to be followed to destination, centered on the right and the left, relative to the georeferenced destination position; defines a third circle around vertices of the polygons; and searches for a flyable lateral trajectory between the aircraft current position and the destination by bypassing the polygons by the vertices in searching for tangential trajectories between the circles, by observing a pre-established vertical trajectory profile, as well as the lateral margin and a vertical margin with the polygons.
Type:
Grant
Filed:
April 27, 2022
Date of Patent:
January 21, 2025
Assignee:
Airbus Operations SAS
Inventors:
Thomas Pastre, Jérôme Arnoux, Miguel Consiglieri Pedroso Mendes Dias
Abstract: A propulsion system having a chassis, two fan cowls and, for each one, an articulation system fastened between the chassis and the fan cowl, so as to move the fan cowl between a closed position and an open position and a locking device like a clamping screw, wherein each articulation system has, for each fan cowl, two pantograph hinges. With such an arrangement, each fan cowl moves away laterally as soon as its opening starts.
Abstract: An aircraft engine nacelle in which the inner fixed structure has a heat exchanger which is filled with a two-phase heat transfer fluid and which comprises a tube forming a loop with front, rear, lower and upper strands, and also a first complementary strand between the central zones of the front strand and of the upper strand, a second complementary strand between the central zones of the front strand and of the lower strand, a third complementary strand between the central zones of the rear strand and of the upper strand, and a fourth complementary strand between the central zones of the rear strand and of the lower strand.
Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.
Abstract: A tank configured to store a liquid and that includes at least one capture device which includes at least a first portion of a line situated at the bottom of the tank, close to its first end, and at least a second portion of the line situated at the bottom of the tank, close to its second end, each of the first and second portions including at least one orifice situated on the upper face thereof, a floating shut-off device for each orifice, the floating shut-off device being movable between an open position in which the floating shut-off device is spaced apart from the orifice and a closed position in which the floating shut-off device shuts off the orifice, the floating shut-off device having a density lower than that of the liquid stored in the tank.
Abstract: An aircraft including at least one pressure-relief device having: at least one fixed part, at least one deformable mobile wall configured to occupy a closed position in which it blocks an opening, at least one retaining system configured to retain the mobile wall in the closed position as long as the wall is not in a given deformed state, the retaining system including: at least one first slot through the mobile wall opening at the level of one of its edges, for each slot, a first retaining element fastened to the fixed part and configured to cooperate with the slot as long as the mobile part is not in the given deformed state.
Abstract: A resin film configured to hold a conductive metallic track against a panel. The resin film partially covers the conductive metallic track, such that the conductive metallic track has at least one region which does not have the resin film, so as to allow an electrical connection by contact. Thus, in the context of assembly on a panel, the metallic track incorporated between the panel and the resin film is protected, thus rendering this technical solution particularly robust. Furthermore, the resin film electrically insulates the metallic track from surrounding elements, and the regions which do not have resin film allow an electrical connection by contact.
Type:
Grant
Filed:
October 18, 2023
Date of Patent:
December 10, 2024
Assignees:
Airbus Operations SAS, Airbus Operations S.L.
Inventors:
Richard Murillo, Matilde De La Mota Mendiola, Nathan Lagache
Abstract: A tank including at least first and second portions connected by a connection ring and weld seams obtained by means of a friction welding method. The connection ring includes at least a first cylindrical portion fitted in the end of the first portion, at least a first shoulder protruding toward the outer zone of the tank relative to the first cylindrical portion and at least a first transverse web positioned approximately in the same transverse plane as the first shoulder. According to this configuration, the first cylindrical portion and the transverse web ensure that the forces generated by a friction welding head during the production of the weld seam which enables the tank to be closed are absorbed.
Type:
Grant
Filed:
November 29, 2022
Date of Patent:
December 10, 2024
Assignee:
Airbus Operations SAS
Inventors:
Benoît Penven, Laurent Costagliola, Hermann Walch
Abstract: A connecting rod with a body, first and second fastening heads provided at each end of the body and connected by first and second connection systems to first and second elements, the first fastening head comprising an extension which is screwed into a housing of the body to adjust the length of the connecting rod. The connecting rod includes an anti-rotation system with a key, positioned astride the first fastening head and the body, which has a first part cooperating with the body so as to be rotationally immobilized with respect to the body and also a second part cooperating with the first fastening head and the first connection system so as to be immobilized with respect to the first fastening head.
Abstract: A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.
Type:
Grant
Filed:
November 2, 2022
Date of Patent:
December 10, 2024
Assignee:
Airbus Operations SAS
Inventors:
Arnaud Bourhis, Florian Ravise, Maxime Zebian
Abstract: A device for handling a shaft forming a pivoting link between two parts, including a body configured to be inserted into the shaft, and blocked in translation with respect to the shaft along a longitudinal axis in a first direction, a compression nut screwed onto a threaded outer portion of the body along the axis in a second direction opposite the first direction, a bearing member positioned against one of the parts, and a return member configured to be compressed between the compression nut and the bearing member by the screwing of the compression nut and to be decompressed in the second direction under the action of the compression nut. This device allows the shaft of the pivoting link to be handled rapidly, and makes it possible to control the load applied onto the shaft during the handling thereof.
Abstract: A tank, in particular for a liquid hydrogen reservoir, provided with at least one dome fixed by way of an outer welded joint and having a central portion provided with at least one free end including a first connecting element and at least one dome provided with an open end including a second connecting element, the dome and the central portion being able to be joined together, the first connecting element and the second connecting element being configured to form, when the central portion and the dome are joined together, a protruding tab extending toward the outside of the tank and able to be welded to a protruding end, such a protruding tab making it possible in particular to join together the tank, this being done entirely from the outside of said tank, and to easily mount and dismount the dome, in particular without accessibility issues.
Abstract: An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.
Abstract: A measuring device able to be closely attached to an outer wall of a movable or fixed object located in an air flow. The measuring device comprises a flexible envelope having a cavity provided with an opening orifice. At least one optical fiber is provided in the cavity, the opening orifice of which is closed by the wall on which the envelope is applied. In this way, the fiber is positioned as closely as possible to the wall for which measurements are desired.
Abstract: An enclosure containing an inerting gas and at least one liquid to be discharged. This enclosure comprises at least one orifice positioned in its lower part and a liquid discharging system positioned at the orifice. This liquid discharging system is configured to take up a closed state and an open state in which the system allows the liquid to flow towards the outside of the enclosure and includes at least one element that is elastically deformable depending on the pressure inside the enclosure and, depending on its deformation, controls the open or closed state of the liquid discharging system. This solution makes it possible to achieve simple and automatic regulation of the volume of the liquid in the enclosure, without a sensor. An aircraft including at least one such enclosure is also provided.
Abstract: A head of a cutting device includes a base configured to be fixed to a machine tool, a cylindrical suction nozzle integral with the base, a connector integral with the base and configured to receive a suction pipe. The suction nozzle is perforated by at least one oblong hole, for example parallel to an axis of the suction nozzle.