Abstract: A heatable floor panel for an aircraft, with a supporting level, a heat-generating level and a heat-conducting level. The heat-generating level comprises a fiber composite layer with fibers and with a matrix surrounding the fibers. The fibers are at least partially formed as conducting fiber, and the conducting fibers are formed as carbon fibers with an electrically insulating coating. The conducting fibers integrated in the floor panel in order to conduct a heating current through them. Due to the electrically insulating coating of the conducting fibers, leakage currents are avoided. The carbon fibers serve not only as heating elements, but, at the same time, also as reinforcing fibers of the fiber composite layer or of the floor panel.
Abstract: A mold assembly for manufacturing a composite part with a stiffener, the mold assembly includes a bottom mold configured to form a first surface of the composite part, wherein the bottom mold has at least one elongated recess configured to form a stiffener in the composite part; a feeder unit having a shape corresponding to the at least one elongated recess, wherein the feeder unit is configured to fit at least partially into the at least one elongated recess; and a top mold configured to form a second surface of the composite part opposite to the first surface. Also a method of manufacturing a composite part using such a mold assembly, which includes draping a flat laminate over the bottom mold and pushing portions of the laminate into the at least one elongated recess.
Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.
Type:
Grant
Filed:
March 31, 2022
Date of Patent:
November 7, 2023
Assignee:
Airbus Operations SAS
Inventors:
Laurent Sammito, Jean Geliot, Thierry Theron
Abstract: A system for ensuring proper installation of components of a cargo management system within a cargo hold has cleats rigidly attached to a floor of the cargo hold, a first subset of the cleats having insets of a first shape, a second subset of cleats having insets of a second shape, keys and rotatable fasteners attached to the components of the cargo management system, a first subset of the keys having the first shape and a second subset of the keys having the second shape. The first subset of keys can only engage with the first subset of cleats and the second subset of keys can only engage with the second subset of cleats and the rotatable fasteners utilize a rotary movement to secure the components of the cargo management system to a respective cleat, against which the rotary fastener is engaged.
Type:
Grant
Filed:
June 29, 2021
Date of Patent:
November 7, 2023
Assignee:
Airbus Operations GmbH
Inventors:
Oliver Nuessen, Martin Guse, Dirk Meiranke, Sascha Nowarre, Dennis Fischer, Uwe Panzram, Matthias Horst
Abstract: A method for manufacturing a component by stacking layers of material that are each obtained by depositing and melting, continuously, a material by virtue of an energy beam of which at least one feature is controlled by a control current intensity. The manufacturing method includes a step of monitoring the control current intensity, a step of comparing the monitored control current intensity with a given threshold and a step of stopping the manufacturing method when the control current intensity is above the given threshold. This momentary stopping of the method makes it possible to significantly reduce the risks of energy runaway liable to destroy the deposited material bead and the neighboring structure.
Abstract: A heated leading edge structure for an aircraft, including a leading edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, and including a heater device mounted to the inner surface of the leading edge panel for heating of the leading edge panel. The heater device is mounted to the inner surface of the leading edge panel in a detachable manner to provide a simple, lightweight and cost-efficient leading edge structure that enables a simple, quick and efficient maintenance.
Type:
Grant
Filed:
March 21, 2022
Date of Patent:
November 7, 2023
Assignee:
Airbus Operations GmbH
Inventors:
Bernhard Schlipf, Alexander Huber, Timo Stöven
Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.
Type:
Grant
Filed:
September 19, 2022
Date of Patent:
November 7, 2023
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Michael Berjot, Thomas Robiglio, Karla Mariana Arellanes Mendoza
Abstract: A method for detecting potential dents in a surface includes providing a flying drone with an image acquisition device and a light source, the shape of which is elongate, and a data processing device. At least one series of images is acquired of portions of the surface by the image acquisition device by moving the flying drone past the surface along a trajectory so that, for each image of the series, the light source is illuminating the corresponding portion of the surface. The data processing device is operated to analyze the shape of a specular reflection of the light source in images of the series of images to estimate the position of any dents in the surface.
Abstract: A method for removing a blind rivet includes a workpiece arrangement having first and second surfaces and a connecting hole. A blind rivet is fixed in the hole and has a shell and screw through the shell extending coaxially along a common center axis, the shell having a shell head portion, straight portion, deformation portion and threaded portion having an internal thread. The straight portion is in the hole and the deformation portion and the threaded portion protrude out of the hole, the screw having a screw head portion and pin portion having an external thread. The screw is in the shell such that the deformation portion of the shell is deformed where the outside diameter of the deformed deformation portion is larger than the diameter of the hole. The shell is cut in the region of the thread portion and/or the deformation portion, and the blind rivet is removed from the hole.
Abstract: A turbofan with a sliding element, rotary blades that can rotate between stowed and deployed positions, and a maneuvering system which moves each blade when the sliding element moves and which includes, for each blade, a rotary main shaft, for each main shaft, a transmission lever rigidly secured to the main shaft, at least two connecting strips articulated to one another, wherein each connecting strip is associated with at least three main shafts, the transmission levers of which are articulated to the connecting strip, and a drive system which rotates the first connecting strip when the sliding element moves. The use of rotary blades on the sliding element and the simplified maneuvering system makes the assembly more lightweight compared to the use of conventional reverser doors.
Type:
Grant
Filed:
June 21, 2022
Date of Patent:
October 31, 2023
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Simon Vanderbauwede, Lionel Sillieres, Antoine Cousin
Abstract: A structure formed from composite material and method of forming a composite structure is disclosed in which one or more metal layers are disposed on a composite structural member.
Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.
Type:
Application
Filed:
March 28, 2023
Publication date:
October 26, 2023
Applicants:
AIRBUS SAS, Airbus Operations SAS, AIRBUS OPERATIONS LTD, Airbus Operations SL, Airbus Operations GmbH
Inventors:
Elisa Alvarez López-Herrero, Matthias Wolff, Alexander Broer, Rainer Tegtmeyer, Michael Wießmeier, Till Marquardt, André Anger, Anna-Katrin Wengorra, Marco Dias Figueiredo, Jose Luis Martinez Munoz, Alberto Gallegos Elvira, Kaya Sahin, Guillaume Gallant, Kasidit Leoviriyakit, Philip Wright
Abstract: A method for parameterizing a photogrammetric cable robot, having a frame, a mobile platform carrying a camera and cables, each cable extending from a mobile platform attachment point to a position-adjustable exit point, while remaining linked to the frame. The robot's maximum workspace is defined by the ranges of possible positions of the different cable exit points. A set of pairs of setpoint positions and orientations of the platform is determined, for performing the point measurements of a scene by photogrammetry. Then, a genetic algorithm comprising crossing, transformation and selection operations is applied to a population of vectors, each representing respective positions of cable exit points, the selection being made via a fitness function involving a first objective function evaluating a collision percentage and a second objective function evaluating a percentage violation of a mobile platform constraint of equilibrium, when the platform assumes the different setpoint positions and orientations.
Type:
Grant
Filed:
July 1, 2020
Date of Patent:
October 17, 2023
Assignee:
Airbus Operations SAS
Inventors:
Stephane Caro, Jean-Christophe Bry, Benjamin Rivalland
Abstract: An aeronautical composite structure configured to monitor a physical status of a bonded portion between structural components using a multi-core optical fiber. A method and system for monitoring the physical status of a bonded portion in an aeronautical composite structure also uses a multi-core optical fiber. More particularly, the invention relates to a structure and method for monitoring the physical status of a bonded portion of an aeronautical composite structure from its manufacturing to its use in flight using a multi-core optical fiber.
Type:
Grant
Filed:
June 15, 2021
Date of Patent:
October 17, 2023
Assignee:
Airbus Operations S.L.
Inventors:
Jacinto Enrique Rodriguez Serrano, Carlos Miguel-Giraldo
Abstract: An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.
Abstract: A method for connecting two components is proposed where a pressure acting on an adhesive between two join partners is supported by an auxiliary body which rests on a cutout of one of the components. Both components to be connected together and the auxiliary body are covered by a vacuum film and once the air has been sucked out, the compressive force is generated below the vacuum film.
Abstract: A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.
Abstract: A support stay is provided to improve failsafe configurations for movable parts of an aircraft. The support stay supports the movable part with a primary body and a separate secondary body. The primary body and the secondary body provide separate load paths. The secondary body is attached to the primary body by a mechanical connection, e.g., rivets. If one of the bodies becomes structurally compromised, for example by a crack, this configuration does not transfer shear load between the primary and secondary body, so that the other body does not become structurally compromised.
Type:
Grant
Filed:
February 25, 2021
Date of Patent:
October 10, 2023
Assignee:
Airbus Operations GmbH
Inventors:
Dort Daandels, Markus Gibbert, Blazenko Coskovic
Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.
Abstract: A flying drone for inspecting surfaces able to reflect light has a lighting device formed of two light sources each having a shape that is elongate in a longitudinal direction of each of the light sources, two first image acquisition devices, and a second image acquisition device between the two first image acquisition devices. The two light sources are respectively between the second image acquisition device and each of the first image acquisition devices. The flying drone allows effective detection of dents in surfaces by analyzing specular reflections, by the lighting device and of the first image acquisition devices, and effective detection of superficial defects on surfaces by the second image acquisition device, with the lighting device switched off.
Type:
Grant
Filed:
November 24, 2021
Date of Patent:
October 10, 2023
Assignee:
Airbus Operations (S.A.S.)
Inventors:
Nicolas Dominguez, François Lefebvre Albaret, Florent Montet, Jérome Fayolet