Abstract: A guiding device includes a rail which extends in a direction, a plurality of runners distributed in the direction, and, for each runner, at least one runner/rail connection connecting each runner and the rail, configured to allow each runner to pivot independently from the other runners relative to the rail, around an axis of pivoting parallel to the direction.
Abstract: An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.
Type:
Grant
Filed:
April 2, 2015
Date of Patent:
December 10, 2019
Assignee:
Airbus Operations Limited
Inventors:
Christopher Lynas, Robert Thompson, Llifon Williams, John Hobday
Abstract: A furnishing item for a vehicle includes a first wall with an access opening situated therein, a door and an oblong flap. The door is arranged on the first wall so that it is swivable relative to the access opening around a first rotational axis. The oblong flap is arranged on the access opening in a vertical direction parallel to the door, and swivelably arranged on a second rotational axis, which is situated on a side of the access opening lying opposite the first rotational axis, and arranged parallel to the first rotational axis. The door and oblong flap extend from the first rotational axis or second rotational axis to the second rotational axis or first rotational axis and together completely close the access opening in a closed state.
Abstract: A connection device of a female pipe and a male pipe, with a head which is configured to be accommodated in a receptacle of the female pipe, and comprising a peripheral groove in which a seal is accommodated. The male pipe comprises at least one extension which is configured to limit the pivoting of the male pipe around an axis of rotation which is perpendicular to the longitudinal axis of the female pipe. This configuration makes it possible to limit the risks of damaging the seal.
Abstract: A desensitization device includes an acquisition module for acquiring the current flight parameters of the aircraft, a generation module for generating a first image depicting flight symbology including at least one reference zero pitch line, a generation module for generating a second image depicting topography of terrain overflown by the aircraft, a generation module for generating a third image including at least two portions separated by a separating line, a generation module configured to generate a fourth image by superposing the first image, the second image and the third image in that order, the first image being placed in the foreground, and a transmission module configured to transmit, to a user device, a signal that is representative of the fourth image.
Abstract: A method for disinfecting a water system of an aircraft includes letting-in of hot water at an inlet of the water system by a first ground service unit; flushing the hot water from the inlet, through water pipes of the water system, to an outlet of the water system; and letting-out of the hot water at the outlet, by the first ground service unit or a second ground service unit; the hot water being flushed into the inlet and out of the outlet over a predefined disinfection period; and the hot water being provided at the inlet via a continuous-flow heater of the first ground service unit.
Type:
Application
Filed:
May 22, 2019
Publication date:
December 5, 2019
Applicant:
Airbus Operations GmbH
Inventors:
Sebastian Flashaar, Michael Rempe, Axel Schreiner
Abstract: A method for disinfecting a water system of an aircraft includes the introduction of damp hot air at an inlet of the water system by a ground service unit; flushing of the damp hot air from the inlet through water pipes of the water system to an outlet of the water system; and extraction of the damp hot air at the outlet; wherein the damp hot air is flushed into the inlet and out of the outlet over a predefined disinfection period, and wherein the damp hot air has a temperature between 60° C. and 80° C.
Type:
Application
Filed:
May 21, 2019
Publication date:
December 5, 2019
Applicant:
Airbus Operations GmbH
Inventors:
Sebastian Flashaar, Michael Rempe, Axel Schreiner
Abstract: An aircraft decompression assembly, comprising a cabin lining element, an element opening and an air channel adjacent to an element rear face and connected to the opening. A channel outlet, during normal assembly operation, discharges air exiting a cabin region delimited by the element through the opening into a secluded area between the element and an aircraft outer skin. A first decompression opening has a first decompression flap, which during normal operation, closes the first decompression opening and, in the event of a rapid decompression, opens the first decompression opening equalizing a pressure between the cabin region and the secluded area. A second decompression opening in the lining element has a second decompression flap which, during normal operation, closes the second decompression opening and which, in the event of a rapid decompression, opens the second decompression opening equalizing a pressure between the cabin region and the secluded area.
Abstract: In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.
Abstract: An aircraft monument for installation in an aircraft cabin. The aircraft monument comprises a movable side wall that is configured for separating the aircraft monument from a passenger area of the aircraft cabin, and that is configured for being moved. The aircraft monument further comprises at least one seat that is fastened to the movable side wall. Also disclosed is an aircraft area having a main aisle that extends along a longitudinal axis of an aircraft cabin, and having an aircraft monument situated next to the main aisle. Also disclosed is an aircraft that includes at least one aircraft area.
Abstract: A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.
Abstract: A system for controlling the thrust of the engines of an aircraft comprises a processing unit configured to receive an aircraft speed setting, to determine a control setting for at least one engine of the aircraft as a function of the speed setting and to transmit a setting to a controller of the at least one engine of the aircraft as a function of the control setting. The processing unit is further configured to receive a current turbulence level measurement information item and to add an additional speed setting, as a function of the turbulence level, to the speed setting.
Abstract: The disclosed subject matter relates to a component design system for generating aircraft component designs. The component design system includes a database having a set of rules representative for different load characteristics of different component geometries. The component design system further includes an input module for inputting user-specific load characteristics relating to an aircraft component to be generated and a processing unit for determining a variety of geometrically different aircraft component designs based on the input user-specific load characteristics and the set of rules. The disclosed subject matter also relates to an aircraft assembly system having a component design system, a method for generating aircraft component designs, a program element, and a computer-readable medium.
Abstract: A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.
Abstract: A flight control surface assembly adapted to be mounted to a main wing of an aircraft includes a flight control surface having a first portion and a second portion spaced from each other, a connection assembly adapted for movably connecting the flight control surface to the main wing, such that the flight control surface is selectively movable in a predetermined movement between a retracted position and an extended position with respect to the main wing, and for each of the flight control surface, a first roller with a first axial face and a second roller with a second axial face facing the first axial face mounted rotatably and coaxially. with a gap between the first and second axial end faces. A biasing mechanism biasing the first and second rollers towards each other, and a transmission mechanism coupled between the flight control surface and the rollers are included.
Abstract: A rudder bar includes a main module provided at least with pedals and with all the elements subject to maintenance, the main module being one-piece and detachable relative to a support frame integrated into the floor of the cockpit of the aircraft, so as to exhibit significant flexibility with respect to its maintainability, particularly in the event of the failure of a component, by allowing quick intervention both on a local level and an overall level.
Type:
Application
Filed:
May 14, 2019
Publication date:
November 28, 2019
Applicant:
Airbus Operations SAS
Inventors:
Bernard Guering, Matthieu De Kergommeaux
Abstract: A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.
Type:
Grant
Filed:
July 7, 2016
Date of Patent:
November 26, 2019
Assignee:
Airbus Operations GmbH
Inventors:
Wolfgang Eilken, Memis Tiryaki, Anton Arosenko
Abstract: A component for an aerofoil structure including a unitary member having a spar; a cover panel; and a substantially flat intermediate section which connects the spar to the cover panel. The spar, the cover panel and the intermediate section are integrally formed such that a first angle between the intermediate section and the cover panel and a second angle between the intermediate section and the spar are both in the range 90° to 180°.
Abstract: Automation of the extraction and the consolidation of maintenance data and relates to a method and a system for automatic integration of data among a plurality of maintenance data, the plurality of maintenance data being diffused through a set of maintenance documentary elements comprising a set of directed links, the system including a processor configured for extracting a subset of pertinent links according to predetermined extraction rules and for integrating into a resultant element pertinent maintenance data sourced from a subset of pertinent maintenance documentary elements associated with the subset of pertinent links.
Type:
Grant
Filed:
October 12, 2015
Date of Patent:
November 26, 2019
Assignees:
Airbus Operations (S.A.S.), Airbus (S.A.S.)
Inventors:
Dang Nguyen Manh, David Marty, Stéphane Sentenac, Maria del Carmen Trigo Romero, Mathieu Dhainaut, Jean-Claude Gallo, Jean-Max Huet
Abstract: A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.