Patents Assigned to Airbus Operations
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Publication number: 20190184894Abstract: A system for generating a moving image in an aircraft, includes a multiplicity of LEDs, a signal input unit, into which image information is fed, a signal output unit coupled to the multiplicity of LEDs and configured for transmitting the image information to the multiplicity of LEDs, and a gyroscopic sensor for acquiring a spatial position of the aircraft, wherein the LEDs are arranged in the form of a grid on an aircraft interior wall, such that the image is a schematic reproduction of the image information and the signal output unit is coupled to the gyroscopic sensor in such a way that the position of the image is matched to the spatial position of the aircraft, such that the image forms an artificial horizon for a viewer.Type: ApplicationFiled: December 14, 2018Publication date: June 20, 2019Applicant: Airbus Operations GmbHInventor: Marvin Bruhn
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Publication number: 20190185130Abstract: An electrical and electronic bay for an aircraft includes a central area forming a free space, a peripheral side area provided for the arrangement of supporting structures and being placed around said central area, and a lower area placed below the central and peripheral side areas and in which the access opening is placed in said central area. Such an electrical and electronic bay is used in particular to optimize the areas dedicated to the incorporation of electronic equipment in aircraft.Type: ApplicationFiled: December 17, 2018Publication date: June 20, 2019Applicant: Airbus Operations S.A.S.Inventors: Bernard Guering, Laurent Saint-Marc
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Publication number: 20190185129Abstract: A pressure bulkhead for a pressurized cabin of an aerospace craft includes: a pressure wall and a frame for connecting the pressure wall to the aerospace craft; wherein the frame is connected to the pressure wall; wherein the pressure wall has: a core layer; and a first covering layer and a second covering layer; wherein the core layer is arranged between the first covering layer and the second covering layer; and wherein the core layer comprises an auxetic foam. Such a pressure bulkhead has increased stiffness, thus ensuring that smaller bending deformations and lower stresses occur. Hence costs can be saved, and the volume of the pressurized cabin which can be made available to the crew and passengers is maximized.Type: ApplicationFiled: November 16, 2018Publication date: June 20, 2019Applicant: Airbus Operations GmbHInventors: Zhenggui Wang, Muhsin Öcal
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Patent number: 10322791Abstract: An aircraft wing torsion box having a front associated with a leading portion of the wing torsion box and a rear associated with a trailing portion of the wing torsion box. The wing torsion box includes a support member having a front spar and a rear spar and a connecting portion between the front and rear spars, the connecting portion includes at least one interposing spar, at least one portion of upper wing skin; and at least one portion of lower wing skin, and at least one portion of the upper wing skin and at least one portion of the lower wing skin being supported by the support member.Type: GrantFiled: December 22, 2015Date of Patent: June 18, 2019Assignee: Airbus Operations LimitedInventor: Steven Evans
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Patent number: 10322793Abstract: A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.Type: GrantFiled: October 17, 2016Date of Patent: June 18, 2019Assignee: AIRBUS OPERATIONS S.L.Inventors: Fernando Pereira Mosqueira, Jesús Javier Vázquez Castro
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Patent number: 10326985Abstract: A display system for a cockpit of an aircraft comprises a display device configured to be secured to a user's head in the cockpit of the aircraft. A display computer is configured to control the display of information on the display device. The display computer is configured to determine a distance between the head of the user and an element of the cockpit intersecting with a direction corresponding to a current orientation of the head of the user, when the user looks inside the cockpit, and to control a virtual display distance of the display device, corresponding to the distance between the head of the user and the element of the cockpit.Type: GrantFiled: December 6, 2017Date of Patent: June 18, 2019Assignee: AIRBUS OPERATIONS SASInventors: Cedric Descheemaeker, Javier Manjon Sanchez
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Patent number: 10322812Abstract: A device providing a signal indicating whether a deployed aircraft evacuation slide is ready for use. A tilt sensor measures tilt angle about a predetermined axis and a tilt sensor measurement signal is provided. An inertial sensor detects acceleration and provides an inertial sensor measurement signal. A slide signal input terminal receives a slide signal indicating deployment of an evacuation slide and of a deployment length. A tilt angle signal output terminal at which a tilt angle signal is provided, and a slide status output terminal and a control unit to determine, based on the detected acceleration, a moment when the device is at rest with respect to earth and to set orientation of the reference plane to a predetermined orientation. The control unit stores data depending on position of a door, and can determine a slide length. A slide status signal is provided at the slide status output terminal.Type: GrantFiled: November 2, 2016Date of Patent: June 18, 2019Assignee: Airbus Operations GmbHInventors: Thorsten Knijnenburg, Andreas Harzmeier, Ilja Waigl
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Patent number: 10316693Abstract: An aircraft tail region including a cooling system installed in the aircraft tail region. The cooling system comprises a cooler, which forms a section of an outer skin of the aircraft tail region, and includes coolant channels allowing a flow of ambient air therethrough, and extending from a first surface of the cooler to a second surface of the cooler. The cooling system also includes a fan system, which is adapted to convey ambient air through the coolant channels of the cooler at least in specified operating phases of the cooling system, and a first opening, which is formed in the outer skin of the aircraft tail region, and which allows, in conveying operation of the fan system, ambient air which is supplied through the coolant channels of the cooler into an interior of the aircraft tail region to be discharged back into the aircraft environment.Type: GrantFiled: September 24, 2013Date of Patent: June 11, 2019Assignee: AIRBUS OPERATIONS GMBHInventors: Ralf-Henning Stolte, Udo Krause, Bruno Stefes, Christian Mueller, Florian Elken, Uwe Wollrab
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Patent number: 10316996Abstract: An aircraft pipe coupling includes a first pipe end and a second pipe end connected to each other by a fastener. A locking collar restricts the rotational movement of the first pipe end, the second pipe end, and the fastener with respect to one another. The locking collar includes a first engagement portion and a second engagement portion, one of the engagement portions includes a resiliently deformable engagement surface. The first engagement portion is located over and engaged with the fastener, and the second engagement portion is located over and engaged with the second pipe end.Type: GrantFiled: September 8, 2015Date of Patent: June 11, 2019Assignee: Airbus Operations LimitedInventors: Timothy Wollaston, Samuel Evans
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Patent number: 10319238Abstract: A method for transmitting flight parameters from a leading aircraft (L) to at least one intruding aircraft (I), wherein, the transmission is effected by a collision avoidance system of TCAS type. The transponder of the leading aircraft (L) is configured to measure the spectrum of an interrogation signal received from the intruding aircraft (I) and to compare the power of the spectrum to a threshold power. If the power of the interrogation signal is greater than or equal to the threshold power, then the intruding aircraft (I) is eligible to receive flight parameters from the leading aircraft to be able to compute the position of the centers or the force of circulation of wake vortexes (14L, 15L) generated by the leading aircraft (L). The exchange of flight parameters from the leading aircraft only to eligible intruding aircraft makes it possible to not exceed the maximum automated communication bandwidth capacity.Type: GrantFiled: April 19, 2018Date of Patent: June 11, 2019Assignee: Airbus Operations S.A.S.Inventor: Jean-luc Robin
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Patent number: 10320909Abstract: An apparatus for controlling appliances aboard a vehicle, including a first data processing device having a network interface that can have a vehicle network for bidirectional data transmission between the first data processing device and connected network appliances. Also provided are an input/output device, a graphics processor device connected to the screen thereof and to the first data processing device, a user interface module provided in the first data processing device and that implements a graphical user interface having pages, and at least one separate second data processing device connected to the first data processing device via a separate bidirectional data link and having a network interface for connection to a vehicle network. Via each bidirectional data link it is exclusively possible to transmit predefined data records having data of predefined data types for display on pages from the second data processing device to the first data processing device.Type: GrantFiled: March 5, 2014Date of Patent: June 11, 2019Assignee: Airbus Operations GmbHInventor: Christian Riedel
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Patent number: 10318893Abstract: A system and a method for dynamic in flight seat management of an aircraft are provided. The system comprises an on board memory unit for storing the current booking status of the seats of the aircraft. Furthermore, the system comprises an output unit for providing the current booking status to a user and an input unit for receiving requests from a user to change the booking status. Therein, the system is adapted to change the booking status in real-time during the flight. In this way, passengers can book a time-limited upgrade during the flight.Type: GrantFiled: August 14, 2014Date of Patent: June 11, 2019Assignee: AIRBUS OPERATIONS GMBHInventors: Gerd Dueser, Frank Quatmann
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Patent number: 10315360Abstract: A manufacturing method of structures formed co-bonding second structural components to a first structural component. The method comprises the following steps: a) preparing for each second structural component an ensemble wherein a preform of the second structural component, surrounded by a band of a suitable material to form a vacuum bag, is disposed between curing tools which are thus in contact with the bag and not with the preform; b) positioning the ensembles on the first structural component and forming the vacuum bag for the complete structure joining the bands and complementary pieces; c) applying to the resulting assembly an autoclave cycle.Type: GrantFiled: April 28, 2016Date of Patent: June 11, 2019Assignee: Airbus Operations S.L.Inventors: Yolanda Miguez Charines, Francisco Javier Jordan Carnicero, Augusto Perez Pastor, Angel Pablo Gordo, Laura Alvarez Antonon
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Patent number: 10319359Abstract: A masking method includes: a step of choosing a generating element which is part of the skin of an aircraft, a first step of measuring a fundamental frequency of a sound signal emitted by the generating element, a step of selecting a masking element which is part of the skin, a second step of measuring a fundamental frequency of another sound signal emitted by the masking element, a step of modification of the structure of the masking element in such a way as to shift the fundamental frequency of the sound signal emitted by the masking element to a frequency lower than the fundamental frequency of the sound signal emitted by the generating element. Such a masking method thus makes it possible to mask the sound signal emitted by the generating element by the sound signal emitted by the masking element.Type: GrantFiled: July 27, 2017Date of Patent: June 11, 2019Assignee: Airbus Operations S.A.S.Inventors: Nicolas Molin, Isabelle Boullet
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Patent number: 10315765Abstract: A service box for storing in a storage rack arrangement of a cargo container of a vehicle, in particular an aircraft, including a rectangular bottom wall, a rectangular upper wall, side walls and narrow end walls and forms an interior space adapted to receive a trolley for catering goods. The service box is provided with a door at at least one of its narrow ends, the door forming at least the main part of the narrow wall and in the open state permits insertion and removal of the trolley and in the closed state provides for an essentially closed space for the trolley.Type: GrantFiled: December 10, 2015Date of Patent: June 11, 2019Assignee: Airbus Operations GmbHInventors: Ingo Roth, Andreas Köhler, Sassa Nadine Boos, Arne Stoldt, Sascha-Jay Salvador, Engin Özkan, Lasse Jensen
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Publication number: 20190170387Abstract: A device for securing at least one insulating tube on a duct, includes an inner ring configured to be mounted on the duct, an outer ring coaxial to the inner ring, and a transverse web linking the inner and outer rings, the inner and outer rings and the transverse web forming two recesses, arranged on either side of the transverse web, each configured to receive an end of an insulating tube.Type: ApplicationFiled: November 26, 2018Publication date: June 6, 2019Applicant: Airbus Operations S.A.S.Inventor: José Lopez
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Publication number: 20190173801Abstract: Described is a method for transmitting continuously created data items from an aircraft to a receiver. The data items are of a plurality of data types and each have a different priority. For each data type a live LIFO buffer and a main LIFO buffer are provided. In a regular operation mode continuously created data items are continuously stored in the main buffers. In a transmission operation mode continuously created data items are continuously stored in the live buffers, consecutive data packets are transmitted and for each data packet the data is selected from the buffers, wherein data items stored in live buffers are transmitted before data items stored in main buffers and data items of higher priorities are transmitted before data items of lower priorities. Further, a transmitter and an aircraft are described and claimed.Type: ApplicationFiled: January 30, 2019Publication date: June 6, 2019Applicant: Airbus Operations GmbHInventors: Uwe Bartels, Marcus Venzke, Maurice Girod, Maciej Mühleisen, Christoph Petersen
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Patent number: 10308351Abstract: Aircraft landing gear comprising a locking assembly including a pair of spaced-apart bearing pads and a lock member. The lock member is moveable between a locked position in which it engages the bearing pads to prevent pivotal movement of a steerable axle, and an unlocked position in which the member is disengaged from the bearing pads such that movement of the axle can occur. The lock member has a guide surface on either side for guiding the member and bearing pads into alignment during movement of the member from the unlocked to the locked position. The guide surface comprises a first inclined portion for moving the member towards alignment with the bearing pads and a second inclined portion, spaced apart from the first portion, for moving the member into alignment with the bearing pads such that the member and bearing pads are aligned in a movement comprising two stages.Type: GrantFiled: May 27, 2016Date of Patent: June 4, 2019Assignee: AIRBUS OPERATIONS LIMITEDInventor: Robert Ian Thompson
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Patent number: 10308369Abstract: An aircraft is disclosed having a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.Type: GrantFiled: December 14, 2018Date of Patent: June 4, 2019Assignee: AIRBUS OPERATIONS LIMITEDInventors: Roger Laguia-Barnola, Matthew Noel Orchard, Norman Wood
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Patent number: 10307860Abstract: A method of making an aerospace component such as a spar for an aircraft wing is disclosed. The method includes placing two billets of different alloy in abutting relation, there being no voids or channels formed therebetween, partial penetration friction stir welding together the two billets from opposing sides of the billets, the welds so formed being separated by a central region formed partly by one billet and partly by the other billet, and then machining away material. The machining may be performed so as to leave no portion having a partial penetration friction stir weld, so as to remove all of the central region, and so as to form a multi-alloy spar having at least one transverse web section having a slot formed at least in part by the removal of the central region.Type: GrantFiled: July 10, 2017Date of Patent: June 4, 2019Assignee: Airbus Operations LimitedInventor: Robert Maziarz