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公开(公告)号：US10690632B2
公开(公告)日：2020-06-23
申请号：US15923418
申请日：2018-03-16
Applicant: Airbus Operations S.A.S. , AIRBUS SAS
Inventor： Alain Tissenier , Aurelien Rautureau
Abstract: An ultrasound probe for inspecting a bore opening onto a peripheral surface includes an offcentring device which includes at least two strips which are elastically deformable, connected to the ultrasound probe and configured to keep the emission head of the ultrasound probe pressed firmly against the wall of the bore that is to be inspected.
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公开(公告)号：US10689090B2
公开(公告)日：2020-06-23
申请号：US15625088
申请日：2017-06-16
Applicant: Airbus Operations S.A.S.
Inventor： David Perez
IPC: B64C1/14
Abstract: An aircraft includes a clearance between an opening and a door. The clearance communicates with a cavity and is oriented in a direction intersecting a flow direction of an air flow to the outside of the aircraft in flight. The aircraft further includes an upstream edge and an upstream outer surface situated in front of the clearance joined by a sharp edge with a bend radius of less than or equal to 1 mm, in order to limit the incidence of aerodynamic noise.
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公开(公告)号：US20200180065A1
公开(公告)日：2020-06-11
申请号：US16689353
申请日：2019-11-20
Applicant: Airbus Operations S.A.S.
Inventor： Stéphane Valadon , Benjamin Dod
Abstract: A process for welding a first part and a second part, includes: a linear friction step during which the two parts are rubbed against one another in a linear movement, a first cooling step during which the temperature of the parts thus welded is reduced to ambient temperature, a heating step during which the parts thus welded are heated to a temperature above a temperature of transition between a two-phase α-β field and a single-phase β field of the material constituting the two parts, and a second cooling step during which the temperature of the parts thus heated is reduced to ambient temperature. Such a process makes it possible to transform the structure of the welding zone and of the whole part thus produced into a lamellar α structure in a transformed β matrix which exhibits better damage tolerance.
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64.发明申请公开(公告)号：US20200165975A1
公开(公告)日：2020-05-28
申请号：US16682271
申请日：2019-11-13
Applicant: Airbus Operations S.A.S.
Inventor： Wolfgang Brochard , Laurent Cazeaux , Claire Maffre
IPC: F02C7/24 , B64D29/00 , G10K11/168
Abstract: A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.
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公开(公告)号：US10655563B2
公开(公告)日：2020-05-19
申请号：US15823053
申请日：2017-11-27
Applicant: Airbus Operations (S.A.S.) , Airbus (S.A.S.)
Inventor： Thierry Surply , Alain Porte , Patrick Oberle , Eric Haramburu , Thomas Sauvalle , Benoit Letay , Frédéric Piard , Vincent Billerot , Franck Oundjian
Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.
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Patent Agency Ranking
公开(公告)号：US20200094949A1
公开(公告)日：2020-03-26
申请号：US16578055
申请日：2019-09-20
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Philippe BERNADET
Abstract: A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.
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67.发明申请公开(公告)号：US20200023938A1
公开(公告)日：2020-01-23
申请号：US16193309
申请日：2018-11-16
Applicant: Airbus Operations GmbH , Airbus Operations S.A.S. , Airbus Operations Ltd.
Inventor： Saskia DEGE , Svenja JEGMINAT , Frank NIENABER , Jean GUILHAMET , Aeron Charles JONES
Abstract: A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport.
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公开(公告)号：US20190389584A1
公开(公告)日：2019-12-26
申请号：US16444419
申请日：2019-06-18
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Laurent SAINT-MARC , Bernard GUERING
Abstract: A coupling is disclosed providing fluidic continuity between first and second orifices of two portions of an air circuit which includes a flexible sleeve, a first frame connected in fluid-tight manner to a first end of the flexible sleeve and having a first opening, and a second frame, connected in fluid-tight manner to a second end of the flexible sleeve and having a second opening. The coupling is deformable so that the flexible sleeve may adapt to the variable spacing between two avionics racks and is able to compensate for a misalignment between the orifices of two portions of an air circuit.
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公开(公告)号：US10457377B2
公开(公告)日：2019-10-29
申请号：US15810459
申请日：2017-11-13
Applicant: Airbus Operations S.A.S.
Inventor： Christian Nguyen , Arnaud D'Ouince , Serge Blind , Gerard Millet , Thomas Menage
Abstract: A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.
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公开(公告)号：US20190316933A1
公开(公告)日：2019-10-17
申请号：US16378840
申请日：2019-04-09
Applicant: Airbus Operations (S.A.S.)
Inventor： Patrice Brot , Olivier Sapin
Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.
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