公开(公告)号：US11124285B2

公开(公告)日：2021-09-21

申请号：US16037269

申请日：2018-07-17

Applicant: Airbus Operations (S.A.S.) ,  Airbus (S.A.S.)

Inventor： Rodolphe Trouve ,  Jean-Claude Lacombe ,  Julien Rodes ,  Thomas Schutz

IPC: B64C3/26 ,  B64C3/18 ,  B64C3/20 ,  B29D99/00 ,  B29L31/30

Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.

公开(公告)号：US20210197984A1

公开(公告)日：2021-07-01

申请号：US17131206

申请日：2020-12-22

Applicant: Airbus (S.A.S.) ,  Airbus Operations (S.A.S.)

Inventor： Jean-Marc Datas ,  Jacques Bouriquet ,  Jean-Mickael Brindeau ,  André Aquila ,  Patrick Guibert

IPC: B64F5/10 ,  B64F5/50

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

公开(公告)号：US10891870B2

公开(公告)日：2021-01-12

申请号：US16126383

申请日：2018-09-10

Applicant: AIRBUS (S.A.S.)

Inventor： Nicolas Gros ,  Antoine Casta

IPC: G08G5/06 ,  G08G5/00 ,  G01C21/36 ,  G01C21/34 ,  G08G5/04 ,  G01C23/00

Abstract: A system (1) for aiding navigation includes an airport navigation device (2) to generate a ground route within the airport for an aided aircraft, a device (3) for determining the current position of the aided aircraft, a traffic surveillance device (9) for determining the location and type of nearby aircraft, a computation unit (10) for determining, for each segment of the ground route congestion information as a function of the position, type and speed of the nearby aircraft on each of the segments, and a display device displaying an airport map, the current location of the aided aircraft and congestion information for each segment.

公开(公告)号：US10800508B2

公开(公告)日：2020-10-13

申请号：US16458560

申请日：2019-07-01

Applicant: Airbus (S.A.S.)

Inventor： Didier Gendre ,  Dimitri Goutaudier

IPC: B64C1/12 ,  B64D45/00 ,  G01L5/00

Abstract: An aircraft with a system for estimating the parameters of an impact. The aircraft includes a skin forming an outer surface of the aircraft, the aircraft equipped with a system for estimating the parameters of an impact including an array of sensors attached to the skin and a central processing unit connected to the array, the array of sensors including a first set of sensors providing data relating to elastic waves, the central processing unit configured for assessing the parameters of an impact from the data of the sensor array and a response model of the skin to external excitations calculated from the modal properties of the skin.

公开(公告)号：US10683080B2

公开(公告)日：2020-06-16

申请号：US15466743

申请日：2017-03-22

Applicant: AIRBUS (S.A.S.)

Inventor： Feng Zhang ,  Li Guo

IPC: B64C9/00 ,  B64C9/08 ,  B64C7/00 ,  B64C9/02 ,  B64C5/02

Abstract: The present disclosure relates to a sealing device and an associated flight control surface mechanism and an associated aircraft. According to an aspect of the present disclosure, a sealing device (100, 100′) for a flight control surface mechanism (10) of an aircraft (1) is provided, the flight control surface mechanism includes a fixed part (20) and a movable wing surface (40), the movable wing surface is attached to the fixed part in a manner of being movable relative to the fixed part. The sealing device includes a fixed seal (120) attached to the fixed part and a movable seal (140, 140′) attached to the movable wing surface so as to move with the movement of the movable wing surface, the movable seal and the fixed seal cooperate with each other in order to provide an aerodynamic sealing for the flight control surface mechanism.

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

IPC: F02K1/70 ,  F02K1/72 ,  F02K1/76 ,  F01D25/24

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.

公开(公告)号：US20200094985A1

公开(公告)日：2020-03-26

申请号：US16588187

申请日：2019-09-30

Applicant: AIRBUS OPERATIONS GMBH ,  AIRBUS (S.A.S.)

Inventor： Frank QUATMANN ,  Nicolas JOURDAN

IPC: B64D45/00 ,  B64D11/00 ,  G09G3/20 ,  G09G3/34

Abstract: An aircraft area having a textile display, aircraft passenger seat having a textile display, and aircraft including an aircraft area. An aircraft area includes an interior component, a textile display on the interior component and including at least one textile fiber capable of changing a color at at least one section of the textile fiber, and a controller operatively coupled to the textile display and configured to change color of the at least one section of the textile fiber, such that the textile display displays information. An aircraft passenger seat includes a back rest, seat pan, and textile display integrated into a seat cover covering the backrest and/or the seat pan. The textile display includes at least one textile fiber capable of changing a color at at least one section of the textile fiber. An aircraft may include one or more aircraft areas and/or one or more aircraft passenger seats.

公开(公告)号：US20200088225A1

公开(公告)日：2020-03-19

申请号：US16569278

申请日：2019-09-12

Applicant: AIRBUS (S.A.S.)

Inventor： Jean-Mickael BRINDEAU ,  André AQUILA ,  Benoit RUSCASSIE

IPC: F16B5/06

Abstract: A double shear attachment device with an eccentric axis and eccentric sleeves, mechanical assembly including such a device and assembling process. The attachment device comprises an eccentric axis and two eccentric sleeves to mount on the eccentric axis to correct, by an appropriate positioning in rotation of the eccentric sleeves on the eccentric axis, the possible clearances between superposed circular holes of mechanical components that have to be linked together by the attachment device, the attachment device including also blocking structure configured to block in rotation the eccentric sleeves, the attachment device thus allowing to generate a quick and clear attachment, that is able to correct clearances locally.

公开(公告)号：US20200010166A1

公开(公告)日：2020-01-09

申请号：US16458560

申请日：2019-07-01

Applicant: Airbus (S.A.S.)

Inventor： Didier Gendre ,  Dimitri Goutaudier

IPC: B64C1/12 ,  B64D45/00 ,  G01L5/00

Abstract: An aircraft with a system for estimating the parameters of an impact. The aircraft includes a skin forming an outer surface of the aircraft, the aircraft equipped with a system for estimating the parameters of an impact including an array of sensors attached to the skin and a central processing unit connected to the array, the array of sensors including a first set of sensors providing data relating to elastic waves, the central processing unit configured for assessing the parameters of an impact from the data of the sensor array and a response model of the skin to external excitations calculated from the modal properties of the skin.

公开(公告)号：US20190283728A1

公开(公告)日：2019-09-19

申请号：US16356567

申请日：2019-03-18

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS (S.A.S.) ,  AIRBUS (S.A.S.)

Inventor： Rodrigo JIMENEZ ,  Brice CHERAY ,  Maud CONSOLA

IPC: B60T17/22 ,  B64F5/60 ,  B64D45/00 ,  B64C25/42 ,  F16D66/00

Abstract: An apparatus and method is disclosed for determining a temperature characteristic at a first location on a wheel or a brake assembly of an aircraft landing gear. The temperature characteristic at the first location is determined using relationship information based on a first temperature at a second location of the wheel or the brake assembly of the landing gear, the relationship information representing a relationship between the temperature characteristic at the first location and the first temperature. Also disclosed is a method to determine the relationship information.