公开(公告)号：US20200377198A1

公开(公告)日：2020-12-03

申请号：US16886383

申请日：2020-05-28

Applicant: Airbus Operations, S.L.

Inventor： Alfonso PARRA RUBIO ,  Alvaro JARA RODELGO

IPC: B64C23/06

Abstract: A system for re-energizing streamflow in control surfaces of aircraft, comprising a panel provided with at least one aerodynamic element movable at least between a rest position, where the at least one aerodynamic element does not protrude from the panel, and a use position, where the at least one aerodynamic element protrudes from the panel, acting as a vortex generator. The at least one aerodynamic element is a die-cut portion of the panel that is hinged to a remainder of the panel.

公开(公告)号：US10830376B2

公开(公告)日：2020-11-10

申请号：US16190732

申请日：2018-11-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Francisco Javier Honorato Ruiz ,  Diego Sanchez Franco ,  Luis Rodriguez Urbina ,  Enrique Guinaldo Fernandez ,  Carlos Garcia Nieto

IPC: F16L3/08 ,  F16L3/123 ,  H02G3/00 ,  F16B5/06 ,  B29C65/50 ,  B29C70/74 ,  B29C65/00 ,  B29C65/56 ,  F16B9/02 ,  F16B7/04 ,  B29L31/00 ,  B29L31/30 ,  F16B2/10

Abstract: A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) including at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).

公开(公告)号：US10807732B2

公开(公告)日：2020-10-20

申请号：US15807857

申请日：2017-11-09

Applicant: Airbus Operations GmbH ,  Airbus Operations S.L.

Inventor： Daniel Reckzeh ,  Raul Carlos Llamas Sandin

IPC: B64D33/02 ,  B64C5/02 ,  B64C7/02 ,  B64D27/26 ,  B64D27/20

Abstract: An aircraft comprising a fuselage extending along a longitudinal axis between a fore section and an aft section, wings mounted to the fuselage, a tail unit mounted to the aft section of the fuselage, and a first propulsion unit and a second propulsion unit both mounted to the aft section of the fuselage in such a way that a first axis of rotation of the first propulsion unit and a second axis of rotation of the second propulsion unit both extend in a vertical center plane spanned by the longitudinal axis and a yaw axis. The provided centerline mounted double-engine aircraft allows for a simple manufacture, maintenance and retrofit of the engines, in that the first propulsion unit and/or the second propulsion unit are arranged outside the fuselage.

公开(公告)号：US20200291854A1

公开(公告)日：2020-09-17

申请号：US16814484

申请日：2020-03-10

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations, S.L.

Inventor： Bruno MEDDA ,  Esteban MARTINO-GONZALEZ ,  Thomas STEVENS ,  Julien CAYSSIALS ,  Juan Tomas PRIETO PADILLA ,  Adeline SOULIE ,  Didier POIRIER ,  Pierre-Alain PINAULT ,  Diego BARRON VEGA

IPC: F02C6/18 ,  B64D15/04 ,  B64D13/08

Abstract: An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

公开(公告)号：US10696377B2

公开(公告)日：2020-06-30

申请号：US15540480

申请日：2015-12-21

Applicant: Airbus Operations S.L.

Inventor： Elena Arévalo Rodríguez ,  Francisco José Cruz Domínguez ,  Ana Reyes Moneo Peñacoba

IPC: B64C5/02 ,  B64C1/26 ,  B64C1/06 ,  B64C1/12 ,  B64C1/14 ,  B64C1/16 ,  B64C7/00 ,  B64D41/00 ,  B64D29/04 ,  B64D29/08 ,  B64C1/10 ,  B64C1/00

Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

公开(公告)号：US10583936B2

公开(公告)日：2020-03-10

申请号：US16281962

申请日：2019-02-21

Applicant: Airbus Operations, S.L.

Inventor： Jesús Robledo Bueno

IPC: B64D47/04 ,  H05B33/08

Abstract: A method for dynamic control of runway illumination on aircraft, suitable for controlling the illumination of a light equipment comprising a LED matrix and refraction optics during a flight phase. The method comprises the steps of a) determining predefined flight dynamic movement equations for the flight phase, b) obtaining real data from autonomous sensors independent from the aircraft sensors, c) using extended Kalman Filter and algorithm taking into account the data from the autonomous sensors to obtain the aircraft dynamics data. This step c) comprises the c1) predict phase and c2) update phase, and d) applying the obtained aircraft dynamics data to light control laws affecting the light equipment.

公开(公告)号：US20200072797A1

公开(公告)日：2020-03-05

申请号：US16553327

申请日：2019-08-28

Applicant: Airbus Operations, S.L. ,  Airbus Operations SAS

Inventor： Aurelien RAUTUREAU ,  Carlos JUSDADO SERRANO ,  Yolanda DE FRUTOS GALINDO

IPC: G01N29/30 ,  G01N29/04

Abstract: A reference block for ultrasonic shear waves calibration, comprising slots, wherein the reference block has at least two different thicknesses, each thickness comprising two cavities with at least one slot being provided at each cavity. Preferably, the reference block comprises a plurality of steps, each step defining a different thickness.

公开(公告)号：US10532807B2

公开(公告)日：2020-01-14

申请号：US15402520

申请日：2017-01-10

Applicant: Airbus Operations, S.L.

Inventor： Carlos García Nieto ,  Enrique Guinaldo Fernández ,  Pablo Cebolla Garrofe ,  Iker Vélez De Mendizabal Alonso ,  Soledad Crespo Peña ,  Francisco Javier Honorato Ruiz ,  Álvaro Torres Salas ,  Álvaro Calero Casanova

IPC: B64C21/06 ,  B64F5/00 ,  B64C3/18 ,  B64C3/26 ,  B64C1/00

Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

公开(公告)号：US10399693B2

公开(公告)日：2019-09-03

申请号：US15180295

申请日：2016-06-13

Applicant: Airbus Operations, S.L.

Inventor： Angel Palomares Mora

IPC: B64D41/00 ,  B64D27/26

Abstract: An aircraft with an auxiliary power unit attached to the aircraft fuselage via an attachment system. The auxiliary power unit is placed inside the aircraft fuselage structure. The attachment system comprises a plurality of structural wires that link the auxiliary power unit to the aircraft fuselage structure. An attachment device is located at the end of each structural wire to connect the structural wire to the aircraft fuselage structure. Each attachment device comprises a metallic plate adjacent to the aircraft fuselage structure and a layer of damping elastomeric material adjacent to the metallic plate. The metallic plate is placed between the layer of damping elastomeric material and the aircraft fuselage structure. The attachment device is joined to the aircraft fuselage structure by attachment fasteners.

公开(公告)号：US20190263615A1

公开(公告)日：2019-08-29

申请号：US16287071

申请日：2019-02-27

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Ivan DOMINGUEZ GARCIA

IPC: B65H18/10 ,  B65H18/02

Abstract: A device for winding an ancillary material which includes: a support mechanism; at least two slats connected to the support mechanism and arranged substantially forming a tubular element, defining an internal section between them; a bar; and an end part; wherein the bar is rigidly attached at a first end to the support mechanism, arranged longitudinally along the inside of the internal section, and configured for being connected at a second end to the end part; and wherein the end part includes a connection mechanism configured for being coupled, in a manner which can be uncoupled, with the second end of the bar, such that in the coupled state of the end part, the internal section defined by the slats is larger than it is in the uncoupled state of the end part.