公开(公告)号：US11220354B2

公开(公告)日：2022-01-11

申请号：US16515330

申请日：2019-07-18

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Esteban Martino-Gonzalez ,  Alberto Arana Hidalgo ,  Melania Sanchez Perez ,  Carlos Garcia Nieto ,  Jesus Javier Vazquez Castro ,  Edouard Menard ,  Fernando Iniesta Lozano ,  Maria Almudena Canas Rios

IPC: B64F5/10 ,  B64C1/26 ,  B64C3/26 ,  B64C5/02 ,  B64C1/00

Abstract: A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).

公开(公告)号：US20210339844A1

公开(公告)日：2021-11-04

申请号：US17241579

申请日：2021-04-27

Applicant: Airbus Operations S.L.

Inventor： Raul Carlos LLAMAS SANDIN

IPC: B64C1/06 ,  B64D29/04 ,  B64D27/24 ,  B64C3/50 ,  B64C9/32

Abstract: A rear end section for an aircraft, having a fuselage, a v-tail, and a thruster assembly including at least one propulsion device installed to ingest and consume air forming a fuselage boundary layer, a control surface attached at the rearmost section of the rear end, and a casing covering at least part of the propulsion device such that an air inlet and an air outlet are defined between the casing and the propulsion device. The air inlet is configured to permit passage of the fuselage boundary layer towards the propulsion device. The air outlet is configured to direct the airflow exhausted from the propulsion device into the control surface, to divert the airflow and provide vectoring thrust for the aircraft.

公开(公告)号：US11125728B2

公开(公告)日：2021-09-21

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：US11091271B2

公开(公告)日：2021-08-17

申请号：US16336956

申请日：2016-09-29

Applicant: Airbus Operations S.L.

Inventor： Carlos Casado-Montero ,  Victor Barreiro Rodriguez ,  Alexandra Carrasco Carrascal

IPC: B64D13/08 ,  B64D13/06 ,  B64D27/10 ,  B64D41/00

Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.

公开(公告)号：US20210187787A1

公开(公告)日：2021-06-24

申请号：US17129057

申请日：2020-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pablo CEBOLLA GARROFE

IPC: B29B11/06

Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

公开(公告)号：US20210138722A1

公开(公告)日：2021-05-13

申请号：US17091306

申请日：2020-11-06

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Asuncion BUTRAGUENO-MARTINEZ ,  Guillermo HERNAIZ LOPEZ ,  Jose SANCHEZ GOMEZ

IPC: B29C64/118 ,  B29C64/245 ,  B29C64/209 ,  B29C64/295

Abstract: A three-dimensional printing system including: a printing bed (3) where a printed material is deposited to form an object (1), a bobbin (4) configured to hold a filament (2) of thermoplastic material reinforced with a continuous electrically conductive element, a printing head (5) fed by the bobbin (4) and configured to deposit, e.g., print, the filament on the printing bed (3) to form an object and first and second electrodes (7, 8) connected to a power supply (6), wherein the first electrode (7) is connected to the printing bed (3), and the second electrode (8) is connected to the filament, wherein an electric circuit is created through the continuous conductive element in the filament to heat the printed material.

公开(公告)号：US10967979B2

公开(公告)日：2021-04-06

申请号：US16067655

申请日：2016-12-22

Applicant: Airbus Operations S.L.

Inventor： Jose Luis Martinez Munoz

IPC: B64D27/02 ,  B64C5/02 ,  B64D27/10 ,  B64C5/16 ,  B64C5/18 ,  B64D27/00

Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.

公开(公告)号：US20210063147A1

公开(公告)日：2021-03-04

申请号：US17005958

申请日：2020-08-28

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Alvaro JARA RODELGO

IPC: G01B11/30 ,  G01M5/00

Abstract: A method for simulating surface roughness on an aircraft part surface and a method for testing the behavior on flight of this aircraft part with surface roughness simulated, wherein the surface roughness simulation includes forming a roughness pattern on the aircraft part surface using a laser.

公开(公告)号：US10906628B2

公开(公告)日：2021-02-02

申请号：US16032246

申请日：2018-07-11

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Alberto Arana Hidalgo ,  Luis Rodriguez Urbina

IPC: B64C3/18 ,  B64C3/20 ,  B64C1/06 ,  B64C5/06 ,  B64C3/26 ,  B64C5/02 ,  F16L3/00 ,  H02G3/04 ,  B64C1/00

Abstract: A box structural arrangement (1) for an aircraft including first (2) and second composite layers (3), at least one spar web (4) extended between opposite edges of the first and second composite layers (2, 3) along a longitudinal direction, and a conduit piece (5) extended between opposite edges of the first and second composite layers (2, 3). The conduit piece (5) has a hollow section (6) comprising at least one conduit (7) dimensioned to receive pipes or harnesses and surrounded by a resilient material (8). The conduit piece (5) is mounted on the spar web (4) to provide a channeled box structural arrangement (1). The box structural arrangement can be applicable in a torsion box or a wing. The invention further refers to a method for manufacturing the box structural arrangement for an aircraft.

公开(公告)号：US10850832B2

公开(公告)日：2020-12-01

申请号：US15817388

申请日：2017-11-20

Applicant: Airbus Operations S.L.

Inventor： Alfonso González Gozalbo

IPC: B64C23/06 ,  B64C9/34 ,  B64C9/22 ,  B64C5/02 ,  B64C9/08 ,  B64C3/14 ,  B64C21/08

Abstract: A lifting surface of an aircraft, comprising a leading edge and a notch located in the leading edge. The notch comprises two walls adapted to be parallel to the direction of the incident flow to the lifting surface and a third wall adapted to face the incident flow to the lifting surface when it is in flight. The lifting surface also comprises a retractable cover element, the notch and the retractable cover element being configured such that when the retractable cover element does not cover the notch, the notch is exposed to the incident flow generating a vortex which increases the lift force of the lifting surface, delaying stall.