公开(公告)号：US20210188421A1

公开(公告)日：2021-06-24

申请号：US17123468

申请日：2020-12-16

Applicant: Airbus Operations S.L.

Inventor： Javier Carlos GOMEZ DEL VALLE ,  Alberto BALSA-GONZALEZ

IPC: B64C3/14 ,  B64C3/18 ,  B64C5/02 ,  B64C3/16

Abstract: A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.

公开(公告)号：US20210147063A1

公开(公告)日：2021-05-20

申请号：US17096108

申请日：2020-11-12

Applicant: Airbus Operations S.L.

Inventor： Manuel KEMPF ,  Asuncion BUTRAGUENO-MARTINEZ ,  Jorge BALLESTERO MÉNDEZ ,  Fernando INIESTA LOZANO ,  Guillermo HERNAIZ LOPEZ ,  Javier GUERRERO MARTÍN ,  Alberto ARANA HIDALGO ,  Jesus Javier VAZQUEZ CASTRO

IPC: B64C1/40 ,  B32B7/12 ,  B32B3/12 ,  B32B9/04

Abstract: A fireproof and thermal insulator product which includes a honey-comb core infilled with Alkaline Earth Silicate material. The material of the honey-comb core can be metallic or polymeric. The product may further include a FRP layer, and/or a liquid barrier film, preferably being of thermoplastic material. An adhesive layer may be further deposited between the layer of honey-comb core infilled with AES and the layer of FRP.

公开(公告)号：US20210147062A1

公开(公告)日：2021-05-20

申请号：US17098772

申请日：2020-11-16

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Manuel KEMPF ,  Asuncion BUTRAGUENO-MARTINEZ ,  Jorge BALLESTERO MÉNDEZ ,  Fernando INIESTA LOZANO ,  Guillermo HERNAIZ LOPEZ ,  Pablo VAZQUEZ SANCHEZ ,  Alberto ARANA HIDALGO ,  Jesus Javier VAZQUEZ CASTRO

IPC: B64C1/40 ,  B32B7/12 ,  B32B7/08 ,  B32B9/00 ,  B32B9/04 ,  B32B27/12 ,  B32B27/30 ,  B32B27/36 ,  B32B27/28 ,  B32B9/02 ,  H01M2/02

Abstract: A fireproof and thermal insulator product (1) including an Alkaline Earth Silicate (AES) material (2), and at least one of the following: a liquid barrier film (5), an FRP (Fiber Reinforcement Plastic) layer (4), cork (3), wherein the liquid barrier film (5) and the FRP layer (4) are staked onto the AES material (2), and wherein the cork (3) material is also staked onto the AES material (2) or embedded into said AES material (2) in where said cork (3) is configured as a plurality of strips performing a grid structure infilled with the AES material (2).

公开(公告)号：US10975769B2

公开(公告)日：2021-04-13

申请号：US15842352

申请日：2017-12-14

Applicant: Airbus Operations, S.L.

Inventor： Leire Segura Martinez De Ilarduya ,  Alberto Juarez Becerril ,  Salvatore Demelas

IPC: F02C7/268 ,  F02C7/06 ,  F01D25/20 ,  F01D25/10 ,  F02C7/14 ,  F28D7/00 ,  B64D41/00 ,  F02C7/22

Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.

公开(公告)号：US10940956B2

公开(公告)日：2021-03-09

申请号：US15379879

申请日：2016-12-15

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Guilherme Barsali ,  Víctor Barreiro Rodríguez

IPC: B64D41/00

Abstract: A suspension system for an aircraft auxiliary power unit (1) located in a fuselage structure (2) including: auxiliary power unit attachment brackets (3) arranged to be attached to the auxiliary power unit (1); fuselage attachment brackets (4) attached to the auxiliary power unit attachment brackets (3) and coupled to the fuselage structure (2); two longitudinal elements (5) arranged to be attached to the fuselage structure (2) in the longitudinal direction of the aircraft for supporting the auxiliary power unit (1), the two longitudinal elements (5) and the plurality of fuselage attachment brackets (4) being connected such that the two longitudinal elements (5) support the plurality of fuselage attachment brackets (4), being the fuselage attachment brackets (4) slidably movable along the longitudinal elements (5) for introducing or extracting the auxiliary power unit (1) into the fuselage structure (2).

公开(公告)号：US10890971B2

公开(公告)日：2021-01-12

申请号：US16549240

申请日：2019-08-23

Applicant: Airbus Operations, S.L.

Inventor： Alberto Arana Hidalgo

IPC: G06F3/01 ,  B64F5/40 ,  B64F5/10 ,  G06F3/14

Abstract: A virtual reality (VR) system for providing a real time VR visualization of a target area of an aircraft that comprises one or more reference targets established in known locations in the target area of an aircraft, hand gloves, a plurality of sensing elements established on at least the operator's hand gloves, a reception device that receives the information provided by the sensing elements to provide relative locations of the sensing elements against the one or more reference targets. The reception device comprises processing means to build the real time VR visualization that represents at least the operator's hands against the target area of the aircraft based on the sensing elements. The VR system also comprises display means that display the real time VR visualization to the operator.

公开(公告)号：US10882597B2

公开(公告)日：2021-01-05

申请号：US15921399

申请日：2018-03-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Edouard Menard ,  Esteban Martino González ,  Fernando Iniesta Lozano

IPC: B64C1/06 ,  F41H5/04

Abstract: An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.

公开(公告)号：US20200347782A1

公开(公告)日：2020-11-05

申请号：US16814506

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: F02C6/08 ,  F02C7/047 ,  F02C7/10 ,  B64D15/04

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

公开(公告)号：US20200324912A1

公开(公告)日：2020-10-15

申请号：US16842173

申请日：2020-04-07

Applicant: Airbus Operations S.L.

Inventor： Gabrielle Josephine Christiane DE BROUWER

IPC: B64D47/04 ,  F21V14/02 ,  F21V21/15

Abstract: A dynamic runway illumination system, including a light source having an addressable light beam direction, and a control unit configured to receive aircraft attitude information and the orientation of the runway selected for takeoff or landing, obtain horizontal and vertical axes, the horizontal axis being collinear with the takeoff or landing longitudinal direction, determine the actual and the reference aircraft trajectories, obtain the actual and the reference vertical approach angles, and the actual horizontal approach angle, and actuate onto the light source to perform an angular movement in the light beam direction of an absolute value of the actual vertical approach angle minus the absolute value of the reference vertical approach angle about the vertical axis, and an angular movement of an absolute value of the actual horizontal approach angle about the horizontal axis, to vertically and horizontally align the beam of the light source towards the runway direction.

公开(公告)号：US20200320961A1

公开(公告)日：2020-10-08

申请号：US16836214

申请日：2020-03-31

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

Inventor： Matthijs PLOKKER ,  Luc Jan HORNSTRA ,  Frank NIELSEN ,  Gabrielle De Brouwer

IPC: G09G5/38 ,  B64D47/02 ,  G03B21/60

Abstract: An illumination system for illuminating outer aircraft components of an airborne vehicle, such as an aircraft, includes a light projection system configured to project visual imagery to an outer surface of the airborne vehicle, and a projection controller having a light control processor configured to control the operation of the light projection system on the basis of at least one of operational flight status of the airborne vehicle, geographical location of the airborne vehicle and configuration data of movable surfaces of the airborne vehicle or on ambient light measurement.