公开(公告)号：US20190263535A1

公开(公告)日：2019-08-29

申请号：US16319104

申请日：2017-06-29

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

Inventor： Valentin GARCIA MARTINEZ ,  Richard MURILLO ,  Sebastien DUPOUY ,  Antoine BREGAND ,  Irene BORILLO LLORCA ,  Romain COËMET

IPC: B64D45/02 ,  B64F5/60 ,  B64F5/40 ,  G07C5/08 ,  G06Q10/00

Abstract: A method and device for inspecting the structural damage on the skin of an aircraft after a lightning strike, the skin has marks derived from the lightning strike, wherein the marks represent a Visual Damage (VD) and a Structural Damage (SD). The method includes for every mark: measuring the area of paint that has been removed by the lightning strike, and comparing the measured area with an area threshold value, wherein the threshold value is related to the Structural Damage (SD) of every mark.

公开(公告)号：US10322793B2

公开(公告)日：2019-06-18

申请号：US15295099

申请日：2016-10-17

Applicant: Airbus Operations S.L.

Inventor： Fernando Pereira Mosqueira ,  Jesús Javier Vázquez Castro

IPC: B64C3/30 ,  B64C3/26 ,  B64C3/28 ,  B64C3/14

Abstract: A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.

公开(公告)号：US20190161209A1

公开(公告)日：2019-05-30

申请号：US16201613

申请日：2018-11-27

Applicant: Airbus Operations, S.L.

Inventor： Carlos CASADO-MONTERO ,  Javier LINDE AYLLON

IPC: B64F1/10 ,  B64F1/22 ,  B64C25/08

Abstract: An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.

公开(公告)号：US10179253B2

公开(公告)日：2019-01-15

申请号：US14725618

申请日：2015-05-29

Applicant: Airbus Operations, S.L.

Inventor： Jose Manuel Santos Gomez ,  Ramón Ramos

IPC: A62C3/00 ,  B29C70/44 ,  A62C35/02 ,  A62C5/00 ,  A62C99/00 ,  B29C35/02

Abstract: A system for making an autoclave inert such that flame propagation is prevented in the event of spontaneous internal combustion, which thus prevents damaging the actual system or equipment, tools and parts, for which it essentially has sodium azide capsules which produce a chemical reaction when they reach an activation temperature, releasing nitrogen, making the chamber inert, venting equipment to prevent damage due to overpressure inside the chamber when the capsules have come into action and released the gas, a main cooling circuit and an additional cooling circuit for the capsules, all of this automatically controlled and managed by a control device.

公开(公告)号：US20190002082A1

公开(公告)日：2019-01-03

申请号：US16021568

申请日：2018-06-28

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Alfonso GONZÁLEZ GOZALBO ,  Eugenio PIÑEYROA DE LA FUENTE

IPC: B64C3/48 ,  B64C3/50

Abstract: A method for manufacturing a modular lifting surface from a standard lifting surface, the modular lifting surface includes a central support structure including an upper skin, a lower skin and at least a first spar. The method includes providing the upper skin and the lower skin which are suitable for any of various sizes of a modular lifting surface for the standard lifting surface, wherein the upper skin and lower skin correspond to a standard upper skin and the lower skin conforms to a standard lower skin.

公开(公告)号：US10164351B2

公开(公告)日：2018-12-25

申请号：US15651587

申请日：2017-07-17

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Adolfo Ávila Gutiérrez

IPC: H01R4/28 ,  H01R4/48 ,  H01R4/70 ,  H01R13/50 ,  H01R13/52 ,  H01R13/627 ,  F16B4/00 ,  B64C1/00

Abstract: A bonding clip shell for protecting a bonding point between a bonding lead and a bonding strap. The bonding clip shell comprises a first part which comprises a first end, a second end, and an inner surface, the inner surface comprising a protrusion and a first seal, and a second part which comprises a first end, a second end and an inner surface, the inner surface comprising a cavity and a second seal. In the first ends of the first and second parts respectively, the first and second parts are joined through a hinge area. The cavity is configured to house and fix the protrusion providing a click system. When the protrusion is housed in the cavity, the first and second seals are configured to hermitically seal the inner surfaces of the bonding clip shell.

公开(公告)号：US10026340B2

公开(公告)日：2018-07-17

申请号：US14475001

申请日：2014-09-02

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Adrián Salazar Ruiz ,  Óscar Macías Martín-Crespo ,  Jesús López Coracho ,  Abraham Pérez Nuevo ,  Nuria Martínez Martín

IPC: B32B43/00 ,  B64F5/00 ,  B65D65/22 ,  G09F3/02 ,  G09F3/00 ,  B64F5/10

Abstract: A method of detection and removal of auxiliary material suitable for the manufacturing of an aircraft element includes providing an auxiliary material having at least one detection label, scanning the element with a label detector suitable to detect the detection label once the element has been manufactured, detecting the auxiliary material by means of a warning signal emitted by the label detector and removing the auxiliary material from the element. An auxiliary material suitable for the manufacturing of an aircraft element includes a detection label.

公开(公告)号：US20180173840A1

公开(公告)日：2018-06-21

申请号：US15840620

申请日：2017-12-13

Applicant: Airbus Operations, S.L.

Inventor： Nuno Vinha ,  David Vallespin Fontcuberta ,  Valentín De Pablo Fouce ,  Eusebio Valero

IPC: G06F17/50

CPC classification number: G06F17/5095 ,  G06F17/5009 ,  G06F17/5018 ,  G06F17/5086 ,  G06F2217/16 ,  Y02T90/50

Abstract: A computer-aided method suitable for assisting in the design of an object zone such as a CROR engine of an aircraft subjected to high vorticity and/or low static pressure fields when moving inside a flow field by providing suitable seed points for constructing vortex core lines in a fluid data model of the environment of said object zone and a system based in said method. The method steps are: a) Obtaining a dataset of candidate seeds containing all the cells or points satisfying a condition of the pressure gradient in the direction of the flow or a condition of the drag friction coefficient at the solid boundaries; b) Updating the previous dataset of candidate seeds with all the cells or points satisfying the equation not used for obtaining the dataset in step a).

公开(公告)号：US20180170520A1

公开(公告)日：2018-06-21

申请号：US15843203

申请日：2017-12-15

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Edouard MENARD ,  Esteban MARTINO GONZÁLEZ ,  Fernando INIESTA LOZANO

IPC: B64C5/06 ,  B64C1/12

Abstract: An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

公开(公告)号：US09964044B2

公开(公告)日：2018-05-08

申请号：US15156619

申请日：2016-05-17

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Alberto Juarez Becerril ,  Mario Marcos Garcia

IPC: F02N11/04 ,  H02P9/04 ,  F02C7/26 ,  F01D19/00 ,  F02C7/268 ,  B64D41/00 ,  F02N11/08 ,  B64D31/00 ,  B64F1/34 ,  G05D1/00

CPC classification number: F02C7/26 ,  B64D41/00 ,  F01D19/00 ,  F02C7/268 ,  F02N11/0803 ,  F02N11/087 ,  F02N2011/0874 ,  F05D2220/50 ,  F05D2220/76 ,  Y02T50/671

Abstract: An auxiliary power unit (APU) starting system for an aircraft comprises an APU comprising a starter motor and a generator, a DC power network, an AC power network, an electric connection line, and a control unit for controlling the APU starting and generating phase. The APU starting system additionally comprises switches for alternatively connecting through the electric connection line the DC power network with the APU starter motor, and the AC power network with the APU generator, wherein the control unit is further configured to operate the switches to connect the DC power network with the APU starter motor during the APU starting phase, and the AC power network with the APU generator during the APU starting phase.