公开(公告)号：US10332324B2

公开(公告)日：2019-06-25

申请号：US15207139

申请日：2016-07-11

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

Inventor： Sebastien Jover ,  Jean-Philippe Corbefin

IPC: G07C5/08 ,  G07C5/02 ,  G07C5/00 ,  H04L29/08

Abstract: A system, device and method for recording data in an aircraft including a memory and a network interface through which it is connected to the network. This device is configured for acquiring information from the avionics communication network, and information relative to characteristic events relative to operation of the aircraft, generating indexes corresponding to different times, recording, in a first part of the memory, indexed data corresponding to the information coming from avionics communication network, the indexed data including a set of recordings, each recording corresponding to the combination of information coming from the avionics communication network and an index corresponding to a time associated with that recording; and recording, in a second part of the memory, for several of the characteristic events, information of correspondence between the characteristic event in question and an index corresponding to a time associated with that characteristic event.

公开(公告)号：US10330221B2

公开(公告)日：2019-06-25

申请号：US15692755

申请日：2017-08-31

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

Inventor： Olivier Verseux ,  David Blain

IPC: F16L55/00 ,  F16L9/18 ,  F16L9/19 ,  B33Y80/00 ,  G01M3/00 ,  F16L59/06 ,  G01M3/04 ,  F16L59/075

Abstract: A piping system includes a first and a second inner tube assembled end to end and a hot fluid detector. For each inner tube, a first peripheral tube into which the inner tube is introduced and fixed. For each first peripheral tube, a second peripheral tube into which the first peripheral tube is introduced and fixed. A sleeve has a first section which surrounds the ends of the second two peripheral tubes facing one another and a second section which extends between the two ends up to the walls of the first two peripheral tubes. A pipe crosses the sleeve and opening out, on the one hand, into the space between the inner tubes and the first peripheral tubes and, on the other hand, in the vicinity of the hot fluid detector. A piping system of this kind is therefore thermally insulated and allows detection in the event of a leak.

公开(公告)号：US20190186676A1

公开(公告)日：2019-06-20

申请号：US16199669

申请日：2018-11-26

Applicant: Airbus Operations S.A.S.

Inventor： José Lopez

IPC: F16L59/135 ,  F16L59/18

CPC classification number: F16L59/135 ,  F16L3/1025 ,  F16L3/20 ,  F16L3/237 ,  F16L3/26 ,  F16L59/12 ,  F16L59/14 ,  F16L59/18 ,  F16L59/20 ,  F24F13/0209 ,  F24F13/0263

Abstract: A securing device includes at least one rigid ring configured to encircle the pipe, and at least one securing system, rigid and distinct from the ring, including a body which has a first contact face configured to be pressed firmly against and secured to a surface of a structure, and at least one groove in which the ring is housed, the groove being configured to allow the securing system to slide with respect to the ring in a direction of sliding along the ring, while being immobile or near-immobile relative to the ring in a plane perpendicular to the direction of sliding.

公开(公告)号：US20190162554A1

公开(公告)日：2019-05-30

申请号：US16163205

申请日：2018-10-17

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

Inventor： Jean-Claude Mere

IPC: G01C23/00 ,  G05D1/02 ,  G08G5/00

Abstract: A flight management assembly for an aircraft includes at least one flight management system and at least one display device, the flight management system configured to manage at least one flight plan of the aircraft and one long-term reference path of the aircraft. The flight management assembly additionally includes an auxiliary computer, the auxiliary computer being separate from and independent of the flight management system, the auxiliary computer linked to the flight management system and to the display device, the auxiliary computer configured to perform prediction computations to generate at least one short-term path, from at least the long-term reference path received from the flight management system and from current flight parameters of the aircraft and from piloting setpoints of the aircraft.

公开(公告)号：US10296183B1

公开(公告)日：2019-05-21

申请号：US15821429

申请日：2017-11-22

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

Inventor： Laurent Peyras ,  Michel Colombier

IPC: G06F3/048 ,  G06F3/0484 ,  G06F3/0482 ,  G05B19/418 ,  B64F5/10 ,  H04L29/08

Abstract: The disclosure herein describes an aircraft assembly tracker system including a user interface configured to display an aircraft part under assembly and overlay one or more zones on the displayed part. The user interface operates on a computing device. The zones represent different panels to be affixed to the aircraft during assembly and their shape displayed on the user interface is identical to the shape of their corresponding panel being affixed to the physical aircraft part. The aircraft assembly tracker system monitors the assembly progress of each zone and automatically alerts aircraft assembly workers when the zone is ready for closure.

公开(公告)号：US20190136905A1

公开(公告)日：2019-05-09

申请号：US16175288

申请日：2018-10-30

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

Inventor： José Lopez

IPC: F16C7/06

CPC classification number: F16C7/06 ,  F16C2226/74 ,  F16C2226/80

Abstract: A length-adjustable control rod includes a first part including a cylindrical peripheral face which has a succession of peripheral grooves separated from one another and positioned in transverse planes. A second part includes a barrel configured to at least partially receive the first part and which has several cutouts configured to divide up the barrel into several cylinder sectors and at least one inner rib, protruding from the inner lateral face of the barrel, which has a section configured to be housed in one of the peripheral grooves.

公开(公告)号：US10276050B2

公开(公告)日：2019-04-30

申请号：US15594242

申请日：2017-05-12

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

Inventor： Andreas Reinke ,  Sebastian Kauertz

IPC: B64D45/00 ,  G08G5/00

Abstract: A method to identify the proximity of a wake turbulence and to generate a report relative to that proximity. A method implemented by an aircraft comprising a processor makes it possible to identify the proximity of a wake turbulence and to generate a report relative to that proximity. The method includes a data acquisition step during which the processor retrieves and records the data relative to each generating aircraft present around the aircraft. In a position estimation step, the processor estimates the position of the wake turbulences generated by each generating aircraft. In a proximity step, the processor determines if the aircraft is close to at least one of the wake turbulences. In a generation step, the processor generates a report containing the data relative to each wake turbulence. The method makes it possible to identify the proximity of a wake turbulence in the vicinity of the aircraft and to automatically record the data relative to that wake turbulence.

公开(公告)号：US20190061908A1

公开(公告)日：2019-02-28

申请号：US16108575

申请日：2018-08-22

Applicant: Airbus Operations S.A.S. ,  AIRBUS SAS

Inventor： Daniel Kierbel ,  Mathias Farouz-Fouquet ,  Laurent Malard

IPC: B64C3/26 ,  B64C3/28 ,  B64C21/10 ,  B29C45/14 ,  B21D26/021 ,  B21D53/92

Abstract: A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

公开(公告)号：US10207288B2

公开(公告)日：2019-02-19

申请号：US15282055

申请日：2016-09-30

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

Inventor： Christophe Menard ,  Nicolas Blond

IPC: B43M11/02 ,  B05C17/02 ,  B05C17/035 ,  B05C1/02 ,  B05C17/03 ,  B05D1/28 ,  B64D11/06

Abstract: A tool for applying a corrosion-protection substance to a rail for securing seats in an aircraft. The tool includes a component of elongate overall shape, with a base configured to slide along the rail, and a rollers support connected to the base. The tool also has an axle incorporated in the rollers support, which extends transversally with respect to the longitudinal direction of the component on each side of the rollers support, and rollers for applying the substance mounted on the transverse axle, one on each side of the component. The tool allows the substance to be applied effectively to the flange parts of the rail that is to be protected.

公开(公告)号：US20190043374A1

公开(公告)日：2019-02-07

申请号：US15668038

申请日：2017-08-03

Applicant: Airbus Operations S.A.S.

Inventor： Jean-Claude Mere

IPC: G08G5/04 ,  G08G5/00

Abstract: In operating an aircraft, a situation is displayed at each instant representing a spatio-temporal overview of risk zones around the aircraft. Each direction in space around the aircraft is scanned, and a simulated displacement of the aircraft in each direction is analyzed so as to identify potential zones of interference with the aircraft's path. Anticipated movement of risk zones over a planned time duration of a flight is determined. Such anticipated movement is correlated with an anticipation position of the aircraft over the planned time duration. Accordingly, risk zones initially appearing as a potential hazard may be determined to be safe by the time the aircraft reaches them, and vice versa. Such information is presented to pilots at an outset of the flight and continuously updated throughout the flight, enabling accurate and safe evaluation and strategy decisions.