公开(公告)号：US20190283890A1

公开(公告)日：2019-09-19

申请号：US16352332

申请日：2019-03-13

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

Inventor： Olivier Pautis ,  Jérôme Colmagro ,  Jonathan Blanc

IPC: B64D27/26

Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.

公开(公告)号：US10399663B2

公开(公告)日：2019-09-03

申请号：US15255639

申请日：2016-09-02

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

Inventor： Denis Soula ,  Matthieu Plet ,  Javier Maqueda Lahoz

IPC: B64C3/18 ,  B64C1/06 ,  B64C1/26 ,  B64C3/22

Abstract: A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.

公开(公告)号：US10392096B2

公开(公告)日：2019-08-27

申请号：US15150674

申请日：2016-05-10

Applicant: Airbus Operations S.A.S.

Inventor： Bernard Guering

IPC: B64C1/14 ,  B64D11/02 ,  E06B3/48 ,  E06B3/80 ,  B64D11/00 ,  B64D45/00

Abstract: An access device enables controlled or secure communication between different areas of an enclosure, and in the example illustrated in the present application of an aircraft, while providing reduced size. The access device includes a folding door which, when in folded position, allows at least one of said openings to be closed and, when in deployed position, forms a security vestibule with at least one movable shutter allowing said opening created by the deployment of said folding door to be closed. By superimposing the main components of the security vestibule that said components allow to close, the device frees up the adjoining cabin space when the security vestibule is not in use.

公开(公告)号：US10380903B2

公开(公告)日：2019-08-13

申请号：US15445506

申请日：2017-02-28

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

Inventor： Jean-luc Robin ,  Camille Caruhel ,  Sylvain Deplanche

IPC: G08G5/04 ,  G08G5/00 ,  G05D1/10

Abstract: Collision avoidance method and device for an aircraft formation relative to an intrusive aircraft. The device manages a collision avoidance for an aircraft formation, relative to an aircraft external to the aircraft formation, the aircraft formation comprising a lead aircraft and at least one following aircraft, the device comprising a formation flight management unit with which all the aircraft of the aircraft formation are equipped and configured to manage the formation flight thereof, and management and control assemblies for determining and applying a coordinated avoidance maneuver intended for all the aircraft of the aircraft formation, this coordinated avoidance maneuver being determined so as to make it possible to avoid the collision with the intrusive aircraft while maintaining the formation flight.

公开(公告)号：US20190226400A1

公开(公告)日：2019-07-25

申请号：US16253548

申请日：2019-01-22

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

Inventor： Jean Geliot ,  Adeline Soulie

IPC: F02C6/04 ,  B64D27/26 ,  B64D29/02 ,  B64D33/08 ,  F02C7/18 ,  F01D25/24 ,  F01D25/12

Abstract: An aircraft pylon including a heat exchange device having a heat exchanger which includes a first circuit portion ducting a flow of hot air tapped off an engine of the aircraft and a second circuit portion ducting a flow of cold air, the first and second circuit portions of the heat exchanger being coaxial, separated by at least one partition forming an exchange surface, and positioned, at least partially, in the primary structure of the pylon.

公开(公告)号：US10356009B2

公开(公告)日：2019-07-16

申请号：US15714625

申请日：2017-09-25

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

Inventor： Adrien Gauffriau ,  Benoît Triquet

IPC: G06F15/80 ,  H04L29/08 ,  H04L12/721 ,  H04L12/741 ,  H04L12/931

Abstract: Multiple-core processor to be connected, by way of communication ports, to a deterministic switched Ethernet network using virtual links to which items of equipment are connected, the processor including clusters each including cores, wherein at least one cluster of the processor implements a switch function that makes it possible to interconnect the items of equipment in the network. At least one cluster of the processor implements an end system function providing functions of sending and receiving data in the network, and at least one cluster of the processor implements an application.

公开(公告)号：US20190210714A1

公开(公告)日：2019-07-11

申请号：US16239730

申请日：2019-01-04

Applicant: Airbus Operations S.A.S.

Inventor： Mathias Farouz-Fouquet

IPC: B64C21/10

CPC classification number: B64C3/141 ,  B64C21/00 ,  B64C23/06 ,  B64C2003/148 ,  B64C2230/26 ,  B64D29/00

Abstract: An aerodynamic element is provided with at least one set of protruding elements, each of the protruding elements is produced in the form of an elongate and profiled rib projecting from a surface of the aerodynamic element. The protruding elements are arranged at the surface of the aerodynamic element, one beside the other, being oriented substantially parallel to one another so that each of them generates a vortex, the set of vortices thus generated making it possible to reduce crossflow instability.

公开(公告)号：US20190202577A1

公开(公告)日：2019-07-04

申请号：US16238059

申请日：2019-01-02

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

Inventor： Freddy LE PROVOST ,  Alexandre DUCHEVET ,  Estelle DELPECH ,  Vincent SOUFFRANT ,  Benoît PAPAÏX ,  Nicolas CHATRENET ,  Yannick DELERIS

IPC: B64D45/00 ,  B64D47/02 ,  G08B7/06 ,  B64D43/00

Abstract: A system (1) including an identification unit (2) for identifying at least one actuation element to be actuated to implement a current control from a check-list, a signaling unit (3) for visually highlighting the identified actuation element, a detection unit (4) for detecting a position of a hand of a pilot, a checking unit (5) for checking whether the detected position of the hand of the pilot is consistent with the position of the identified and highlighted actuation element for the actuation thereof, an alert unit (6) for alerting the pilot to a risk of incorrect actuation, in case of absence of consistency between the detected position of the hand of the pilot and the position of the actuation element, and a recovery unit (15) for identifying, in case of incorrect actuation, at least one suggest correct actuation element.

公开(公告)号：US10336458B2

公开(公告)日：2019-07-02

申请号：US14575332

申请日：2014-12-18

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

Inventor： Julien Guillemaut ,  Sébastien Alby ,  Jérôme Colmagro ,  Pascal Pome ,  Jonathan Blanc ,  Thomas Robiglio ,  Tobias Sjostrom

IPC: B64D27/26 ,  B64D27/20

Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.

公开(公告)号：US20190196508A1

公开(公告)日：2019-06-27

申请号：US16209298

申请日：2018-12-04

Applicant: Airbus Operations S.A.S.

Inventor： Matthieu Barba ,  Maxime Semat ,  Florent Lanterna

IPC: G05D1/06 ,  G05D1/00 ,  G01P5/02

CPC classification number: G05D1/0638 ,  B64C13/503 ,  G01P5/02 ,  G05D1/0077 ,  G05D1/0607

Abstract: A piloting assistance system for an aircraft includes a measuring module for measuring a vertical manoeuvre of the aircraft, a computational module for computing a first load factor from the measured vertical manoeuvre and from a setpoint vertical manoeuvre, a measuring module for measuring an inclination angle, a pitch rate and a pitch acceleration, a protection module including a computational submodule configured to compute a second load factor and a comparison submodule in order to compare the first and the second load factor in order to determine an applicable load factor equal to the minimum between the first and the second load factor, a computational module configured to compute elevator control from the applicable load factor and a sending module configured to send the elevator control to the automatic pilot.