公开(公告)号：US11487301B2

公开(公告)日：2022-11-01

申请号：US16714880

申请日：2019-12-16

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

Inventor： Jean-Claude Mere ,  Ramon Andreu Altava

IPC: G05D1/08 ,  B64D43/00 ,  G06N3/08 ,  G06N3/04

Abstract: A method and device for generating an optimum aircraft vertical trajectory, including a unit performing iterative processing to determine, on each iteration, a next state from a computational state, by using an estimated overall cost for next states, each estimated overall cost, which is computed by a cost computation unit, being equal to the sum of a real cost computed up to the next state under consideration by using predetermined constraints and a cost estimated up to the current state of the aircraft. The estimated cost is computed using a deterministic neural network based on performance calculations for the aircraft without using energy constraints, allowing computation of this estimated cost and the estimated overall cost to be performed rapidly. The iterative processing is repeated until the determined state is situated in proximity to the current state of the aircraft, the corresponding trajectory part forming the optimum vertical trajectory.

公开(公告)号：US11486781B2

公开(公告)日：2022-11-01

申请号：US16803595

申请日：2020-02-27

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

Inventor： Clément Chirol ,  Patricia Morgue ,  Manuel Paredes ,  Simon Dols

IPC: G01L5/24 ,  B25B23/14 ,  B23P19/06

Abstract: A device for monitoring clamping of an assembly including at least one part to be clamped, an internally threaded element and an externally threaded element engaged in an internal thread of the internally threaded element. The device includes a driver to rotate one of the elements including the internally threaded element and the externally threaded element to clamp the assembly and a first sensor to measure a screwing torque of the driver, a tool for holding fixed against rotation the other of the elements including the internally threaded element and the externally threaded element, a second sensor to measure a reaction torque of the holding tool, a mechanism for determining a third parameter chosen from a time elapsed from a given time and a screwing angle from a reference position, and a calculation system to determine pre-tension in the externally threaded element.

公开(公告)号：US11472573B2

公开(公告)日：2022-10-18

申请号：US16832114

申请日：2020-03-27

Applicant: Airbus Operations S.A.S.

Inventor： Marc Chauveau

IPC: B64F5/10 ,  B64D27/26

Abstract: A holding tool for holding the first and second side panels of a primary structure of an aircraft pylon during assembly thereof includes: a first portion configured to be removably secured to the first side panel, at least one second portion including at least one pair of first and second parts, positioned on either side of the second side panel and attracting one another by virtue of a magnetic field so as to secure the second portion to the second side panel, and at least one connection element connecting the first and second portions. Thus, during assembly of the primary structure, the second portion of the holding tool may be secured to the second side panel without the need for through-holes. The primary structure thus assembled does not comprise any through-holes in the side panels.

公开(公告)号：US11435203B2

公开(公告)日：2022-09-06

申请号：US16378840

申请日：2019-04-09

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

Inventor： Patrice Brot ,  Olivier Sapin

IPC: G01P13/02 ,  G01D3/08 ,  B64D43/02

Abstract: Method and system for merging measurements of flight parameters of an aircraft. The system is for merging measurements of flight parameters of an aircraft, linked to one another by at least one equation, and includes at least one acquisition module for acquiring at least one measurement of flight parameters, a scoring module for attributing a first validity score to the equations by checking whether the measurement or measurements of flight parameters are a solution or solutions of the equation or equations, a scoring module for attributing a second validity score to failure scenarios involving one or more acquisition modules from the first validity scores, a determination module for determining the validity of the measurements of flight parameters from the second validity scores, consolidation module for consolidating the measurements of flight parameters, a transmission module for transmitting the consolidated measurements of flight parameters to a user device.

公开(公告)号：US20220250769A1

公开(公告)日：2022-08-11

申请号：US17669011

申请日：2022-02-10

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

Inventor： George HOWELL ,  Louis Emmanuel ROMANA

IPC: B64F5/60 ,  B64D43/00 ,  B64D45/04 ,  G06N20/00

Abstract: An aircraft control system (100) including an aircraft control module (110) and a test module (120). The aircraft control module includes a memory storing a machine learning model (130) adapted, based on received live aircraft operating inputs (102a-102f), to generate live aircraft control outputs (104a-104b). The test module (120) includes a memory storing input data representing test aircraft operating inputs (102a′-102f′) and respective output data representing expected aircraft control outputs (114a, 114b) that are expected to be generated by the aircraft control module in response to an input of the respective test aircraft operating inputs (102a′-102f′). The test module (120) is adapted to write test aircraft operating inputs (102a′-102f′) to the aircraft control module, read test aircraft control outputs (104a′-104b′) of the aircraft control module (110), and remove the authority of the aircraft control module (110) to perform aircraft control.

公开(公告)号：US20220219829A1

公开(公告)日：2022-07-14

申请号：US17558213

申请日：2021-12-21

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

Inventor： Alexis Courpet ,  Jean Geliot ,  Arnaud Bourhis

IPC: B64D27/26 ,  B64D29/06 ,  B64D29/08

Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

公开(公告)号：US20220177112A1

公开(公告)日：2022-06-09

申请号：US17495449

申请日：2021-10-06

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

Inventor： Russell OLDER ,  Paul MORRELL ,  Ryan HOLLAND ,  Oliver MARKS ,  Pierre-Antoine COMBES ,  Guillaume DE ALMEIDA

IPC: B64C3/56 ,  B64C9/02

Abstract: A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

公开(公告)号：US20220172344A1

公开(公告)日：2022-06-02

申请号：US17535052

申请日：2021-11-24

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

Inventor： Nicolas Dominguez ,  François Lefebvre Albaret ,  Florent Montet ,  Jérome Fayolet

IPC: G06T7/00 ,  H04N5/225 ,  H04N5/247 ,  G06T7/40 ,  G06T7/514 ,  G06T7/70 ,  G06T7/55 ,  H04N5/232 ,  B64C39/02 ,  B64D47/02 ,  B64D47/08 ,  F21V21/30

Abstract: A flying drone for inspecting surfaces able to reflect light has a lighting device formed of two light sources each having a shape that is elongate in a longitudinal direction of each of the light sources, two first image acquisition devices, and a second image acquisition device between the two first image acquisition devices. The two light sources are respectively between the second image acquisition device and each of the first image acquisition devices. The flying drone allows effective detection of dents in surfaces by analyzing specular reflections, by the lighting device and of the first image acquisition devices, and effective detection of superficial defects on surfaces by the second image acquisition device, with the lighting device switched off.

公开(公告)号：US11312505B2

公开(公告)日：2022-04-26

申请号：US17131206

申请日：2020-12-22

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

Inventor： Jean-Marc Datas ,  Jacques Bouriquet ,  Jean-Mickael Brindeau ,  André Aquila ,  Patrick Guibert

IPC: B64F5/10 ,  B64F5/50

Abstract: To reduce the footprint of an installation for assembling a fuselage section, a support structure includes a chassis and a core mounted so that it can rotate relative to the chassis about an axis of rotation of the core. The core includes a fastener(s) for holding the longitudinal fuselage portions around the core, with a view to assembling them to form the fuselage section. The support structure includes one or more rolling elements provided on the chassis, in order to allow the movement of this support structure within the installation.

公开(公告)号：US11295717B2

公开(公告)日：2022-04-05

申请号：US16659793

申请日：2019-10-22

Applicant: Airbus Operations S.A.S.

Inventor： César Garnier

IPC: G10K11/168 ,  B32B3/12 ,  B64D33/02 ,  F02C7/045

Abstract: An acoustic absorption structure includes: a porous layer in contact with a medium through which the sound waves travel, a cellular layer including a plurality of cells, which has at least one exterior annular canal open towards the porous layer, and a reflective layer. An aircraft propulsion system having at least one such acoustic absorption structure is also described.