公开(公告)号：US20240169849A1

公开(公告)日：2024-05-23

申请号：US18501361

申请日：2023-11-03

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Mohamed-Habib ESSOUSSI ,  Didier FOURCADE ,  Olivier FALIPOU

IPC: G08G5/02 ,  G08G5/00 ,  G08G5/04

CPC classification number: G08G5/025 ,  G08G5/0021 ,  G08G5/0086 ,  G08G5/045

Abstract: The avionics computer comprises a processing unit configured to compare the distance between a first position and a second position with a predetermined distance, the first position corresponding to the position of an initial anchor point of an initial terminal segment and the second position corresponding to the position of a landing threshold point of the runway, to check whether the initial terminal segment of the virtual path crosses the threshold of the runway and, if the distance between the first position and the second position is less than the predetermined distance and if the initial terminal segment of the virtual path crosses the threshold of the runway, to define the landing threshold point as an anchor point of a terminal segment of a virtual path for a non-precision FLS approach mode, the avionics computer thus making it possible to increase availability to implement FLS mode.

公开(公告)号：US11984839B2

公开(公告)日：2024-05-14

申请号：US17713581

申请日：2022-04-05

Applicant: Airbus Operations SAS

Inventor： Jean-François Allias ,  Olivier Raspati

IPC: H02P7/343 ,  B64D27/24

CPC classification number: H02P7/343 ,  B64D27/24

Abstract: A propulsive electric motor set for aircraft includes an electrical energy source and an electric motor provided with a drive shaft on which is mounted a propeller. The electric motor includes a first set of windings linked to the electrical energy source to provide a rotational drive function for the drive shaft. The electric motor further includes a second set of windings which, when the drive shaft is driven in rotation by an electric powering of the first set of windings, provides an electric generation function configured to supply non-propulsive loads of the aircraft. Thus, the non-propulsive loads of the aircraft can be electrically powered without any overload compromising the aerodynamics of the aircraft.

公开(公告)号：US11981446B2

公开(公告)日：2024-05-14

申请号：US17878360

申请日：2022-08-01

Applicant: Airbus Operations SAS

Inventor： Umberto Gastaldi ,  Wolfgang Brochard ,  Olivier Pautis

IPC: B64D29/08 ,  B64D29/06

CPC classification number: B64D29/08 ,  B64D29/06

Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

公开(公告)号：US20240150028A1

公开(公告)日：2024-05-09

申请号：US18502248

申请日：2023-11-06

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Michael BERJOT ,  Pierre-Antoine COMBES ,  Paul-Adrien TAVEAU

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/264

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

公开(公告)号：US11975858B2

公开(公告)日：2024-05-07

申请号：US17971680

申请日：2022-10-24

Applicant: Airbus Operations SAS

Inventor： Lionel Czapla ,  Frédéric Piard

IPC: B64D29/00

CPC classification number: B64D29/00

Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.

公开(公告)号：US11975857B2

公开(公告)日：2024-05-07

申请号：US17899673

申请日：2022-08-31

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Thomas Robiglio

IPC: B64D27/40 ,  F02C7/20

CPC classification number: B64D27/40 ,  F02C7/20

Abstract: A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.

公开(公告)号：US20240133351A1

公开(公告)日：2024-04-25

申请号：US18490833

申请日：2023-10-19

Applicant: Airbus Operations SAS

Inventor： Michael BELIN ,  Lionel SILLIERES ,  Julie CAZALIS ,  Simon VANDERBAUWEDE ,  Samuel MAGNE

IPC: F02K1/76

CPC classification number: F02K1/766 ,  F02K1/763 ,  F05D2220/323 ,  F05D2260/50

Abstract: A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.

公开(公告)号：US20240125284A1

公开(公告)日：2024-04-18

申请号：US18484548

申请日：2023-10-11

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT

IPC: F02K1/32

CPC classification number: F02K1/32

Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

公开(公告)号：US20240116648A1

公开(公告)日：2024-04-11

申请号：US18363426

申请日：2023-08-01

Applicant: Airbus Operations SAS

Inventor： Anthony MERTES

IPC: B64D37/04

CPC classification number: B64D37/04

Abstract: An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.

公开(公告)号：US11952135B2

公开(公告)日：2024-04-09

申请号：US17851407

申请日：2022-06-28

Applicant: Airbus Operations SAS

Inventor： Cédric Poupon ,  Olivier Pautis ,  Jonathan Blanc

IPC: B64D27/26 ,  F16C11/06

CPC classification number: B64D27/26 ,  F16C11/0628 ,  B64D2027/262

Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.