公开(公告)号：US11084567B2

公开(公告)日：2021-08-10

申请号：US16209353

申请日：2018-12-04

Applicant: Airbus Operations SAS

Inventor： Mathias Farouz-Fouquet

IPC: B64C3/48 ,  B64D27/02 ,  B64C39/00 ,  B64C5/12

Abstract: An airplane comprising a fuselage, two wings, a rear tail unit comprising a horizontal tail provided with two tail ends, and at least two engines arranged on the fuselage on either side of a vertical plane of symmetry of the airplane, the airplane having a longitudinal axis, the engines being mounted so as to be able to be displaced, at least in flight, on the fuselage, substantially parallel to the longitudinal axis, and the tail ends being mounted so as to be able to be pivoted, at least in flight, relative to the horizontal tail, the airplane thus having a configuration that changes in flight.

公开(公告)号：US11081014B2

公开(公告)日：2021-08-03

申请号：US16840604

申请日：2020-04-06

Applicant: Airbus Operations SAS

Inventor： Alexis Frenot

IPC: G08G5/02 ,  B64D43/00 ,  G01C21/00 ,  G01C21/20

Abstract: A landing assistance system includes a module for acquiring environment and current flight parameters of the aircraft, a module for generating flight and navigation symbology to be displayed on the display device at least from current flight parameters, a module for generating a land topography of terrain overflown by the aircraft, a transmission module configured to transmit a signal to the display device that represents the flight and navigation symbology and the synthetic representation, the symbology generating module including a sub-module for displaying a mock-up at a predetermined non-zero positive pitch angle relative to a median line of the display zone. The system allows a landing to occur in good conditions by virtue of the enlargement of the lower part of the display zone.

公开(公告)号：US11066992B2

公开(公告)日：2021-07-20

申请号：US16394339

申请日：2019-04-25

Applicant: Airbus Operations SAS

Inventor： Jean Geliot ,  Adeline Soulie

IPC: B64D33/02 ,  F02C6/08 ,  F02C9/18 ,  F02C7/141

Abstract: A propulsion assembly for an aircraft comprising a pylon and a bypass turbomachine having a fan duct in which an air flow flows. The turbomachine further comprises an air intake system with a cold bleed air device for bleeding some of the air flow from the fan duct, the device comprising a sliding scoop comprising an upstream face that is open to allow the air to pass and a lower side that has an air outlet opening connected to an exchanger. The scoop is able to slide between an open position in which the scoop extends at least in part into the fan duct and in which part of the air flow in the fan duct rushes into the scoop via the upstream face thereof, and a closed position in which the scoop does not extend into the fan duct and has its upper side closing off the cutout.

公开(公告)号：US20210207557A1

公开(公告)日：2021-07-08

申请号：US17140717

申请日：2021-01-04

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT ,  Julien LE FANIC

IPC: F02K1/72 ,  F02K1/76

Abstract: A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.

公开(公告)号：US20210207556A1

公开(公告)日：2021-07-08

申请号：US17140707

申请日：2021-01-04

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Benjamin THUBERT ,  Julien LE FANIC

IPC: F02K1/72 ,  F02K1/76

Abstract: A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

公开(公告)号：US11053026B2

公开(公告)日：2021-07-06

申请号：US16251865

申请日：2019-01-18

Applicant: Airbus Operations SAS

Inventor： Jean-luc Martres

IPC: B64F5/60 ,  G01B5/06 ,  G01B5/00 ,  F16B5/02

Abstract: A device and an inspection method for inspecting screw and nut assemblies in an aircraft, comprising a mechanical tool and a digital human-machine interface. The mechanical tool comprises a housing comprising a bearing surface defining a reference plane, a support beam mounted to be translationally mobile inside the housing, a linear encoder configured to measure, in use, a distance between the reference plane and a bottom face of the mobile support beam. The digital human-machine interface comprises a central unit, a display screen, an application and a database in which are stored validity ranges or standardized distances relating to types of assembly, the application and the database being loaded and operational in the central unit.

公开(公告)号：US20210188445A1

公开(公告)日：2021-06-24

申请号：US17123454

申请日：2020-12-16

Applicant: Airbus Operations SAS

Inventor： Laurent FEUILLERAC ,  Patrick SALGUES ,  Vincent AURIAC

IPC: B64D13/00 ,  B64C1/08 ,  B64C1/18 ,  B64C1/06 ,  B64F5/10

Abstract: An aircraft duct assembly comprising at least two ducts extending along a general direction of rectilinear extent, each duct being an electrical, hydraulic or aeraulic duct connected to a duct support. The duct support comprises a first slideway element configured to cooperate with a second slideway element to form a slideway in the general direction of extent of the ducts. The duct assembly can thus be inserted, after mounting, by translation along the direction of the slideway into an aircraft fuselage portion. The mounting of the duct assembly and installation thereof in a fuselage are simplified, and the duct assembly is more reliable.

公开(公告)号：US20210183256A1

公开(公告)日：2021-06-17

申请号：US17117571

申请日：2020-12-10

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Elodie SABY ,  Stéphanie BOUCHET ,  Philippe CASTAIGNS ,  Vincent SIBELLE ,  Pascal ARNASSAN ,  Laetitia MARQUIE

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

Abstract: An aircraft landing assistance system includes a processing unit configured to determine whether there is total failure of the aircraft's engines and, if yes, to determine a set of airports at which the aircraft could land from its current position, taking into account its current energy and current configuration. For each airport, the system determines a runway on which the aircraft could land and at least one possible landing direction of the aircraft on this runway and determines a reference point ahead of each runway, corresponding to a deployment point for the landing gear and a point of changing from a smooth configuration of the aircraft to a non-smooth configuration, to allow the aircraft to land on the runway. The system also commands the display, on an aircraft navigation screen, of a depiction of each of the runways and the reference points associated with these runways.

公开(公告)号：US11028801B2

公开(公告)日：2021-06-08

申请号：US16201265

申请日：2018-11-27

Applicant: Airbus Operations SAS

Inventor： Christophe Bourdeau ,  Quentin Vaucouloux ,  Romain Cusset

IPC: F02K1/72

Abstract: A grating for the formation of a reverse flow of a turbofan engine and comprising fins of a first type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the first type, fins of a second type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the second type. In this grating, each fin of one of the two types is inserted between two fins of the other type moving from forward to aft and the cord of the fins of the second type is smaller than the cord of the fins of the first type.

公开(公告)号：US11027718B2

公开(公告)日：2021-06-08

申请号：US16440807

申请日：2019-06-13

Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS SAS

Inventor： Kurt Brüggemann ,  Brice Cheray ,  Louis Emmanuel Romana

IPC: B60T17/22 ,  B64C25/42 ,  B64C25/44 ,  B60T8/17 ,  B60T8/171 ,  B60T8/172 ,  B60T8/1761

Abstract: An apparatus for reducing brake wear having a brake de-selection function for selectively disabling at least one brake on a vehicle; and a controller. The controller is configured to receive torque information which relates to torque reacted by a brake on the vehicle during a braking event and wheel speed information which relates to a speed of a wheel associated with the brake during the braking event; calculate an energy input into the brake during the braking event, based on the received torque information and the received wheel speed information; determine whether the calculated energy input meets at least one predefined energy input criterion; and activate the brake de-selection function if the calculated energy input meets the at least one predefined energy input criterion.