公开(公告)号：US20240227751A1

公开(公告)日：2024-07-11

申请号：US18397913

申请日：2023-12-27

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Ashley BIDMEAD ,  Mark JOHNSON

IPC: B60T7/14 ,  B64D45/00 ,  G05G1/02 ,  G05G5/05 ,  G05G9/00

CPC classification number: B60T7/14 ,  B64D45/00 ,  G05G1/02 ,  G05G5/05 ,  G05G9/00 ,  G05G2505/00

Abstract: A control device for an aircraft is disclosed including a push-button switch that is configured to be held in a depressed position by a pilot during taxiing of the aircraft. The push-button switch is configured to return automatically to a released position if it is not held in the depressed position by the pilot. The control device is configured to output a command for braking to a braking system of the aircraft, if the push-button switch moves to the released position during taxiing of the aircraft and does not return to the depressed position within a set time. The button may be provided on a tiller. A method of detecting on-board pilot incapacitation during an aircraft taxi phase is also disclosed.

公开(公告)号：US20240246663A1

公开(公告)日：2024-07-25

申请号：US18415079

申请日：2024-01-17

Applicant: Airbus Operations Limited

Inventor： Ashley BIDMEAD ,  Mark JOHNSON

IPC: B64C25/50 ,  B60T8/17 ,  B60T8/1755 ,  B60T17/22 ,  B64D45/00

CPC classification number: B64C25/50 ,  B60T8/1703 ,  B60T8/17551 ,  B60T17/22 ,  B64D45/00 ,  B60T2260/02

Abstract: An aircraft includes a ground maneuver control system that automatically steers a nose landing gear wheel to compensate for asymmetrical braking of the wheels of the aircraft resulting from a failure on one side in comparison to the other. A control system detects such a failure in order to be able to effect such automatic steering. The system may be retrofitted by the installation of software on an existing aircraft, having a braking and steering computer system with a pre-existing steering control functional block and a pre-existing braking control functional block.

公开(公告)号：US20230234699A1

公开(公告)日：2023-07-27

申请号：US18100316

申请日：2023-01-23

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Fernando IZQUIERDO CIVERA ,  Alex Robert PIDDOCK ,  Mark JOHNSON

IPC: B64C19/02 ,  B64C13/16

CPC classification number: B64C19/02 ,  B64C13/16

Abstract: An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

公开(公告)号：US20220266992A1

公开(公告)日：2022-08-25

申请号：US17650558

申请日：2022-02-10

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Alexander HAYES ,  Ashley BIDMEAD ,  Thierry STORME ,  Robert COOMBE ,  Mark JOHNSON ,  Andrew HEBBORN

IPC: B64C25/46 ,  B60T8/17 ,  B60T8/172

Abstract: An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.

公开(公告)号：US20250153845A1

公开(公告)日：2025-05-15

申请号：US18938054

申请日：2024-11-05

Applicant: Airbus Operations Limited

Inventor： Sean KERR ,  Mark JOHNSON

IPC: B64C25/26

Abstract: A landing gear controller that: determines whether a predetermined criterion is met; and causes a power supply system of an aircraft to supply power to an actuation system of the aircraft to cause a component of a landing gear system of the aircraft to move from a first position to a second position selectively according to: a first predetermined supplied-power profile, when the landing gear controller determines that the predetermined criterion is not met, and a second predetermined supplied-power profile, according to which a maximum power supplied by the power supply system to the actuation system is greater than a maximum power supplied by the power supply system to the actuation system according to the first predetermined supplied-power profile, to move the component from the first position to the second position more quickly, when the landing gear controller determines that the predetermined criterion is met.

公开(公告)号：US20250108911A1

公开(公告)日：2025-04-03

申请号：US18889012

申请日：2024-09-18

Applicant: Airbus Operations Limited

Inventor： Sean KERR ,  Mark JOHNSON

IPC: B64C13/16 ,  B64C25/50

Abstract: A computer-implemented method that includes receiving information indicative of an aircraft steering angle of an aircraft, comparing the received information against a threshold above which degradation of a tire of a landing gear of the aircraft is expected to occur and causing an action to be performed based on a result of the comparison. Also an aircraft system.

公开(公告)号：US20250002141A1

公开(公告)日：2025-01-02

申请号：US18754424

申请日：2024-06-26

Applicant: Airbus Operations Limited

Inventor： Mark JOHNSON ,  Jason SHORTO ,  Peter DAVIS

IPC: B64C25/30 ,  B64C25/22 ,  B64C25/24

Abstract: An aircraft has a landing gear that can be extended and retracted and a landing gear control system that is configured so that it can cause extension/retraction of the landing gear of the aircraft in response to pilot operation of a landing gear lever. The control system is also configured such that in the scenario of pilot incapacitation, it can cause extension/retraction of the landing gear of the aircraft in response to an automated command for landing gear extension/retraction. A kit of parts including a relaying unit can be used for converting an existing aircraft to one that has this functionality. There is also a method of automatically extending/retracting landing gear, for example in the event of pilot incapacitation when performing single-pilot operation of the aircraft.

公开(公告)号：US20240062665A1

公开(公告)日：2024-02-22

申请号：US18450223

申请日：2023-08-15

Applicant: Airbus Operations Limited

Inventor： Ashley BIDMEAD ,  Mark JOHNSON

IPC: G08G5/06 ,  B64C25/50 ,  G08G5/00 ,  B64C25/32

CPC classification number: G08G5/065 ,  B64C25/50 ,  G08G5/0047 ,  B64C25/405

Abstract: An aircraft is disclosed including a ground manoeuvre control unit for automatically controlling ground manoeuvres. The aircraft has control mechanisms such as a rudder, nose wheel steering, spoilers, wheel brakes and the like for controlling motion of the aircraft. The control unit is configured to receive lateral input demands concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit passes on the input demands as output demands to the relevant control mechanisms of the aircraft with, if so required, a modification which prioritises one of the lateral input demand and longitudinal input demand based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion.