公开(公告)号：US20220281590A1

公开(公告)日：2022-09-08

申请号：US17688643

申请日：2022-03-07

Applicant: Airbus Operations Limited

Inventor： Alexander HAYES ,  Ashley BIDMEAD ,  Andrew HEBBORN

IPC: B64C25/46 ,  B64C25/42 ,  B60T8/17

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

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：US20240239480A1

公开(公告)日：2024-07-18

申请号：US18539390

申请日：2023-12-14

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Alexander HAYES ,  Ashley BIDMEAD

IPC: B64C25/44 ,  B60T7/12 ,  B60T13/14 ,  B64C25/60

CPC classification number: B64C25/44 ,  B60T7/12 ,  B60T13/148 ,  B64C25/60 ,  B64C29/0008

Abstract: A VTOL aircraft (100) including a wheel braking system and a hydraulically coupled shock absorber (5) and brake piston (7). The shock absorber (5) carries the weight of the aircraft (100) when a wheel (1) connected to the shock absorber (5) is in contact with a ground surface. A hydraulic pressure within the shock absorber (5) is proportional to the weight of the aircraft (100) carried by the shock absorber (5). The shock absorber (5) and brake piston (7) are hydraulically coupled such that, when the pressure within the shock absorber (5) exceeds a threshold pressure, the pressure within the shock absorber (5) actuates the brake piston (7) to apply a braking torque to the wheel (1) of the VTOL aircraft (100).

公开(公告)号：US20230101767A1

公开(公告)日：2023-03-30

申请号：US17956697

申请日：2022-09-29

Applicant: Airbus Operations Limited

Inventor： Alexander HAYES ,  Yasser IBRAHIM ,  Marica PALITTA ,  Romain SIEGEL

IPC: B64C25/44 ,  B60T8/32 ,  B60T8/34

Abstract: An aircraft hydraulic braking system having at least one hydraulic accumulator and a brake actuator. The at least one hydraulic accumulator is the sole source of pressurised hydraulic fluid in the aircraft hydraulic braking system for operating the brake actuator and thereby apply a braking force to a wheel on an aircraft.

公开(公告)号：US20220017237A1

公开(公告)日：2022-01-20

申请号：US17375660

申请日：2021-07-14

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Alexander HAYES

IPC: B64F5/60 ,  B64C25/44

Abstract: A method of testing an aircraft landing gear is disclosed including: a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal; b) receiving the test signal via one of the tachometer output lines; c) issuing a braking command in response to the receipt of the test signal, wherein the braking command is issued via the braking command line which is associated with the one of the tachometer output lines; and d) monitoring a response of the first or second braking system to the braking command to test for a cross-connection between the first and second braking systems. The landing gear includes first and second wheels; a first braking system having a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel.

公开(公告)号：US20240140596A1

公开(公告)日：2024-05-02

申请号：US18542307

申请日：2023-12-15

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Alexander HAYES ,  Ashley BIDMEAD ,  Andrew HEBBORN

IPC: B64C25/46 ,  B60T8/17 ,  B64C25/42

CPC classification number: B64C25/46 ,  B60T8/1703 ,  B64C25/426

Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

公开(公告)号：US20230126930A1

公开(公告)日：2023-04-27

申请号：US17769167

申请日：2020-10-12

Applicant: Airbus Operations Limited

Inventor： Ashley BIDMEAD ,  Alexander HAYES

IPC: F15B21/00 ,  B64C25/42 ,  F15B21/02

Abstract: A method of removing hydraulic fluid from an aircraft hydraulic system is disclosed including a hydraulically actuated mechanism that is actuated by an electrohydraulic servo valve, a hydraulic fluid port through which hydraulic fluid can escape, and a hydraulic fuse with a closed state and an open state between the electrohydraulic servo valve and the hydraulic fluid port. The hydraulic fluid port is opened, and then the activation of the electrohydraulic servo valve is controlled to force hydraulic fluid to escape from the hydraulic system via the hydraulic fluid port, the control being so that the hydraulic fuse does not enter and remain in the closed state.