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    METHODS AND BRAKE SYSTEMS TO REDUCE BRAKE WEAR DURING AIRCRAFT TAXIING
    77.
    发明公开
    METHODS AND BRAKE SYSTEMS TO REDUCE BRAKE WEAR DURING AIRCRAFT TAXIING 审中-公开

    公开(公告)号：EP4015321A1

    公开(公告)日：2022-06-22

    申请号：EP21194231.3

    申请日：2021-09-01

    申请人： The Boeing Company

    发明人： MILLER, TRENT DARYL

    IPC分类号： B60T8/17 ,  B60T17/22

    摘要： Methods for reducing brake wear during aircraft taxiing are disclosed. As one example, a method comprises determining a sequence to apply brakes of a given set of landing gear during a brake event, wherein the determining includes selecting a warmer brake of the brakes to initially apply at a start of the brake event, and selecting a cooler brake of the brakes to subsequently apply when the warmer brake is released during the brake event. The method further comprises applying the warmer brake and the cooler brake in the determined sequence during the brake event. In another example, an aircraft brake system comprises brakes and a controller that is programmed to, during taxiing, apply a warmer subset of the brakes before applying a cooler subset of the brakes during a brake event.

    HEALTH MONITORING SYSTEMS AND METHODS FOR SERVO VALVES
    78.
    发明公开
    HEALTH MONITORING SYSTEMS AND METHODS FOR SERVO VALVES 审中-公开

    公开(公告)号：EP4008593A1

    公开(公告)日：2022-06-08

    申请号：EP21211102.5

    申请日：2021-11-29

    申请人： Goodrich Corporation

    发明人： GEORGIN, Marc

    IPC分类号： B60T8/17 ,  B60T8/32 ,  B60T17/22 ,  B64C25/42

    摘要： A system (200) for performing frequency response health monitoring of a servo valve (252) prior to flight of an aircraft (100) may comprise: the servo valve (252); and a brake controller (208) in electrical communication with the servo valve, the brake controller configured to: determine the brake controller is powering up, supply a variable current to the servo valve to perform the frequency response health monitoring to the servo valve in response to determining the brake controller is powering up, and determine a health status of the servo valve based on the frequency response health monitoring.

    AIRCRAFT LANDING GEAR LONGITUDINAL FORCE CONTROL
    79.
    发明公开
    AIRCRAFT LANDING GEAR LONGITUDINAL FORCE CONTROL 审中-公开

    公开(公告)号：EP4001104A1

    公开(公告)日：2022-05-25

    申请号：EP21212320.2

    申请日：2013-11-15

    申请人： Airbus Operations Limited ,  Airbus Opérations SAS

    发明人： GAMA-VALDEZ, Miguel Angel ,  ROMANA, Louis-Emmanuel ,  DAMIANI, Andrea

    IPC分类号： B64C25/40 ,  B64C25/46 ,  B60T8/17

    摘要： An aircraft landing gear longitudinal force control system for an aircraft having landing gears with braking and/or driving wheel(s). The system includes an error-based force controller having feedback for minimising any error between the demanded force and the actual force achieved by the force control system. The feedback may be derived from force sensors on the landing gear for direct measurement of the landing gear longitudinal force. The force control system may include an aircraft level landing gear total force controller and/or a landing gear level force controller for each actuated landing gear.