A control system 120, for an aircraft, detects failure of part of the aircraft braking system that, without other action being taken, would lead to differential braking being applied in response to a command for non-differential braking, and in response automatically steers a nose landing gear 112 to compensate for the yawing moment caused by the asymmetrical braking forces. Preferably, the amount of automatic steering is proportional to the level of braking, and the nose landing gear is subject to a maximum angular deflection from its neutral position depending on aircraft speed. The maximum angular deflection may be different values above and below a threshold speed. Preferably, the function of the control system is provided by software 132 or a computer program which may be installed to convert an existing aircraft to cause an interaction between its steering control module 134 and its braking control module 136 to provide the steering compensation.


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    Titel :

    System for controlling aircraft ground manoeuvres


    Beteiligte:
    ASHLEY BIDMEAD (Autor:in) / MARK JOHNSON (Autor:in)

    Erscheinungsdatum :

    2024-07-31


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen



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