A landing gear controller 33 for an aircraft configured to determine whether a predetermined criterion is met; and cause a power supply system 32 of the aircraft to supply power to an actuation system of the aircraft to cause a component of a landing gear system 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 more quickly, when the landing gear controller determines that the predetermined criterion is met. The system may comprise a main power supply and an auxiliary power supply and utilise the main and auxiliary power supplies to provide power in the second supplied power-profile and utilise only the main power supply in the first power-supply profile. There is also disclosed is a landing gear extension and retraction system 30 and a corresponding method.


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    Titel :

    Landing gear controller


    Beteiligte:
    SEAN KERR (Autor:in) / MARK JOHNSON (Autor:in)

    Erscheinungsdatum :

    14.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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