Disclosed is a landing gear controller for an aircraft. The landing gear controller is configured to: determine whether a predetermined criterion is met; and cause a power supply system of the 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. Also disclosed is a landing gear extension and retraction system.


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    Title :

    LANDING GEAR CONTROLLER


    Additional title:

    FAHRWERKSTEUERUNG
    DISPOSITIF DE COMMANDE DE TRAIN D'ATTERRISSAGE


    Contributors:
    KERR SEAN (author) / JOHNSON MARK (author)

    Publication date :

    2025-05-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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