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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    Title :

    Landing gear controller


    Contributors:
    SEAN KERR (author) / MARK JOHNSON (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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