The invention relates to a leading-edge flap control method. A leading-edge flap control switch is arranged in an aircraft cockpit, and the leading-edge flap control switch is connected with a flight control computer which is connected with a hydraulic steering gear; besides, the flight control computer generates digital control commands according to the position of the leading-edge flap control switch and the deflection rules for leading-edge flap control, and a servo controller arranged in the flight control computer processes the digital control commands and position feedback signals of the hydraulic steering gear through servo amplification and signal conversion, and generates servo commands for the hydraulic steering gear, in order to control the hydraulic steering gear to push rudder surface deflection of leading-edge flaps; manual control or automatic control of the leading-edge flaps can be quickly realized, the leading-edge flap control method is suitable for the control of the leading-edge flaps of fixed-wing aircrafts, not only meets the demands for increasing lifting force during an aircraft takeoff stage and an aircraft landing stage as well as improving the stallout characteristics at large angle of attack, but also reduces the operating load of pilots and reduces retracting and launching transients of the leading-edge flaps, so that the flying quality is effectively improved.


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    Titel :

    Leading-edge flap control method


    Beteiligte:
    YANG JIEHONG (Autor:in) / XIE HUICI (Autor:in) / LIU XIN (Autor:in) / CHEN LIN (Autor:in) / ZHANG KUN (Autor:in) / CUI YANYONG (Autor:in) / XIANG GUOHUI (Autor:in) / WAN MING (Autor:in) / ZHANG YUBAI (Autor:in) / TU LIANGHUI (Autor:in)

    Erscheinungsdatum :

    02.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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