The invention disclose an automatic yawing rectification pedal and spring mechanism which comprises a left pedal, a right pedal, a servo mechanism, a rocker arm and a spring, wherein the left pedal or the right pedal is connected with a link rod by the spring; the link rod is driven by the servo mechanism; a connecting rod is arranged between the left pedal and the right pedal; the two ends of the connecting rod are connected with control steel cables; the end parts of the two control steel cables are connected with a rudder by the rocker arm; the servo mechanism drives the link rod to move; the compression amount of the spring is changed by the movement of the link rod; and the compressed spring drives the pedals to move, so as to drive the rudder to deviate to produce a yawing moment, and the yawing influence of propeller slip flow on aircraft heading is eliminated automatically. The servo mechanism is mounted nearby the pedals and drives the spring to be compressed through the link rod 3, and the compressed spring drives the pedals to move, so that yawing caused by the propeller slip flow is rectified automatically.


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    Titel :

    Automatic yawing rectification pedal and spring mechanism


    Beteiligte:
    YANG BO (Autor:in) / LI TAIAN (Autor:in) / LIU ZHUO (Autor:in) / ZHOU XIAOYONG (Autor:in) / LIANG BIN (Autor:in) / LI ZIQI (Autor:in) / LYU JING (Autor:in) / ZHANG DAWEI (Autor:in)

    Erscheinungsdatum :

    16.09.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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