An actuator-link assembly includes an actuator having first and second opposing ends in order to drive a control surface of an aircraft and a link coupled to the actuator. The actuator has a rod portion having a tip end, located at first end of the actuator, said tip end pivotably attach to a control surface of an aircraft. The link includes a pair of linear portions, each having first and second opposing ends, wherein the linear portions are disposed alongside each other; a coupling portion connecting the first ends of linear portions, a fulcrum shaft attachment portion protruding from the coupling portion configured to pivotably attach to a fulcrum shaft for rotatably supporting the control surface; and an actuator attachment portion configured to pivotably attach to the second end of the actuator. A material constituting the linear portions and the coupling portion contains fiber reinforced plastic.


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    Title :

    Actuator-link assembly for aircraft control surface


    Contributors:

    Publication date :

    2015-08-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16H Getriebe , GEARING



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