A method and apparatus for controlling an angular parameter between a base member (202) and a control surface (204) of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface (204) with respect to an inertial frame (215) of the aircraft using a rate sensor (210). A residual angular rate ( ¸ res ) that is a difference between a commanded angular rate and the estimate of the angular rate ( ¸ RVDT ) of the control surface (204) is determined. The residual angular rate ( ¸ res ) is used to control the angular parameter of the control surface (204) or the angular parameter of the base member (202).


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    Title :

    Flutter control actuator


    Additional title:

    Verfahren und Vorrichtung zum Vermeiden eines Flatterns von Stellflächen an Flugzeugen
    Actionneur de commande flutter


    Contributors:

    Publication date :

    2015-05-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge



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