This paper describes an aeroelastic simulation of a fully elastic hingeless helicopter rotor incorporating a partial span trailing edge flap. Aerodynamic loads are provided by a new, two-dimensional, compressible flow unsteady aerodynamic model developed for an airfoil/flap combination and unsteady freestream. Aerodynamic loads are approximated in the frequency domain as rational functions of the Laplace variable using a least squares fit to oscillatory response data. Transformation to the time domain yields a state space model for the unsteady aerodynamic loads. Frequency domain loads are obtained using a two dimensional doublet-lattice analysis. Vibration control studies using the actively controlled flap are presented, with comparisons to results obtained using quasisteady aerodynamics.


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    Title :

    Application of a new compressible time domain aerodynamic model to vibration reduction in helicopters using an actively controlled flap


    Additional title:

    Anwendung eines neuen zeitabhängigen aerodynamischen Modells zur Schwingungsreduktion von Hubschrauberrotorblättern unter Berücksichtigung von aktiv gesteuerten Klappen


    Contributors:

    Published in:

    Publication date :

    2001


    Size :

    14 Seiten, 16 Bilder, 6 Tabellen, 36 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English