A nonlinear time history simulation of an all movable control surface with varying amounts of free play was performed. The 'Flexible Aicraft Modeling Using State Space', (FAMUSS), computer code was used to generate state models at selected velocities. Two different state models are used during the simulation. One state model is used whenever the stabilator rotation angle is inside the free play zone, and another state model is used whenever the stabilator is outside the free play zone. The state models are switched during the simulation as a function of stabilator position. The nonlinear time simulation predicted that the free play will reduce the flutter velocity and flutter frequency from the no free play case. The predicted results for a generic fighter aircraft stabilator matches wind tunnel results. Finally, a physical explanation is presented as to why the free play effects results in a lower flutter speed than the free play case. It is also shown that the linear p-k-flutter analysis of both the no free play and free play (no pitch spring) case can be used to predict the velocity and frequency where the maximum response will occur.


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    Title :

    A physical explanation of free play effects on the flutter response of an all movable control surface


    Additional title:

    Physikalische Erklärung für den Einfluß des freien Spiels auf das Flattern einer vollbeweglichen Steuerfläche


    Contributors:
    Pitt, D.M. (author)


    Publication date :

    1995


    Size :

    9 Seiten, 11 Bilder, 9 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    A Physical Explanation of Free Play Effects on the Flutter Response of an All Movable Control Surface

    Pitt, D. / American Institute of Aeronautics and Astronautics| ASME| ASCE | British Library Conference Proceedings | 1995




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    Hu, P. / Zhao, H. / Xue, L. et al. | British Library Conference Proceedings | 2011