A nonlinear flutter analysis is performed to study the limit-cycle-oscillation characteristics of an F-35 wind-tunnel model with horizontal-tail free-play effects using a direct simulation method. The result of this study is first validated with the wind-tunnel data. Then, a set of free-play design charts is generated to investigate the limit-cycle-oscillation-occurrence domain at various free-play angles and hinge moments of the horizontal tail. It is found that, as long as the horizontal tail is unloaded, the limit-cycle oscillation is inevitable even with a very small free-play angle. Furthermore, the free-play angle cannot be the only significant parameter involved in the free-play criteria. Therefore, it is suggested that an improved military specification for free-play limits of all-movable control surfaces be established. This effort will make a substantial impact on the control-surface design that may lead to a paradigm shift in the design criteria of aircraft structure.


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    Title :

    Nonlinear Flutter Analysis for the Scaled F-35 with Horizontal-Tail Free Play


    Contributors:
    Chen, P. C. (author) / Ritz, Erich (author) / Lindsley, Ned (author)

    Published in:

    Journal of Aircraft ; 51 , 3 ; 883-889


    Publication date :

    2014-05-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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



    High-fidelity Modeling and Simulation of Flutter/LCO for All-movable Horizontal Tail with Free-play

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