Recently, the parallel cascade reduced-order modeling approach has been successfully used for the flutter prediction of a two-degree-of-freedom wing section. However, this approach has been less successful when applied to reveal other important aeroelastic phenomena, such as the transonic aeroservoelastic behaviors of a three-dimensional wing with a trailing-edge control surface. Because of the complexity introduced by the forced control-surface deflection, effects of oscillating shock waves, and aerodynamic viscosity, the stability of the dynamic linear parts of the parallel cascade reduced-order model cannot be guaranteed. In this paper, a novel, stable representation of the parallel cascade reduced-order model is explored in which the linear part is identified by using a predictor-based subspace scheme. To demonstrate the performance of the present parallel cascade reduced-order model in modeling the aeroservoelastic behaviors of a three-dimensional wing with a trailing-edge control surface, the Benchmark Active Control Technology wing is used as an illustrative example. The numerical results demonstrate that the parallel cascade reduced-order models are capable of modeling open/closed-loop aeroservoelastic behaviors. Moreover, the effects of the aerodynamic nonlinearity on the dynamic behaviors of the aeroservoelastic systems are investigated always based on the proposed reduced-order model.


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    Title :

    Open/Closed-Loop Aeroservoelastic Predictions via Nonlinear, Reduced-Order Aerodynamic Models



    Published in:

    Publication date :

    2015




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040




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