Tuning the finite element model using measured data to minimize the model uncertainties is a challenging task in the area of structural dynamics. A test validated finite element model can provide a reliable flutter analysis to define the flutter placard speed to which the aircraft can be flown prior to flight flutter testing. Minimizing the difference between numerical and experimental results is a type of optimization problem. Through the use of the National Aeronautics and Space Administration Dryden Flight Research Center's (Edwards, California) multidisciplinary design, analysis, and optimization tool to optimize the objective function and constraints; the mass properties, the natural frequencies, and the mode shapes are matched to the target data, and the mass matrix orthogonality is retained. The approach in this study has been applied to minimize the model uncertainties for the structural dynamic model of the aerostructures test wing, which was designed, built, and tested at the National Aeronautics and Space Administration Dryden Flight Research Center. A 25 percent change in flutter speed has been shown after reducing the uncertainties.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Reduced Uncertainties in the Flutter Analysis of the Aerostructures Test Wing


    Beteiligte:
    Pak, Chan-Gi (Autor:in) / Lung, Shun Fat (Autor:in)

    Erscheinungsdatum :

    2011-01-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




    REDUCED UNCERTAINTIES IN THE ROBUST FLUTTER ANALYSIS OF THE AEROSTRUCTURES TEST WING

    Pak, C.-G. / Lung, S.-F. / International Council of the Aeronautical Sciences; Optimage Ltd | British Library Conference Proceedings | 2010



    Aerostructures Test Wing

    Lind, RIck / Voracek, David F. / Doyle, Tim et al. | NTRS | 2003