A geometrically exact shell element is developed within the finite-element, multibody dynamics-based Rotorcraft Comprehensive Analysis System. The shell element accommodates transverse shear deformation as well as arbitrarily large displacements and rotations. The shell element is developed using an approach that allows for compatibility with other structural elements in the Rotorcraft Comprehensive Analysis System. It is validated by comparing its predictions with benchmark problems. The two-dimensional shell and one-dimensional beam finite-element analyses are compared for three typical blade configurations of varying slenderness ratio: a swept-tip blade, a blade with discontinuous chordwise elastic axis and center-of-gravity locations, and a blade with a flex beam. The purpose is to quantify the differences between two-dimensional-shell one-dimensional-beam finite elements for modeling rotor blades. There is good agreement between the one- and two-dimensional analyses in predicting the natural frequencies of straight blades with a slenderness ratio of greater than 12.5. However, there are up to 16.5% differences in frequency predictions for a slenderness ratio of 17.5 or less and a tip sweep angle of 30 deg or higher. The differences increase with decreasing slenderness ratio and increasing tip sweep angle. For a blade with a discontinuous center-of-gravity offset, frequencies predicted using the two- and one-dimensional analyses show up to 12.5% difference and increase with the center-of-gravity offset. For a blade with discontinuous elastic axis offset, the frequencies predicted using the two analyses have good agreement. The differences are observed when both approaches calculate the structural loads (bending moments) and deformations of a blade with an elastic axis offset.


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    Titel :

    Assessment of Beam and Shell Elements for Modeling Rotorcraft Blades


    Beteiligte:
    Kang, Hao (Autor:in) / Chang, Chongseok (Autor:in) / Saberi, Hossein (Autor:in) / Ormiston, Robert A. (Autor:in)

    Erschienen in:

    Journal of Aircraft ; 51 , 2 ; 520-531


    Erscheinungsdatum :

    2014-03-11


    Format / Umfang :

    12 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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