The aeroelastic response and stability of isotropic and composite rotor blades are investigated using a large deflection-type beam theory. The finite element equations of motion for beams undergoing arbitrary large displacements and rotations, but small strains, are obtained from Hamilton's principle. The sectional elastic constants of a composite box beam including warping deformations are determined from the refined cross-sectional finite element method. The analysis is performed for a soft-in-plane hingeless rotor in free flight propulsive trim. The nonlinear periodic blade steady response is obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim. After the coupled trim response is computed, the aeroelastic response is calculated through a time-marching solution procedure under small perturbations assumption, and then the stability analysis is performed by using a moving block analysis. Numerical results of rotating natural frequencies, blade response, and aeroelastic stability are presented. The results of the full finite element analysis using the large deflection-type beam theory are quite different from those of a previously published modal analysis using the moderate deflection-type beam theory.


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    Title :

    Aeroelastic analysis of a hingeless rotor blade in forward flight


    Additional title:

    Aeroelastische Analyse eines scharnierlosen Hubschrauberrotors im Vorwärtsflug


    Contributors:
    Jeon, S.M. (author) / Lee, I. (author)

    Published in:

    AIAA Journal ; 38 , 5 ; 843-850


    Publication date :

    2000


    Size :

    8 Seiten, 12 Bilder, 4 Tabellen, 40 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English