An aeroelastic stability analysis has been formulated for hingeless rotors with composite blades in the hovering flight condition. The structural dynamic model is based on a mixed formulation of geometrically exact nonlinear beam theory, which can accurately model composite blades, including the effects of large deflections, transverse shear deformation, free warping, and initial curvature and twist. The aerodynamic includes three-dimensional unsteady wake effects by means of the finite-state generalized dynamic wake theory. The present approach integrates these two theories, resulting in an elegant and computationally efficient formulation for rotor aeroelastic analysis. The formulation is symbolically explicit and concise as opposed to conventional aeroelastic approaches and other nonlinear finite element methods. This method is very computationally efficient due to its very sparse coefficient matrices, allowing a high-speed numerical solution of practical problems with relatively low memory requirement. Numerical results are correlated with available experimental data.


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    Title :

    Aeroelastic stability of composite rotor blades in hover


    Additional title:

    Aeroelastische Stabilität von Verbund-Rotorschaufeln während des Schwebeflugs


    Contributors:
    Shang, X. (author) / Hodges, D.H. (author)


    Publication date :

    1995


    Size :

    9 Seiten, 7 Bilder, 1 Tabelle, 29 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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