A new aeroelastic formulation for the advanced geometry blades, involving variable sweep, droop, pretwist and planform, is presented. The blade is modeled as a series of arbitrarily-oriented elastic segments with each segment divided into finite elements. Interelement compatibility relations governing non-Eulerian moderte rotations of the finite elements are also presented. Fuselage dynamic interaction with the advanced geometry blades is included in the formulation. The nonlinear partial differential equations of motion are discretized in space and time using Hamilton's principle. Selective results are presented in hover and forward flight. Results indicate that sweep, and droop in particular, can have a strong influence on both the rotor aeroelastic stability and the rotorcraft aeromechanical stability. Droop can be considerably stabilizing. Sweep increases the blade torsional loads, but is not detrimental to flap and lag vibratory loads.


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    Title :

    Aeromechanical stability of rotorcraft with advanced geometry blades


    Additional title:

    Die aerodynamische Stabilität der Rotorkraft mit verbesserter Geometrie der Rotorblätter


    Contributors:
    Bir, G.S. (author) / Chopra, I. (author)


    Publication date :

    1993


    Size :

    25 Seiten, 13 Bilder, 1 Tabelle, 13 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English







    General Rotorcraft Aeromechanical Stability Program (GRASP): Theory manual

    Hodges, Dewey H. / Hopkins, A. Stewart / Kunz, Donald L. et al. | NTRS | 1990


    General Rotorcraft Aeromechanical Stability Program (GRASP): Theory Manual

    D. H. Hodges / A. S. Hopkins / D. L. Kunz et al. | NTIS | 1990