The aerodynamics of a helicopter main rotor blade significantly contribute to the structural dynamics of the blade. In particular, aerodynamics provide a very strong damping force in the flap direction. Further complicating the structural dynamics of a helicopter blade are the large centrifugal forces that greatly stiffen the blade. Any complete health monitoring system for rotor blades must incorporate both of these effects. In this paper, a modal-based damage detection algorithm is developed and analytically validated. Previous work in this area has yielded an algorithm to simultaneously detect mass and stiffness changes in a rotating structure. This paper extends that analysis to a state-space approach that is capable of detecting changes in damping. For completeness, the aerodynamic forces on a hovering rotor blade are considered and the appropriate damping matrix is derived. The damping matrix is used to complete a finite element model of an S-76 rotor blade. This model is intentionally perturbed to obtain 'damaged' modal test data. This is used to analytically test the validity of the eigenstructure methodology with reasonable success.


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    Titel :

    Effects of aerodynamic damping on damage detection in helicopter main rotor blades


    Beteiligte:
    Kiddy, J. (Autor:in) / Pines, D. (Autor:in)


    Erscheinungsdatum :

    1999


    Format / Umfang :

    9 Seiten, 13 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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