Abstract This paper discusses the impact of different models of aerodynamic loads on rotorcraft-pilot couplings stability using a robust stability analysis approach. The aeroelasticity of the main rotor of a helicopter is formulated using aerodynamic models based on the blade element/momentum theory and boundary element method coupled to a finite element model of the blade. The resulting linearized models are used to determine stability limits according to the generalized Nyquist criterion, associated with the accelerations of the pilot’s seat caused by the involuntary action of the pilot on the control inceptors. The resulting stability curves are discussed considering examples of involuntary pilot transfer functions from the literature.


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    Titel :

    Rotorcraft aeroelastic stability using robust analysis


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2013




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    50.03 Methoden und Techniken der Ingenieurwissenschaften / 50.03 Methoden und Techniken der Ingenieurwissenschaften, Methoden und Techniken der Ingenieurwissenschaften / 55.50 Luftfahrzeugtechnik / 55.50 Luftfahrzeugtechnik, Luftfahrzeugtechnik
    DDC:    629.105



    Rotorcraft aeroelastic stability using robust analysis

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    Rotorcraft aeroelastic stability using robust analysis

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    Rotorcraft aeroelastic stability

    Ormiston, Robert A. / Warmbrodt, William G. / Hodges, Dewey H. et al. | NTRS | 1988


    Rotorcraft Aeroelastic Stability

    R. A. Ormiston / W. G. Warmbrodt / D. H. Hodges et al. | NTIS | 1988


    Aeroelastic Analysis for Rotorcraft

    Johnson, W. | NTRS | 1982