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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    Title :

    Rotorcraft aeroelastic stability using robust analysis



    Published in:

    Publication date :

    2013




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    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



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    Rotorcraft aeroelastic stability

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    Aeroelastic Analysis for Rotorcraft

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