This paper outlines the development of a mathematical model that is expected to be useful for rotorcraft flying qualities research. A computer model is presented that can be applied to a range of different rotorcraft configurations. The algorithm computes vehicle trim and a linear state-space model of the aircraft. The trim algorithm uses non linear optimization theory to solve the nonlinear algebraic trim equations. The linear aircraft equations consist of an airframe model and a flight control system dynamic model. The airframe model includes coupled rotor and fuselage rigid body dynamics and aerodynamics. The aerodynamic model for the rotors utilizes blade element theory and a three state dynamic inflow model. Aerodynamics of the fuselage and fuselage empennages are included. The linear state-space description for the flight control system is developed using standard block diagram data.


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    Titel :

    Model for Rotorcraft Flying Qualities Studies


    Beteiligte:
    M. Mittal (Autor:in) / M. F. Costello (Autor:in)

    Erscheinungsdatum :

    1993


    Format / Umfang :

    16 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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