A rotorcraft analysis is conducted to assess tilt-rotor stability and conversion loads for the XV-15 rotor with metal blades within its specified test envelope. A 38-DOF flutter analysis based on the code by Johnson (1988) is developed to simulate a wind-tunnel test in which the rotor torque is constant and thereby study stability. The same analytical model provides the simulated loads including hub loads, blade loads, and oscillatory pitch-link loads with attention given to the nonuniform inflow through the proprotor in the presence of the wing. Tilt-rotor stability during the cruise mode is found to be sensitive to coupling effects in the control system stiffness, and a stability problem is identified in the XV-15 Advanced Technology Blades. The present analysis demonstrates that the tilt-rotor is stable within the specified test envelope of the NASA 40 x 80-ft wind tunnel.


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    Title :

    Analytical aeroelastic stability considerations and conversion loads for an XV-15 tilt-rotor in a wind tunnel simulation


    Contributors:

    Conference:

    AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference ; 1992 ; Dallas, TX, United States


    Publication date :

    1992-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Wind Tunnel Testing of a Eurofar Tilt Rotor Aeroelastic Stability Model

    Jessop, D. A. C. / Juggins, P. T. W. / Associazione Italiana di Aeronautica ed Astronautica et al. | British Library Conference Proceedings | 1993