Off-axis coupling of a helicopter exhibits the opposite sign in flight tests as compared to simulations. lt has been shown that this effect may be attributable to the bending of the wake during a pitching maneuver, which introduces a fore-to-aft gradient in induced flow that can reverse the predicted sign of roll coupling. lt has been shown that this result can also be obtained with momentum and vortex theory. In the present work, a generalized mode for wake curvature in hover is developed using the exact relation derived from vortex tube theory. This model is coupled with a flop model to investigate the influence on dynamic coupling.


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    Title :

    Helicopter rotor dynamic inflow modeling for maneuvering flight


    Additional title:

    Ein dynamisches Hubschrauberrotor-Einlaufströmungsmodell für Schwebeflugzustände


    Contributors:

    Published in:

    Publication date :

    2001


    Size :

    11 Seiten, 12 Bilder, 3 Tabellen, 34 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Helicopter Rotor Dynamic Inflow Modeling for Maneuvering Flight

    Krothapalli, K.R.K. | Online Contents | 2001



    ROTOR DYNAMIC WAKE DISTORTION MODEL FOR HELICOPTER MANEUVERING FLIGHT

    Zhao, J. / Prasad, J. V. R. / Peters, D. A. et al. | British Library Conference Proceedings | 2002


    Validation of a Rotor Dynamic Wake Distortion Model for Helicopter Maneuvering Flight Simulation

    Zhao, J. / Prasad, J. V. R. / Peters, D. A. et al. | British Library Conference Proceedings | 2004


    Modeling of rotor dynamic wake distortion during maneuvering flight

    Zhao, Jinggen / Prasad, J. / Peters, David | AIAA | 2001