A comprehensive study on unsteady effects of oscillating Gurney flaps, or microflaps, has been conducted. Twodimensional unsteady airloads for lift, moment, and drag due to an oscillating microflap were computed using a compressible Reynolds-averaged Navier-Stokes flow solver. The computational fluid dynamics results were generated with an overset-mesh approach that captures oscillatory microflap motion. Three microflap configurations were examined to determine the type most suitable in terms of actuation efficiency and practical implementation. Furthermore, a reduced-order model for the unsteady microflaps was developed based on computational fluid dynamics simulations, using the rational function approximation approach. The resulting rational function approximation model is a state-space time-domain aerodynamic model that accounts for unsteadiness, compressibility, and time-varying freestream effect. The agreement between the reduced-order model and direct computational fluid dynamics calculations was found to be excellent for a wide range of flow conditions examined. The approximate model is suitable for incorporation in a comprehensive code, from which the potential of microflaps for active control of vibrations in rotors can be determined. Open-loop control studies indicated that the microflap produces substantial vibration reduction (80 % reduction in vertical shear), whereas closed-loop control using combined harmonic inputs consisting of a sum of four harmonics (2-5/rev) reduced the vibration objective by 92 %, on a hingeless rotor configuration resembling the Messerschmitt-Bölkow-Blohm BO-105. These results confirmed the control authority and effectiveness of the microflap for vibration reduction in rotorcraft.


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    Titel :

    Computational study of microflaps with application to vibration reduction in helicopter rotors


    Weitere Titelangaben:

    Numerische Studie über Mikroklappen mit Anwendung auf die Schwingungsdämpfung bei Hubschrauberrotoren


    Beteiligte:
    Liu, Li (Autor:in) / Padthe, Ashwani K. (Autor:in) / Friedmann, Peretz P. (Autor:in)

    Erschienen in:

    AIAA Journal ; 49 , 7 ; 1450-1465


    Erscheinungsdatum :

    2011


    Format / Umfang :

    16 Seiten, 25 Bilder, 2 Tabellen, 51 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





    Computational Study of Microflaps with Application to Vibration Reduction in Helicopter Rotors

    Liu, Li / Padthe, Ashwani K. / Friedmann, Peretz P. | AIAA | 2011



    A comprehensive study of active microflaps for vibration reduction in rotorcraft

    Padthe, Ashwani K. / Liu, Li / Friedmann, Peretz P. | Tema Archiv | 2010


    A Computational Study of Microflaps with Application to Vibration Reduction in Helicopter Rotors

    Friedmann, P. / Padthe, A. / Liu, L. | British Library Conference Proceedings | 2009