A hybrid design method, focused on reducing vibration while minimizing control effort, is developed. In this integrated active-passive approach, trailing edge flap controller design is combined with blade structural optimisation. An aeroelastic model is developed for a helicopter rotor with a trailing edge flap. The objective function, which includes vibratory hub loads and active flap control inputs, is minimised by an integrated optimal control/structural optimisation process. It is demonstrated that both the hub vibratory loads and active flap control effort can be reduced. The study shows that retrofitting an active flap to a baseline blade or to an optimal passive blade configuration might not be an effective design approach. The active-passive hybrid method can outperform these configurations by achieving more vibration reduction with less control effort. The hybrid design procedure can reduce the required active flap deflections by about 30-60 % in the whole flight range. An analysis and parametric study of the hybrid design of rotor blades with trailing edge flaps is conducted. The off-design condition for hybrid approaches is examined and the robustness of the hybrid design is addressed. The physical understandings of the hybrid design are explored.


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    Titel :

    Active-passive hybrid optimization of rotor blades with trailing edge flaps


    Weitere Titelangaben:

    Aktiv-Passiv Hybrid-Optimierung von Rotorblättern mit Hinterkantenklappen


    Beteiligte:
    Zhang, J. (Autor:in) / Smith, E.C. (Autor:in) / Wang, K.W. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2004


    Format / Umfang :

    12 Seiten, 19 Bilder, 7 Tabellen, 36 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch






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