Active control of helicopter vibrations, with actuators in the airframe structure, is appealing in terms of simplicity, air-worthiness, and effectiveness. The actuator Iocations of current active control systems an centrally Iocated in the cabin or near the main rotor. A new actuator placement methodology is proposed and explored in this research. The approach uses an optimizaion process to distribute a set of actuators at optimal locations throughout the airframe. A reduced-order airframe dynamic model is utilized for the design methodology synthesis and system analysis. Oscillatory Ioads at the main rotor hub and at the horizontal tail surface excite the airframe model. Actuation loads are integrated with the airframe dynamic model. A hybrid optimization methodology is formulated to simultaneously determine optimal actuator placement and control actions. The optimization process couples an optimal control formulation with a Simulated Annealing optimization routine. An analytical study is performed comparing optimally distributed actuator configurations to a representative state-of-the-art centralized actuator configuration. lt is shown that actuators in the airframe can more effectively control some of the dominant airframe modes, rather than actuators centralized near the main rotor support assembly. When compared to a representative state-of-the-art centralized control configuration, the distributed actuator configuration can achieve significantly greater vibration reduction with less control effort. One of die case studies shows that the centralized actuator configuration reduces vibration by 49 % (below 0.07 g); however, the optimally distributed actuator configuration reduces vibration by 90 % (below 0.03 g) und requires 50 % less control effort. The proposed design methodology that simultaneously determines actuator placement und the associated control action is extremely beneficial to reduce vibration und control effort.


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    Titel :

    An optimal actuator placement methodology for active control of helicopter airframe vibrations


    Weitere Titelangaben:

    Eine optimale Aktor-Positionierungs-Methodologie zur aktiven Schwingungsdämpfung von Hubschrauber-Rumpfstrukturen


    Beteiligte:
    Heverly, D.E. II (Autor:in) / Wang, K.W. (Autor:in) / Smith, E.C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2001


    Format / Umfang :

    11 Seiten, 16 Bilder, 5 Tabellen, 24 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





    OPTIMAL ACTUATOR PLACEMENT AND ACTIVE STRUCTURE DESIGN FOR CONTROL OF HELICOPTER AIRFRAME VIBRATIONS

    Heverly, D. E. / Wang, K. / Smith, E. et al. | British Library Conference Proceedings | 2002


    A distributed actuator approach for active control of helicopter airframe vibrations

    Heverly, II, David / Smith, Edward / Wang, K. | AIAA | 1999


    A Distributed Actuator Approach for Active Control of Helicopter Airframe Vibrations

    Heverly, D. / Smith, E. / Wang, K. | British Library Conference Proceedings | 1999


    Helicopter airframe

    FINK AXEL / STEINDL CHRISTOPH | Europäisches Patentamt | 2018

    Freier Zugriff