In an effort to expand the helicopter flight envelope, this analytical study proposes the concept of using high frequency blade pitch actuation to alleviate blade stall at high speed and/or high thrust flight conditions. The availability of high-frequency blade-mounted actuators has made this concept realizable. This study is carried out using the University of Maryland Advanced Rotorcraft Code (or UMARC), which employs state-of-the-art structural and aerodynamic modelings. The salient features of this code include the application of the finite element methods in both space and time domains, and the incorporation of an advanced unsteady aerodynamic and nonuniform inflow models. Preliminary results indicate that two-per-rev blade pitch control can reduce retreating blade stall for a rotor operating at high speed and high thrust flight condition. Current efforts concentrate on developing an automatic stall suppression system which employs a combination of higher harmonic blade pitch schedule.


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    Titel :

    Active Control of Helicopter Blade Stall


    Beteiligte:

    Kongress:

    AIAA Dynamics Specialists Conference ; 1996 ; Salt Lake City, UT, United States


    Erscheinungsdatum :

    01.01.1996


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Active control of helicopter blade stall

    Nguyen, Khanh | AIAA | 1996



    Active Control of Helicopter Blade Stall

    Nguyen, K. | Online Contents | 1998


    HELICOPTER ROTOR BLADE STALL DETECTOR

    L VOV NIKOLAJ LEONIDOVICH / KHABAROV STANISLAV SERGEEVICH / NOSOV ANDREJ ANATOL EVICH et al. | Europäisches Patentamt | 2015

    Freier Zugriff