A methodology to develop piezostack-based actuator for trailing edge flap on a full-scale helicopter rotor blade is presented. By a systematic down-selection approach through the experimental validation on piezostack characteristics, one among numerous candidates was chosen for current study, which has higher stiffness as well as good strain/block force capability. The prototype actuator was designed and fabricated using two pieces of selected piezostack incorporated with a double-lever amplification mechanism that extends a level-fulcrum amplification concept. To validate the feasibility of the designed actuator, the prototype actuator was tested in vacuum chamber that simulates the centrifugal force environment. It was shown that the actuator operated with no major degradation in performance up to 600 g of centrifugal loading. The present actuator has a capability of oscillating the trailing edge flap to the required deflection/frequency to actively control rotor vibration in the rotating environment. Then, a further design refinement was considered to reduce the drawbacks, which finally results in an improved actuator with peak actuation force of 80 lbs at 38 mils stroke.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Development and validation of a refined piezostack-actuated trailing edge flap actuator for a helicopter rotor


    Beteiligte:
    Lee, Taeoh (Autor:in) / Chopra, I. (Autor:in)


    Erscheinungsdatum :

    1999


    Format / Umfang :

    15 Seiten, 28 Quellen




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch






    Actuation of trailing edge flap in a wing model using piezostack device

    Chandra, Ramesh / Chopra, Inderjit | AIAA | 1997


    Helicopter rotor blade based on seamless trailing edge flap mechanism

    YANG WEIDONG / ZHOU JINLONG / DONG LINGHUA | Europäisches Patentamt | 2020

    Freier Zugriff

    HELICOPTER AEROFOIL WITH TRAILING EDGE FLAP

    CAVE ANDREW / STACEY SIMON | Europäisches Patentamt | 2024

    Freier Zugriff