Active vibration reduction in the modern helicopters is influenced by various properties of composite rotor blades. Current work is focused on understanding the influence of elastic coupling which is a key property of the composite blades, on active vibration control in the helicopters. Governing equations of composite rotor blades with surface bounded piezoceramic actuators are obtained using Hamilton's principle. The equations are then solved for dynamic response using finite element discretization in the spatial and time domains. A time domain unsteady aerodynamic theory with free wake model is used to obtain the airloads. A newly developed single crystal piezoceramic material is introduced as an actuator material in order to exploit its relatively high shear actuation authority. Seven rotor blades with different elastic couplings representing stiffness properties similar to stiff-inplane rotor blade are used to investigate the hub vibration characteristics. The rotor blades are modeled as a box beam with actuator layers bounded on the outer surface of top and bottom of the box section. Numerical results indicate that the vibration reduction can be obtained considerably for all the combinations of composite rotor blades.


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    Title :

    Helicopter vibration reduction using active twist control of composite rotor blades


    Additional title:

    Schwingungsreduzierung bei Hubschraubern


    Contributors:


    Publication date :

    2008


    Size :

    10 Seiten, 27 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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