Helicopter Rotor Blade Vibration Control on the Basis of Active/Passive Piezoelectric Damping Approach

In the presented article a comparative analysis of efficiency of the helicopter rotor blades vibrations suppression by active (controlled) and passive (shunted by electric circuit) piezoelectric patches was performed. For obtaining the information about influence of the external load circuit parameters to behavior of kinematically excited actuator PZT patch the harmonic analysis in the frameworks of 1D electro-elasticity for R, L, C and combined RLC type of a load in a longwave approximation is performed. For PZT-5H plate working in d31-mode the dependence of oscillations energy harvesting and change of actuator's elastic properties on the patch's geometrical and material parameters were founded. It is shown that for reasonable values of the load capacitance, inductance and resistance the effective suppression of oscillations energy is marked at frequencies greater than 1 kHz only. A flexible structure with surface-bonded PZT patch actuated by PD controller is modelled using Euler-Bernulli beam theory. Emphasis in this study is given to the effect of actuator size and location on the observability, controllability, and stability of the control system. The hybrid vibration damping system with PZT patches actuators was proposed. In this system the vibration suppression on the first flexural modes is yielded with use of the power PD-controllers, and oscillation damping on the torsional and higher flexural modes – by PZT patches loaded on a tuned RC circuits. Efficiency of the offered solution is illustrated by results of the transient analysis of the beam FE model and by experimental data obtained on a scaled model of the helicopter composite rotor blade with bonded flexural and torsional – operated PZT actuators.

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