Active Vibration Control Of Helicopter Frame Structure Driven By Piezoelectric Stack Actuators

The serious vibration problem of helicopter limits its performance. Method must be taken to controlthe helicopter vibration. Active vibration control is effective and adaptive, therefore has become animportant research and development direction of helicopter vibration control. The piezoelectric stackactuators (PSA) are light, small and convenient to install. So they are ideal actuators for activevibration control.From the piezoelectric equations of piezoelectric ceramics, this article deduced the mechanicalmodel of the piezoelectric stack actuator idealizing it as a force generator. By using the technique offinite element correction, a frame structure which have the similar dynamic character as the realhelicopter airframe, is designed for the modeling and simulation of active vibration control. The realframe structure is fabricated out, and based on that, modal experiment is carried out. The result showsthat the first three natural vibration frequency of the real frame structure are similar as the helicopterairframe. State space formulations are established and active vibration control is carried out byoptimal algorithm in frequency domain. Good control suppression has been achieved. In this paper, asimulation system, which based on the optimal control law in frequency domain, is established in thesoftware Simulink. Simulations were carried out in different exciting conditions. Simulation showsthat the control algorithm have great vibration suppression effect and can adapt to different excitingconditions.