Piezoelectric actuators are used to drive trailing-edge flaps of helicopters, but hysteresis of these actuators can degrade the vibration control performance of the active rotor. To solve this problem, hysteresis modeling and suppression are studied for a piezoelectric actuator. The hysteresis curves of this actuator at different frequencies are measured, and the Bouc-Wen model is utilized to model its rate-dependent hysteresis. Particle Swarm Optimization (PSO) algorithm is selected to identify the unknown parameters of the Bouc-Wen model, and a good agreement is shown between experimental results and model outputs for a range of frequencies from 10 Hz to 60 Hz, demonstrating that the established model is capable of simulating the actuator’s dynamic hysteresis. A compound control scheme combining feedforward control based on inverse Bouc-Wen model and PID feedback control is established, and experimental results show that hysteresis of the piezoelectric actuator is suppressed remarkably at frequency range of 10 Hz to 60 Hz. Hysteresis model of the piezoelectric actuator is incorporated into helicopter rotor dynamic model to study the effect of actuator hysteresis on vibration control performance. Simulations of a model rotor with trailing-edge flaps are conducted in moderate speed forward flight condition. The results show that hysteresis can result in performance degradation of the trailing-edge flaps, while the compound control algorithm has the potential to improve the control authority of active rotor.
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