Effect of Piezoelectric Hysteresis on Helicopter Vibration Control Using Trailing-Edge Flaps

摘要: This study investigates the effect of piezoelectric actuator hysteresis on helicopter vibration control using trailingedge flaps. An aeroelastic analysis is used represent with trailing-edge A compressible unsteady aerodynamic model to predict incremental airloads due flap motion. The material and mechanical in modeled classical Preisach model. Experimental data from literature are estimate weighting function through geometric interpretation numerical implementation. Results obtained studies performed a 1) ideal linear 2) real modeled. Multicyclic input gives 90 81% reduction hub at high-speed flight $(\mu = 0:30)$ for actuator, respectively. In low-speed 0:15)$, reduced by 99 86% indicate that presence nonlinearity leads deterioration controller performance lower reductions both high- forward flight.