Viswamurthy, SR and Ganguli, Ranjan (2006) Effect of Piezoelectric Hysteresis on Helicopter Vibration Control Using Trailing-Edge Flaps. In: Journal of Guidance, Contro, and Dynamics, 29 (5). pp. 1201-1209.
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This study investigates the effect of piezoelectric actuator hysteresis on helicopter vibration control using trailingedge ﬂaps. An aeroelastic analysis is used represent the helicopter with trailing-edge ﬂaps. A compressible unsteady aerodynamic model is used to predict the incremental airloads due to trailing-edge ﬂap motion. The material and mechanical hysteresis in the piezoelectric actuator is modeled using the classical Preisach model. Experimental data from the literature are used to estimate the weighting function through geometric interpretation and numerical implementation. Results are obtained from vibration control studies performed using a trailing-edge ﬂap with 1) ideal linear actuator and 2) real actuator with hysteresis modeled. Multicyclic control input gives 90 and 81% reduction in hub vibration at high-speed ﬂight $(\mu = 0:30)$ for the ideal and real actuator, respectively. In low-speed ﬂight $(\mu = 0:15)$, the hub vibration is reduced by 99 and 86% for ideal and real actuator, respectively. Results indicate that the presence of actuator hysteresis nonlinearity leads to deterioration in controller performance and lower vibration reductions in both high- and low-speed forward ﬂight.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||30 Nov 2007|
|Last Modified:||17 Jan 2012 06:19|
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