Modeling and compensation of piezoceramic actuator hysteresis for helicopter vibration control
Modeling and compensation of piezoceramic actuator hysteresis for helicopter vibration control
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DOI：
10.1016/j.sna.2006.09.020
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发表时间：
2007-04-15
影响因子：
4.6
通讯作者：
Ganguli, Ranjan
中科院分区：
文献类型：
--
作者：
Viswamurthy, S. R.;Ganguli, Ranjan
压电陶瓷材料中的滞后现象在诸如振动控制的应用中的压电致动器的使用中引起相当大的复杂性。在这项研究中，经典的Preisach模型被用来描述迟滞在压电叠层致动器用于移动后缘襟翼直升机振动控制。致动器中的滞后主要是由于材料非线性，并且在较小程度上是由于放大机构中的损耗。大多数直升机振动控制研究忽略了迟滞对作动器性能的影响。通过对直升机的气动弹性分析，确定了襟翼最大减振所需的运动。数值计算结果表明，作动器迟滞的完全补偿可以使直升机的振动减少90%。当致动器由线性模型表示或当补偿器仅基于致动器的主要材料滞后时，振动控制系统的性能显著恶化。因此，作动器中材料和机械滞后的完全补偿对直升机后缘襟翼振动控制系统的性能至关重要。(c)2006 Elsevier B.V.保留所有权利。
Hysteresis in piezoceramic materials causes considerable complications in the use of piezo actuators in applications, such as vibration control. In this study, the classical Preisach model is used to characterize the hysteresis in a piezostack actuator used to move a trailing-edge flap for helicopter vibration control. The hysteresis in the actuator is primarily due to material nonlinearity and to a lesser extent due to losses in the amplification mechanism. Most helicopter vibration control studies ignore the effect of the hysteresis on the actuator performance. The desired motion of the flap for maximum reduction in vibration is determined using an aeroelastic analysis of the helicopter. Numerical results indicate that complete compensation of actuator hysteresis can result in up to 90% reduction in helicopter vibrations. The performance of the vibration control system deteriorates considerably when the actuator is represented by a linear model or when the compensator is based only on the primary material hysteresis of the actuator. Complete compensation of both material and mechanical hysteresis in the actuator is therefore critical to the performance of the trailing-edge flap vibration control system in a helicopter. (c) 2006 Elsevier B.V. All rights reserved.