Active aeroelastic flutter analysis and vibration control of supersonic beams using the piezoelectric actuator/sensor pairs
Active aeroelastic flutter analysis and vibration control of supersonic beams using the piezoelectric actuator/sensor pairs
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DOI：
10.1088/0964-1726/20/5/055013
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发表时间：
2011-05-01
影响因子：
4.1
通讯作者：
Li, Feng-Ming
中科院分区：
文献类型：
--
作者：
Song, Zhi-Guang;Li, Feng-Ming
利用压电材料对各种结构进行振动主动控制已得到广泛的研究。本文对压电材料应用于超声速梁的主动气动弹性颤振特性和振动控制进行了深入的研究。将压电材料粘贴在梁的上、下表面，作为作动器和传感器，对超声速梁进行气动弹性颤振主动抑制。采用超声速活塞理论计算气动压力。采用汉密尔顿原理和假设模态法建立了结构系统的动力学模型。利用标准特征值法，得到了复特征值问题的解。采用速度负反馈控制策略获得主动阻尼。计算了气动弹性颤振边界，分析了主动气动弹性颤振特性。采用Houbolt数值算法计算了结构系统的脉冲响应，研究了气动弹性振动主动控制问题。分析了无量纲气动压力对颤振主动控制的影响。从数值结果可以看出，通过使用压电作动器/传感器对，可以提供主动阻尼，可以显著地改善超声速梁的气动弹性颤振特性，并且可以显著地减小气动弹性振动的振幅，特别是在颤振点处。在一定的反馈控制增益范围内，随着反馈控制增益的增大，颤振气动压力（或颤振速度）增大，控制效果也得到改善。
The active vibration control of all kinds of structures by using the piezoelectric material has been extensively investigated. In this paper, the active aeroelastic flutter characteristics and vibration control of supersonic beams applying the piezoelectric material are studied further. The piezoelectric materials are bonded on the top and bottom surfaces of the beams to act as the actuator and sensor so that the active aeroelastic flutter suppression for the supersonic beams can be conducted. The supersonic piston theory is adopted to evaluate the aerodynamic pressure. Hamilton's principle with the assumed mode method is used to develop the dynamical model of the structural systems. By using the standard eigenvalue methodology, the solutions for the complex eigenvalue problem are obtained. A negative velocity feedback control strategy is used to obtain active damping. The aeroelastic flutter bounds are calculated and the active aeroelastic flutter characteristics are analyzed. The impulse responses of the structural system are obtained by using the Houbolt numerical algorithm to study the active aeroelastic vibration control. The influences of the non-dimensional aerodynamic pressure on the active flutter control are analyzed. From the numerical results it is observed that the aeroelastic flutter characteristics of the supersonic beams can be significantly improved and that the aeroelastic vibration amplitudes can be remarkably reduced, especially at the flutter points, by using the piezoelectric actuator/sensor pairs which can provide an active damping. Within a certain value of the feedback control gain, with the increase of it, the flutter aerodynamic pressure (or flutter velocity) can be increased and the control results are also improved.