Active vibration control experiments on an AgustaWestland W30 helicopter airframe
Active vibration control experiments on an AgustaWestland W30 helicopter airframe
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DOI：
10.1177/0954406211423609
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发表时间：
2012-06
期刊：
影响因子：
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通讯作者：
J. Mottershead;M. G. Tehrani;S. James;P. Court
中科院分区：
文献类型：
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作者：
J. Mottershead;M. G. Tehrani;S. James;P. Court
本文介绍了作者所发展的一种振动控制技术-即所谓的“感受法”-在耶奥维尔振动试验室中对AgustaWestland W30直升机机体的实际应用。2011年2月和3月，在对耶奥维尔现场的两次访问中，进行了总共5天的实验工作。在实验中，使用了现有的电液作动器;它们被安装在机身结构中，最初是为了通过耶奥维尔的阿古斯塔韦斯特兰直升机公司开发的结构响应主动控制方法来抑制振动而设计的。加速度计被放置在机身周围的大量点上，并进行了初始开环模态试验。在随后的测试中，在较高的致动器输入电压下，发现相当大的非线性，以至于某些模式的顺序发生了变化。振动模式，一般来说，严重阻尼。使用在较高输入水平下获得的测量频率响应函数来实现控制。在获得必要的测量值后，进行了仿真，并使用MATLAB/Simulink和dSPACE实现了控制器。闭环极点大多分配有小的真实的部分，使得系统将被轻微阻尼，并且在所测量的闭环频率响应函数中尖锐的峰值将是明显的。获得了复s平面中开环和闭环极点的位置，以验证所需的极点分配是否已经发生。
This article describes the practical application of a vibration control technique, developed by the authors and known as the receptance method, to the AgustaWestland W30 helicopter airframe in the vibration test house at Yeovil. The experimental work was carried out over a total of 5 days in two visits to the Yeovil site during February and March 2011. In the experiments, existing electro-hydraulic actuators were used; they were built into the airframe structure and originally designed for vibration suppression by the methodology known as active control of structural response developed at the AgustaWestland Helicopters site in Yeovil. Accelerometers were placed at a large number of points around the airframe and an initial open-loop modal test was carried out. In a subsequent test, at higher actuator input voltage, considerable non-linearity was discovered, to the extent that the ordering of certain modes had changed. The vibration modes were, in general, heavily damped. Control was implemented using measured frequency response functions obtained at the higher input level. After acquiring the necessary measurements, simulations were carried out and the controller was implemented using MATLAB/Simulink and dSPACE. The closed-loop poles were mostly assigned with small real parts so that the system would be lightly damped and sharp peaks would be clearly apparent in the measured closed-loop frequency response functions. Locations of the open- and closed-loop poles in the complex s-plane were obtained to verify that the required assignment of poles had taken place.