• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of guidance, control, and dynamics >Control Evaluations of Semiactive Fluid-Elastomeric Helicopter Lag Damper
【24h】

Control Evaluations of Semiactive Fluid-Elastomeric Helicopter Lag Damper

机译：半活性流体-弹性直升机滞后阻尼器的控制评估

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A semiactive magnetorheological fluid-elastomeric device has been assembled and evaluated in control experiments to demonstrate its utility to compensate for measured changes as a helicopter lag damper. The baseline used in this study was lag damper (snubber) for a hingeless helicopter rotor that employs both elastomers and fluids: that is, a fluid-elastomeric damper. This damper was disassembled and modified to include two internal magnetorheological control valves, and the existing hydraulic fluid was replaced with magnetorheological fluid. Hence, the resulting prototype damper is a retrofit design that can easily be installed in a test rotor in future evaluations. The magnetorheological fluid-elastomeric damper was subject to extensive performance characterization at displacement amplitudes ranging from 0.8 to 3.4 mm, temperatures ranging from 20 to 55℃, and control currents up to 2.0 A. Using this database and a hydromechanical model of the damper, control systems were designed to track a reference damping profile, which is a function of amplitude only, in the presence of measured amplitude and temperature variations at the rotor lag frequency (3.8 Hz). Both open-loop (interpolating lookup table) and closed-loop (proportional-integral and gain scheduling) techniques were employed in simulations and experiments. The results demonstrated that all of the control schemes were effective, although a minimum tracking error was achieved with the closed-loop systems. Comparing the two closed-loop systems, the gain-scheduling controller provided a faster response overall, but the improvement was marginal.
机译：半活性磁流变流体弹性器件已组装并在控制实验中进行了评估，以证明其可作为直升机滞后阻尼器补偿所测量的变化。在这项研究中使用的基准是滞后阻尼器（缓冲器），用于同时使用弹性体和流体的无铰链直升机旋翼：即，流体弹性阻尼器。对该阻尼器进行了拆卸和修改，使其包括两个内部磁流变控制阀，并用磁流变液代替了现有的液压油。因此，最终的原型阻尼器是一种改型设计，可以在将来的评估中轻松安装在测试转子中。磁流变流体弹性阻尼器在位移幅度为0.8至3.4 mm，温度范围为20至55℃，控制电流高达2.0 A的情况下经受了广泛的性能表征。使用该数据库和阻尼器的流体力学模型，可控制系统被设计为在转子滞后频率（3.8 Hz）处存在测得的幅度和温度变化时，跟踪参考阻尼曲线，该曲线仅是幅度的函数。在仿真和实验中都采用了开环（插值查找表）和闭环（比例积分和增益调度）技术。结果表明，尽管使用闭环系统可实现最小跟踪误差，但所有控制方案均有效。与两个闭环系统相比，增益调度控制器总体上提供了更快的响应，但改进幅度很小。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号