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首页> 外文会议>MV2 Convention on Active Control in Mechanical Engineering, Oct 22-23, 1997, Lyon, France >Stabilizing helicopter rotor blades using delayed feedback
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Stabilizing helicopter rotor blades using delayed feedback

机译：使用延迟反馈稳定直升机旋翼桨叶

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摘要

A new control law for stabilizing the periodic motion of uncertain systems, with particular application to helicopter rotor blades, is presented. The control law uses proportional displacement and velocity feedback with a time delay equal to the period of the motion being stabilized. No knowledge of the dynamics of the system being controlled or the desired trajectory is required. The control law is tested on a two-degree-of-freedom mathematical model which approximates the motion of a helicopter rotor blade in both hover and forward flight. Analysis of the developed perturbation equations shows that a significant improvement in the stability of the motion of the rotor blade is achieved by the appropriate choice of the control parameters. The control law greatly affects the transient states without altering the steady-state motion of the uncontrolled system. This feature is particularly important for helicopters because the steady-state motion of the rotor blades determines the flight path.
机译：提出了一种稳定不确定系统周期性运动的新控制律，特别适用于直升机旋翼桨叶。控制律使用比例位移和速度反馈，其时延等于稳定的运动周期。不需要了解所控制系统的动力学或所需的轨迹。该控制律是在两自由度数学模型上进行测试的，该模型可以模拟直升机旋翼桨叶在悬停和向前飞行中的运动。对已开发的摄动方程的分析表明，通过适当选择控制参数，可以显着提高转子叶片运动的稳定性。控制律极大地影响了瞬态，而不会改变不受控制系统的稳态运动。该特性对直升机而言尤其重要，因为旋翼桨叶的稳态运动决定了飞行路径。

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