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基于压电纤维复合材料的旋转叶片主动控制

ACTIVE VIBRATION CONTROL OF A ROTATING BLADE BASED ON MACRO FIBER COMPOSITE

  • 摘要: 旋转叶片结构的振动失效占据了航空发动机整机故障的相当比重. 发展针对旋转叶片结构的减振技术对于减轻叶片重量, 提升叶片性能, 延长叶片寿命具有重要意义. 通过引入压电纤维复合材料(macro fiber composite, MFC)传感器和作动器, 研究预变形旋转叶片2:1内共振的主动控制. 建立考虑时滞效应的旋转叶片比例微分闭环控制系统运动方程. 通过摄动分析推导出受控叶片的演化方程, 并结合延拓法揭示速度增益、位移增益、时滞量等系统参数对受控系统稳态响应及稳定性的影响规律. 理论研究结果与数值结果得到相互验证. 研究发现时滞量对系统稳定性影响显著, 当时滞超过某临界值时, 演化方程原有的平衡点失稳, 闭环受控系统将缓慢进入一个大振幅的周期运动, 从而丧失控制效果. 位移增益存在一个范围使得系统出现多值稳态响应, 进而破坏了增益平面内系统稳定区和非稳定区域的直线边界. 不恰当的速度增益和位移增益会给受控系统引入新的共振. 研究结果为叶片结构的减振提供了理论基础.

     

    Abstract: For a long time, blade vibration failure occupies a quite large proportion of the total failure of the complete aeroengine. Developing the vibration reduction technology is of great importance for reducing the weight, improving the performance and extending the life for the rotating blade structure. In the present paper, the active vibration control is investigated in the presence of the 2:1 internal resonance of a pre-deformed rotating blade through introducing the sensors and actuators made of macro fiber composite (MFC). The equations of motion of the proportional-derivative feedback closed-loop control system are established with the effects of the time delay. The evolution equations of the controlled system are derived via the perturbation analysis. The effects of the velocity gain, the displacement gain, the time delay and some other system parameters on the steady-state response and the stabilities of the controlled system are revealed by the application of the continuation method. The analytic solutions are in good agreement with those obtained from the numerical integration. The main findings of the present study are as followings: the time delay has a significant effect on the stabilities of the controlled system. When the time delay exceeds a certain value, the equilibrium points of the evolution equations lose their stability. At the same time, the closed-loop control system enters a new period motion with a large vibration amplitude. There exists a range of displacement gain in which the multi-valued phenomenon appears in the steady-state response of the controlled system. Moreover, the straight borderline between the stable and the unstable regions in the gains plane is destroyed due to this range. Inappropriate assignments of the velocity gain and the displacement gain will cause a new resonance in the close-loop control system. The research results lay the theoretical foundations for the vibration reduction of the blade structure.

     

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