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The present work proposed an hourglass-type electromagnetic isolator with negative resistance (NR) shunt circuit to achieve the effective suppression of the micro-amplitude vibration response in various advanced instruments and equipment. By innovatively design of combining the displacement amplifier and the NR electromagnetic shunt circuit, the current new type of vibration isolator not only can effectively solve the problem of micro-amplitude vibration control, but also has significant electromechanical coupling effect, to obtain excellent vibration isolation performance. The design of the isolator and motion relationship is presented firstly. The electromechanical coupling dynamic model of the isolator is also given. Moreover, the optimal design of the NR electromagnetic shunt circuit and the stability analysis of the vibration isolation system are carried out. Finally, the simulation results about the transfer function and vibration responses demonstrated that the isolator has a significant isolation performance. [ABSTRACT FROM AUTHOR]

A bilateral piezoelectric stack actuator (BPSA) is introduced, and its actuated property is also analyzed. Usually, a piezoelectric stack can only undertake significant compressive loads but cannot tolerate tension, while this new actuator is able to generate obvious bilateral actuated outputs. The actuated principle of the new actuator is analyzed firstly. The linear and nonlinear models are also built up. The latter is to analyze the piezoelectric hysteresis based on the classical Preisach model. Moreover, the effect of the preload on the actuator is considered. By comparison with the experiment results, the Preisach model is valid for the present actuator. [ABSTRACT FROM AUTHOR]

An active vibration control scheme was proposed based on Macro Fiber Composite (MFC) actuators for the bending and torsional vibration control of large flexible lightweight wing structures. Firstly, a finite element modeling and modal analysis of a flexible wing are carried out. Further, the number, type, and location distribution of the MFC actuators bonded on the supported beam of the wing are designed. Then, the actuated characteristics of the two kinds of MFC actuators required for bending and torsional vibration controls was theoretically analyzed. The simulation model of the overall vibration control system was also finally obtained. Finally, through ANSYS simulation analysis, the vibration control effect of the current control system on the first two-order low-frequency modal response of the wing structure is given. The simulation results show that the proposed active vibration control scheme has specific feasibility and effectiveness. [ABSTRACT FROM AUTHOR]