Active vibration control

About: Active vibration control is a research topic. Over the lifetime, 6770 publications have been published within this topic receiving 76599 citations. The topic is also known as: active vibration damping.

Active vibration control system for attenuating engine generated vibrations in a vehicle

Abstract: An active vibration control (AVC) system is disclosed for attenuating vibrational frequency components generated by an engine and transferred through an engine mounting unit to vibrate a motor vehicle body. The motor vehicle is characterized by sprung mass and unsprung mass natural resonant frequencies at which the body also vibrates when the vehicle is driven over an undulating road surface. The AVC system operates by generating input signals representing different vibrational frequency components generated by the engine based upon sensed changes in engine rotation. Each input signal is filtered by an adaptive filter to produce a respective output signal. The output signals are summed to produce a canceling signal for driving an inertial mass shaker mounted on the body. The shaker inversely vibrates the body with respect to the different vibrational frequency components transferred to the body from the engine. A vibration sensor mounted to the body proximate the shaker monitors body vibration and develops a representative error signal. Vibrational components associated with the sprung and unsprung mass natural resonant frequencies are substantially removed from the error signal using a dual notch filter. The filtered error signal is then used to adjust the filtering characteristics of the adaptive filter to minimize vibration of the body caused by the different vibrational frequency components transferred to the body from the engine.

Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics

Abstract: This paper presents a dual-stage control system design method for the three-axis-rotational maneuver control and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design approach, the attitude control system and vibration suppression were designed separately using a lower order model. Based on the sliding mode control (SMC) theory, a discontinuous attitude control law in the form of the input voltage of the reaction wheel is derived to control the orientation of the spacecraft actuated by the reaction wheel, in which the reaction wheel dynamics is also considered from the real applications point of view. The asymptotic stability is shown using Lyapunov analysis. Furthermore, an adaptive version of the proposed attitude control law is also designed for adapting the unknown upper bounds of the lumped disturbance so that the limitation of knowing the bound of the disturbance in advance is released. In addition, the concept of varying the width of boundary layer instead of a fixed one is also employed to eliminate the chattering and improve the pointing precision as well. For actively suppressing the induced vibration, modal velocity feedback and strain rate feedback control methods are presented and compared by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty.