Conference Paper

Active vibration control of aerospace structures using a modified Positive Position Feedback method

Center for Vehicle Syst. & Safety, Virginia Tech., Blacksburg, VA, USA
DOI: 10.1109/ACC.2009.5159955 Conference: American Control Conference, 2009. ACC '09.
Source: IEEE Xplore

ABSTRACT A positive position feedback controller is modified and a new active vibration control technique is developed. Unlike the conventional positive position feedback, the new controller separates the damping and stiffness control using two parallel first order and second order compensators. The second order compensator has a damping ratio as low as the damping of flexible structure to provide periodic vibration control. Simultaneously, the high damping is made available through a first order compensator. The new controller is applicable to a strain-based sensing/actuating approach and can be extensively applied to piezoelectrically controlled systems. Control gains are obtained by performing the stability analysis. The controller is verified experimentally using a plate vibration suppression setup. The plate is controlled through two piezoelectric patches and its vibrations are monitored by ten sensors mounted on the surface of the plate. The results confirm that the new controller is able to provide good vibration reduction, with the ability to be used to simultaneously control more than one natural frequency.

  • Journal of Vibration and Acoustics. 01/2006; 128(2).
  • [Show abstract] [Hide abstract]
    ABSTRACT: This paper is concerned with vibration control of a flexible spacecraft in the presence of parametric uncertainty/external disturbances as well as control input nonlinearity through distributed piezoelectric sensor/actuator technology. To satisfy pointing requirements and simultaneously suppress vibrations, two separate control loops are adopted. The first uses piezoceramics as sensors and actuators to actively suppress certain flexible modes by designing suboptimal positive position feedback (SOPPF) compensators which add damping to the flexible structures in certain critical modes. The problem of determining the SOPPF gain is formulated as static output feedback problem. The second feedback loop is designed based on an output feedback sliding mode control (OFSMC) design where control input nonlinearity is taken into consideration. The controller has the ability to reject the disturbance, deal with uncertainty and to ensure that the system trajectories globally converge to the sliding mode. Furthermore, an adaptive version of the proposed controller is achieved through releasing the limitation of knowing the bounds of the uncertainties and perturbations in advance. Simulation studies for the proposed control strategy on a flexible spacecraft have been carried out which demonstrate the effectiveness of the proposed approach.
    Journal of Vibration and Control 01/2007; 13(11):1573-1602. · 4.36 Impact Factor

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