Vibration control of plate structures using PZT actuators and type II fuzzy logic

Focuses on methods for achieving active damping on plate structures by use of discrete point piezoelectric sensors and actuators (PZTs). A typical spacecraft or launch vehicle structure consists of a series of thin panels that are clamped around their individual boundaries by a continuous metal frame. Avionic equipment mounted onto these panels can be exposed to excessive vibration due to large acoustic emanations during launch. In this study, a two degree-of-freedom model has been constructed for a structural dynamic system consisting of a linear elastic plate bonded with piezoelectric sensors and actuators. The signal from the sensors is the input of our type II fuzzy logic system, and the actuators receive its output. To test this new control technique, a digital control system was built that uses the MATLAB/SIMULINK modeling software in a personal computer. The off-line simulation results confirm that the fuzzy type II control method is robust and efficient in the suppression of steady-state resonance vibrations