Many vibration suppression systems are required to function across a variety of different temperatures, yet most literature ignores the effects of temperature changes on the structure and on the closed loop response. This paper presents an experimental implementation of a vibration suppression system based on a piezoceramic actuator that effectively controls vibration of a clamped panel as it undergoes a variation in ambient temperature. The desire to reduce fatigue in aircraft panels motivates this experimental investigation and implementation.
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