Abstract
Current trend in the spacecraft design lies in using large, complex and lightweight space structures to achieve increased functionality with the lower launch costs. Combination of large and lightweight designs results in these space structures becoming extremely flexible and acquiring the low frequency fundamental vibration modes. These modes could be used in various tasks, such as turning, guidance maneuvers and docking with the other spacecraft. Effective vibration suppression is a challenge for the spacecraft designers. One of the promising methods for solving this problem is introduction of the built-in piezoelectric elements as the actuators. The paper analyzes various control systems for the built-in piezoelectric elements to ensure the payload vibration protection. Experimental studies of these systems were carried out to determine the dynamics coefficient levels.
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