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In this paper, the problem of attitude synchronization for flexible spacecraft system with actuator faults is investigated. The spacecraft formation is studied in a leader-following architecture and the reference attitude is represented by a virtual leader. A distributed unit quaternion-based synchronization control law is proposed for flexible spacecraft with loss of actuator effectiveness fault...
This paper considers robust vibration control of uncertain flexible structures. It firstly uses finite element method (FEM) to formulate the model and then reduces the degrees of freedom by employing mode truncation method. It compares the control effects of different number of modes reserved, and presents the principle of determining the number of modes truncated. Then it chooses the number and optimal...
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