Vibration suppression for flexible satellite during attitude stabilization

This paper treats the problem of vibration mode and attitude control stabilization of a spacecraft with flexible appendage based on state feedback controller (SFC) and vibration suppression using disturbance observer (DO). The spacecraft has a central rigid body and large flexible appendage. The unwanted coupling torques in attitude dynamics that is generated by the vibration of large flexible appendage can affect the performance of attitude stabilization systems. By intergrading DO with SFC, the vibration torques can be reduced and the performance of the desired dynamic can be guaranteed. The Simulation results for flexible spacecraft are given to demonstrate the excellent performance of the composite control approach.

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