Stabilization of low-frequency vibrations of a large satellite structure with powered gyro control

This paper considers the feasibility of using a discrete-time proportional-plus-derivative (PD) algorithm as a control law of gyrodyns for eliminating the drawback of their frames precession in the stabilization mode of the angular position of a deformable spacecraft. Moreover, we analyze dynamics features of applying such approach to control orientation of the above class of spacecrafts under "infralow" (0.01---0.1 Hz) frequencies of flexible vibrations of their structure. Finally, the issues concerning organization of a subsystem of additional gyro stabilization for weakly damped low-frequency vibrations are treated.