Robust stability of nonlinear gyro-moment orientation system of flexible spacecraft
The paper discusses a method of synthesis of a nonlinear orientation system with gyro-flywheels. The system must guarantee the robustness of the stability property of the flexible spacecraft (FS) movement. Two-stage procedure of the FS parameters correction and further extension of the base control algorithm was suggested. In the extended algorithm the estima-tions of the unstable modes of the FS elastic oscillations were used. Some results of computer simulation of the suggested orientation system were obtained. These results confirm the effi-ciency of the control algorithm and the stability robustness of the FS construction elastic oscillations.