Dynamics Features and Algorithms of Gyroscopic Control of Large-Scale Flexible Spacecraft

Abstract The paper discusses a gyro-moment stabilization system of a flexible spacecraft (FS). The possibility of using a proportionally-differential algorithm (PD) for attitude control employing the single-gimbals control moment gyroscopes (gyrodines) is investigated. Specifics of this type of control at “infra-low” (0.01–0.1 Hz) frequencies of the object's flexible oscillations are studied. The questions of designing an additional gyro-stabilization subsystem at weakly damped and low-frequency flexible oscillations are considered. An adaptive regulator is suggested for FS that is described either by a not exactly defined mathematical model or by a non-stationary model.