Abstract: For solving the problem of large-angle maneuver control for satellites subject to input saturation, a low gain feedback control law based on characteristic model is designed. The characteristic model is established in the form of a secondorder timevariable difference equation based on the dynamic model of the initial system, and the range of characteristic model parameters is calculated. The low-gain feedback law is instructed and is designed based on the characteristic model to deal with the performance deterioration or instability caused by input saturation. Characteristic model extends the application range of low-gain feedback law to some complex systems. By simulating single axes attitude maneuvering process of satellites subject to input saturation, availability of the lowgain control law based on this characteristic model is validated.

Key words: input saturation, attitude maneuver, characteristic model, low gain feedback control