Abstract: A new PIDlike attitude control law with saturated integrals is proposed for the control of spacecraft. The control law can not only eliminate the influence of constant disturbances, but prevent the control torque from getting too large by means of saturation constraint on the integrals. With the associated theory of forwarding system, it is rigorously proven that the closed loop is globally asymptotically stable, and the corresponding sufficient conditions of the relevant parameters are also derived. Numerical simulations demonstrate the effectiveness of the proposed approach.

Key words: attitude control, PIDlike control, saturation control