Abstract: The backstepping control method was applied to the slew maneuver of the rigid spacecraft. In order to avoid the complicated calculation of the derivation of the intermediate control law which is required in the conventional backstepping method, the intermediate control law presents in a form of differential equation. On this basis, two methods were applied to reduce the requirement in the max actuator output torque by means of postponing the peak of the control torque. One method is to change the initialization of the intermediate control law. The other is to utilize a worse angular velocity tracking law. The system stability with the second control law depends on the parameters of the controller, however, the max control torque can be accurately restricted. Simulation results illuminate the availability of the derived control laws.