Abstract: The dynamical problem of a spin satellite attitude maneuver to any aim attitude is discussed in this paper. A set of analytical formulae of attitude of the spin satellite which is applied by a series of control pulses torque have been derived. These formulae described the variational rules of angular momentum, of nutation angle, and of attitude phase angle with control torque and control times. They may be directly applied to the design of the satellite attitude control system and attitude determination. It is necessary to point out that both cases in which the spin axis is to orient normal to orbit normal to orbit or coincide with the Sun direction are all the special examples of what we obtained.