The (w,z) parametrization is a new attitude describing method, which describes the satellite attitude using two perpendicular rotations. The kinematics equations expressed by w and z parameters can be decomposed from each other in favor of controlling respectively. Firstly the (w,z) parameters were deduced and based on it the kinematics and dynamics model were established, then aiming at the attitude reorientation control of non-symmetry satellite under actuator failure, the feasible trajectory using differential flatness method as well as the corresponding controllers were designed. The effectiveness of the proposed method was illustrated by simulation tests using thrusters system which was based on pulse width modulation (PWM) tech-nology.