This paper investigates effect of coupling of satellite translational dynamics and rotational kinematic aiming to design of geosynchronous satellite formation flying at drift phase to the determined operational nominal position at the orbital window in the geosynchronous orbit. Firstly, dynamical and kinematical equations of satellite, and then, the interaction of translational and rotational motion at drifting to the final position at the target orbit by considering satellite as a rigid object have been studied. Despite of similar studies utilized simplifications such as circular assumption of target orbit or various linearization methods, presented analysis of this paper are based on the general form of nonlinear translational equations. According to acquired results of investigating the coupled dynamics at the drift phase to the determined position at the orbital window by considering different attitudinal situations, drift considerations and procedure in presents of other satellites at the orbital window have been presented. Position and attitude of satellite have been controlled by utilization of PD control law associated with the optimized gains based of PSO optimization algorithm aiming to minimizing control effort and fuel and consequently minimizing fuel consumption and increasing satellite operational life. Acquired results from simulations represent effectiveness of the proposed methodology.