The aim of the present thesis is to develope a simulink environment for the analysis and simulation of the final approach phase of a rendezvous manoeuver for an on-orbit servicing applications. The first part is aimed to design the active stabilization system for the chaser spacecraft using thrusters, the reaction wheels and the modulator PWPFM is implemented, furthermore, the thruster managment function, modeling of thruster in simulink environment and the thruster placement are carried out. Moreover, after that the control and guidance functions are implemented using LQR. The second part has the objective to study the dynamic coupling between the manipulator and the spacecraft during the end effector motion.