Abstract: A pointing mechanism for use in an electric propulsion system of a spacecraft, the pointing mechanism comprises a mobile plate adapted to receive a thruster and defining a thrust vector of the thruster received on the mobile plate. The pointing mechanism further comprises a rotary actuator coupled to the mobile plate by means of a connecting element, the rotary actuator being configured to rotate the connecting element about a rotational axis of the rotary actuator such that the thrust vector defined by the mobile plate rotates about the rotational axis, wherein the thrust vector is inclined relative to the rotational axis.