This disclosure relates to a satellite attitude control apparatus, comprising a spherical inertial body (1), which is arranged to be rotated in space in a desired rotational mode, one or more rotational feedback sensors. The apparatus further comprises a set of supports (3) and/or actuators (2), whereas one or more actuator is used to create rotational momentum to the spherical inertial body through friction. A set of three or more actuators and supports is used in order to keep the inertial body in place. Three or more supporting elements (supports and actuators) are used in combination with magnetic attraction or four or more supporting elements are used in case magnetic attraction is not in use. Supports can be passive or semi-active in order to reduce friction.