Abstract: A vane control system (2) for a guided missile (1) with at least two vanes (3) has two toothed rings (7, 8), which are arranged in parallel to one another on both sides of the vane axes (18), are driven by pinions (15, 16) which are driven by electric motors and rotate continuously. Two drive gears (11, 17), which engage one of the toothed rings (7, 8) and rotate together with them such that they have opposite directions of rotation, are arranged on each vane axis (18). A clutch disk (19), which can be connected to one of the drive gears (11, 17), as a result of which the vanes (3) can be rotated in the desired direction, is arranged between the drive gears (11, 17). A brake (22) for fixing the vane axis (18) and an incremental transducer (23) for indicating the actual position of the vane are arranged on each vane axis (18).