Electrical control system for an aircraft steering vane

An electric control system for a steering control surface of an aircraft, said system (1) comprising:

• said steering control surface (2) which is mounted rotatably about an axis (Z-Z) so as to be able to take any angular deflection position inside a range of travel which is limited by a first and a second limits of travel;
• a set (11) of information sources capable of generating respectively the current values of flight parameters related to the aircraft;
• a rudder bar (5) which is capable of being actuated by a pilot of the aircraft and which is associated with a transducer (6) which delivers a piloting order representative of the action of the pilot on said rudder bar (5);
• a first means (7) which determines, on the basis of said piloting order, by taking account of said first and second limits of travel, a deflection order making it possible to bring said steering control surface (2) to a position situated between said first and second limits of travel and dependent on said piloting order;
• and
• an actuator (9) which receives this deflection order and which displaces said steering control surface (2) about said axis (Z-Z) as a function of said deflection order received,
• wherein it comprises, moreover, a second means (12) for varying, as a function of the current values of said flight parameters which are representative of actual displacement conditions of the aircraft, said first and second limits of travel, doing so at least partially in a dissymmetric manner, so as to adapt the range of travel of the steering control surface (2) to said actual displacement conditions of the aircraft, and for transmitting these first and second limits of travel to said first means (7).