Electrical rudder control system for an aircraft

A rudder control system for an aircraft, of an electrical type, without any mechanical control trim, and comprising:

• a rudder bar (2) being adapted to be actuated by a pilot of said aircraft;
• means (3) for automatically detecting the position of the rudder bar (2) and generating an electrical control signal being representative of such position;
• and
• calculation means (4) receiving such electrical control signal and automatically generating, thru at least the latter, control orders which are transmitted to operating means (6) for a vertical rudder (7) of the aircraft,
• wherein it comprised additionally:
• auxiliary means (10) for generating a rudder trim order under the shape of an auxiliary electrical signal so that the nil effort rudder bar position is the neutral position of the rudder bar (2);
• and
• means (11, 12) to transmit such auxiliary electrical signal to said calculation means (4) being formed so as to generate, thru both this auxiliary electrical signal and said electrical control signal, the control orders which are transmitted to the operating means (6) for the vertical rudder (7), said control orders being calculated from an overall order corresponding to the sum of the order relative to the rudder bar (2) position represented by the electrical control signal and the compensation order represented by the auxiliary electrical signal generated by said auxiliary means (10) so that the nil effort rudder bar position is always the neutral position of the rudder bar (2).