Abstract: A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

Abstract: A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

Abstract: A control method for controlling an electric motor driving rotation of an aircraft wheel (4a, 4b) for generating a torque command for controlling the motor, the method being characterized in that it comprises implementing: a first servo-control loop (23) having as its input signal a speed setpoint, having as its return signal a signal representative of the speed of the wheel or of the aircraft, and having as its output signal an acceleration setpoint (Cons_a); and a second servo-control loop (24) having as its input signal the acceleration setpoint (Cons_a), as its return signal a signal representative of the acceleration (Ar) of the wheel or of the aircraft, and as its output signal the torque command.

Abstract: A control method for controlling an electric motor driving rotation of an aircraft wheel (4a, 4b) for generating a torque command for controlling the motor, the method being characterized in that it comprises implementing: a first servo-control loop (23) having as its input signal a speed setpoint, having as its return signal a signal representative of the speed of the wheel or of the aircraft, and having as its output signal an acceleration setpoint (Cons_a); and a second servo-control loop (24) having as its input signal the acceleration setpoint (Cons_a), as its return signal a signal representative of the acceleration (Ar) of the wheel or of the aircraft, and as its output signal the torque command.