Abstract: A method of controlling a drive system of an aircraft. The drive system comprised a drive motor arranged to drive at least one wheel of an aircraft landing gear. A power signal indicative of a power level for the drive motor and a speed signal indicative of a rotation speed of the drive motor are received. A torque level for the drive motor is determined using the power signal and the speed signal. The drive motor is then driven such that the torque generated by the drive motor is at the determined torque level.

Abstract: The invention relates to an aircraft steering system using an aircraft ground taxi drive system whereby electrical power generated by a first motor-generator of a landing gear wheel drive system in a regenerative braking mode is supplied to a second motor-generator of a landing gear wheel drive system in a motorized driving mode.

Abstract: A method of controlling a drive system of an aircraft. The drive system comprised a drive motor arranged to drive at least one wheel of an aircraft landing gear. A power signal indicative of a power level for the drive motor and a speed signal indicative of a rotation speed of the drive motor are received. A torque level for the drive motor is determined using the power signal and the speed signal. The drive motor is then driven such that the torque generated by the drive motor is at the determined torque level.

Abstract: The invention relates to an aircraft steering system using an aircraft ground taxi drive system whereby electrical power generated by a first motor-generator of a landing gear wheel drive system in a regenerative braking mode is supplied to a second motor-generator of a landing gear wheel drive system in a motorized driving mode.

Abstract: An aircraft comprising a landing gear, having at least one wheel rotatably driven by an electric motor, and a motor control system. The control system comprises a control panel, presenting a first control configured to deliver a torque or power value to the motor along a direction of forward travel of the aircraft and second control configured to deliver a taxiing speed value along a direction of reverse travel, a control unit connected to the control panel and to the electric motor, presenting a first arrangement configured to control, in torque or power, the motor according to the value delivered by the first control, and a second arrangement configured to control, in speed, the motor according to the taxiing speed value delivered by the second control, and a speed sensor configured to measure the taxiing speed of the aircraft, and to transmit this speed information to the control unit.

Abstract: A method, apparatus and software is disclosed for controlling the heading of an aircraft travelling on the ground in which veering is detected and compensatory steering commands generated so as to automatically maintain a reference heading.

Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Abstract: The invention relates to a method and device for limiting the number of alarms generated by an anticollision system on board an airplane according to which the duration of a phase of capture of a setpoint altitude by the airplane is adjusted so that a theoretical time for collision with an intruder aircraft is greater than a predetermined threshold, when the airplane is close to said setpoint altitude and air traffic exists in the environment of said airplane.

Abstract: The invention relates to a method and device for limiting the number of alarms generated by an anticollision system on board an airplane according to which the duration of a phase of capture of a setpoint altitude by the airplane is adjusted so that a theoretical time for collision with an intruder aircraft is greater than a predetermined threshold, when the airplane is close to said setpoint altitude and air traffic exists in the environment of said airplane.

Abstract: The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Abstract: A method, apparatus and software is disclosed for controlling the heading of an aircraft travelling on the ground in which veering is detected and compensatory steering commands generated so as to automatically maintain a reference heading.