Method of powering an electromechanical brake actuator for an aircraft wheel

A method of electrically powering an electro-mechanical braking actuator fitted to an aircraft wheel brake, the method comprising:

• determining a saturation value of a power supply current as a function of an internal temperature of the electro-mechanical braking actuator while the electro-mechanical braking actuator is in operation, by measuring a value of an approach current flowing through an electric motor of the electro-mechanical braking actuator during an approach stage at a given speed, which value depends on the internal temperature of the electro-mechanical braking actuator, and adding an additional current to the measured value of the approach current in order to determine the saturation value, the saturation value being adjusted so that the saturation value lies in the range from a predetermined minimum value to a predetermined maximum value;
• and
• delivering the power supply current to the electro-mechanical braking actuator so that the power supply current is saturated to the saturation value in order to limit the current consumed by the electro-mechanical braking actuator and thereby limit the forces developed by the electro-mechanical braking actuator.

A method of electrically powering electro-mechanical braking actuators fitted to an aircraft wheel brake, the method comprising:

• determining a saturation value of a power supply current as a function of an internal temperature of the electro-mechanical braking actuator while the electro-mechanical braking actuator is in operation, by measuring a value of an approach current flowing through an electric motor of the electro-mechanical braking actuator during an approach stage at a given speed, which value depends on the internal temperature of the electro-mechanical braking actuator, and adding an additional current to the measured value of the approach current in order to determine the saturation value, wherein the approach current values of the various electro-mechanical braking actuators are compared in order to detect and eliminate any outlier value, and to replace the outlier value with a corrected value;
• and
• delivering the power supply current to the electro-mechanical braking actuator so that the power supply current is saturated to the saturation value in order to limit the current consumed by the electro-mechanical braking actuator and thereby limit the forces developed by the electro-mechanical braking actuator.

A method of electrically powering an electro-mechanical braking actuator fitted to an aircraft wheel brake, the actuator having two casings, with a first casing containing an electric motor of the electro-mechanical braking actuator and a second casing containing a mechanical transmission and a pusher of the electro-mechanical braking actuator, the method comprising:

• determining a saturation value of a power supply current as a function of an internal temperature of the electro-mechanical braking actuator while the electro-mechanical braking actuator is in operation, wherein the internal temperature of the electro-mechanical braking actuator is measured and the saturation value is calculated using the internal temperature, and wherein, in order to determine the internal temperature, a temperature sensor is arranged in the first casing in order to measure indirectly the temperature of a lubricant of the mechanical transmission contained in the second casing;
• and
• delivering the power supply current to the electro-mechanical braking actuator so that the power supply current is saturated to the saturation value in order to limit the current consumed by the electro-mechanical braking actuator and thereby limit the forces developed by the electro-mechanical braking actuator.