Patent ID: 8733847

Claim:
An asymmetrical electric braking architecture for aircraft, comprising a plurality of electro-mechanical brake actuators for selectively applying a braking force on friction elements in order to slow down rotation of braked wheels, said architecture comprising: a brake control unit for acting in normal mode to generate braking setpoint values in response to a braking order; a plurality of electro-mechanical actuator controllers, each powered by an AC electrical power source, and each including at least one inverter for supplying electrical power to the plurality of the electro-mechanical brake actuators in response to the braking setpoint values; at least one emergency brake power and control unit powered only by a DC electrical power source, and including at least one inverter for supplying electrical power to some of the plurality of the electro-mechanical brake actuators in response to the braking order; and protection means for channeling power supplied by the electro-mechanical actuator controllers or the emergency brake power and control unit towards the actuators while preventing power from being diverted towards the architecture, wherein the brake control unit and the plurality of electro-mechanical actuator controllers define a normal braking system, wherein the at least one emergency brake power and control unit defines an emergency braking system, and wherein the electric braking architecture is configured to be asymmetrical by excluding all elements of the normal braking system from being used in the emergency braking system.