Electronic motor actuators brake inhibit for aircraft braking system

A method for controlling a plurality of electric motor-actuators associated with an aircraft wheel brake, the aircraft brake system including a plurality of electric motor-actuators, said plurality of electric motor-actuators including a first portion of said plurality of electric motor-actuators and a second portion of said plurality of electric motor-actuators, said plurality of electric motor-actuators being operatively connected to an aircraft wheel brake to actuate the aircraft wheel brake, an electronic brake actuation controller operatively connected to said plurality of electric motor-actuators and configured to control the operation of said first and second portions of said plurality of electric motor-actuators, and a brake system control unit configured to receive a brake pedal command for a commanded braking force, said brake system control unit being connected to said electronic brake actuation controller and configured to control said electronic brake actuation controller, the method comprising:

• generating a brake pedal command for a commanded braking force for an aircraft wheel brake;
• receiving said brake pedal command;
• and
• controlling said electronic brake actuation controller in an inhibited braking mode such that one of said first and second portions of said plurality of electric motor-actuators is activated and the other of said first and second portions of said plurality of electric motor-actuators is deactivated.

A method for controlling a plurality of electric motor-actuators associated with an aircraft wheel brake, the aircraft brake system including a plurality of electric motor-actuators, said plurality of electric motor-actuators including a first portion of said plurality of electric motor-actuators and a second portion of said plurality of electric motor-actuators, said plurality of electric motor-actuators being operatively connected to an aircraft wheel brake to actuate the aircraft wheel brake, an electronic brake actuation controller operatively connected to said plurality of electric motor-actuators and configured to control the operation of said first and second portions of said plurality of electric motor-actuators, and a brake system control unit configured to receive a brake pedal command for a commanded braking force, said brake system control unit being connected to said electronic brake actuation controller and configured to control said electronic brake actuation controller, such that one of said first and second portions of said plurality of electric motor-actuators is activated and the other of said first and second portions of said plurality of electric motor-actuators is deactivated during an inhibited braking mode, the method comprising:

• generating a brake pedal command for a commanded braking force for an aircraft wheel brake;
• receiving said brake pedal command and controlling said electronic brake actuation controller such that one of said first and second portions of said plurality of electric motor-actuators is activated and the other of said first and second portions of said plurality of electric motor-actuators is deactivated during an inhibited braking mode;
• and
• generating a braking force of the activated one of said first and second portions of said plurality of electric motor-actuators greater than the commanded braking force of the brake pedal command to compensate for said other of said first and second portions of said plurality of electric motor-actuators being deactivated during said inhibited braking mode.