Abstract: An electromechanical brake (E-brake) system including a first brake control unit, a second brake control unit, a first electromechanical brake actuator controller, a second electromechanical brake actuator controller, a first wheel and brake assembly, and a second wheel and brake assembly. The first electromechanical brake actuator controller includes a first monitor circuit communicatively coupled to the first brake control unit and the second brake control unit. The second electromechanical brake actuator controller includes a second monitor circuit communicatively coupled to the first brake control unit and the second brake control unit. The first wheel and brake assembly is communicatively coupled to the first electromechanical brake actuator controller and the second electromechanical brake actuator controller. The second wheel and brake assembly is communicatively coupled to the first electromechanical brake actuator controller and the second electromechanical brake actuator controller.

Abstract: An improved motor velocity control selection mechanism. An electromechanical brake (E-brake) system includes a brake control unit, an electromechanical brake actuator controller coupled to the brake control unit, and at least one brake coupled to the electromechanical brake actuator controller. The electromechanical brake actuator controller includes a velocity controller. The velocity controller is configured to command a braking force via an electromechanical brake actuator to the at least one brake based upon whether a command to go to at least one of zero torque point (ZTP) or running clearance point (RCP) has been received and at least one of a force error, a ZTP flag, and a measured electric brake actuator position.

Abstract: A brake system is disclosed herein and includes a brake mode selection mechanism configured to provide a desired braking command, an antiskid control mechanism configured to provide an antiskid control braking command, and a brake executive mechanism. The brake executive mechanism is configured to determine whether the antiskid control braking command is less than the desired braking command; responsive to the antiskid control braking command being less than the desired braking command, send a first command to implement the antiskid control braking command via an antiskid controller configured to control a pressure or a force applied to a brake assembly; and, responsive to the desired braking command being less than the antiskid control braking command, send a second command to implement the desired braking command via a desired braking controller configured to control the pressure or the force applied to the brake assembly.

Abstract: A brake system is disclosed herein. The brake system includes an electromechanical brake actuator, a pressure plate, an end plate, a ball screw positioned between the electromechanical brake actuator and the pressure plate, and a plurality of rotating discs positioned between the pressure plate and the end plate. The electromechanical brake actuator is configured to extend the ball screw to a ball screw position to apply a requested force to the pressure plate towards the end plate thereby forcing the plurality of rotating discs together in an axial direction in order to reduce a rotational speed of the plurality of rotating discs. The ball screw is extended by the electromechanical brake actuator to the ball screw position based on a worn state of the plurality of rotating discs and a stiffness curve for the electromechanical brake actuator that represents force versus ball screw position for the worn state.

Abstract: A method for detecting a fault within a brake mechanism on an aircraft is disclosed. In various embodiments, the method includes activating, by a brake control unit, the brake mechanism; receiving, by the brake control unit, a wheel speed data for a wheel associated with the brake mechanism; determining, by the brake control unit, a wheel speed characteristic for the wheel associated with the brake mechanism; and detecting, by the brake control unit, whether the brake mechanism is faulty based on a comparison of the wheel speed characteristic and a wheel speed deceleration database.

Abstract: A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.

Abstract: A brake assembly coupled to a wheel is disclosed herein. The brake assembly includes a plurality of stator disks, a plurality of rotor disks interleaved with the plurality of stator disks and configured to apply a braking force to the wheel, a pressure plate disposed adjacent a rotor disk of the plurality of rotor disks, a first electric brake actuator disposed adjacent the pressure plate and configured to apply the braking force to the pressure plate, the first electric brake actuator including a parking brake mechanism, and a second electric brake actuator disposed adjacent the pressure plate and configured to apply the braking force to the pressure plate.

Abstract: A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.

Abstract: A braking system is disclosed. In various embodiments, the braking system includes a brake stack; an actuator configured to apply a compressive load to the brake stack; a servo valve coupled to a power source and to the actuator; and a brake control unit configured to operate the servo valve at a current ramp rate in response to a pedal deflection signal, wherein the current ramp rate is determined via a relationship between the current ramp rate and a brake pressure command signal.

Abstract: A method for detecting a fault within a brake mechanism on an aircraft is disclosed. In various embodiments, the method includes activating, by a brake control unit, the brake mechanism; receiving, by the brake control unit, a wheel speed data for a wheel associated with the brake mechanism; determining, by the brake control unit, a wheel speed characteristic for the wheel associated with the brake mechanism; and detecting, by the brake control unit, whether the brake mechanism is faulty based on a comparison of the wheel speed characteristic and a wheel speed deceleration database.

Abstract: A braking system is disclosed. In various embodiments, the braking system includes a brake stack; an actuator configured to apply a compressive load to the brake stack; a servo valve coupled to a power source and to the actuator; and a brake control unit configured to operate the servo valve at a current ramp rate in response to a pedal deflection signal, wherein the current ramp rate is determined via a relationship between the current ramp rate and a brake pressure command signal.