Abstract: An aircraft electric brake actuator assembly includes an actuator housing, a motor housing, an actuator, an electric motor, and an actuator brake. The actuator housing is configured to be mounted on an aircraft landing gear. The motor housing is coupled to the actuator housing and is removable therefrom. The motor housing is also accessible when the actuator housing is mounted on an aircraft. The electric motor is disposed within the motor housing and is coupled to the actuator. The actuator brake is disposed within the motor housing and is removably coupled to the motor.

Abstract: A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined. When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.

Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.

Abstract: In some examples, a system includes a brake rotor, a brake armature configured to engage with the brake rotor to substantially fix a rotational position of the brake rotor relative to the brake armature, and a mechanism mechanically coupled to the brake armature. The brake armature may be configured to rotate in a first rotational direction and a second rotational direction substantially opposite the first rotational direction. The mechanism may be configured to maintain the brake armature in a fixed rotational position when a torque applied to the brake armature in a second rotational direction is less than or equal to a threshold torque value. The mechanism also may be configured to permit rotation of the brake armature in the second rotational direction when torque on the brake armature in the second rotational direction exceeds the threshold torque value.

Abstract: In some examples, a system includes a brake rotor, a brake armature configured to engage with the brake rotor to substantially fix a rotational position of the brake rotor relative to the brake armature, and a mechanism mechanically coupled to the brake armature. The brake armature may be configured to rotate in a first rotational direction and a second rotational direction substantially opposite the first rotational direction. The mechanism may be configured to maintain the brake armature in a fixed rotational position when a torque applied to the brake armature in a second rotational direction is less than or equal to a threshold torque value. The mechanism also may be configured to permit rotation of the brake armature in the second rotational direction when torque on the brake armature in the second rotational direction exceeds the threshold torque value.

Abstract: An aircraft electric brake actuator assembly includes an actuator housing, a motor housing, an actuator, an electric motor, and an actuator brake. The actuator housing is configured to be mounted on an aircraft landing gear. The motor housing is coupled to the actuator housing and is removable therefrom. The motor housing is also accessible when the actuator housing is mounted on an aircraft. The electric motor is disposed within the motor housing and is coupled to the actuator. The actuator brake is disposed within the motor housing and is removably coupled to the motor.

Abstract: A fault-tolerant position feedback filter may be used in an actuation control system to limit the authority of a first position signal, should the first position signal become erroneous, and thereby prevent a postulated runaway condition of an acuator. The filter includes a difference function, a limited integrator, and a summer. The difference function supplies a first position error signal representative of a mathematical difference between a first position signal and a combined position signal. The limited integrator supplies an integrated position error signal that is limited in magnitude to a predetermined limit. The summer supplies the combined position error signal that is representative of a mathematical sum of the integrated position error signal and the second position signal.

Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: An electromechanical actuator test system includes an inertia simulator, a first load actuator, a second load actuator, and a test system control. The inertia simulator simulates the inertia of at least a portion of a system that is moved by a test actuator. The first load actuator supplies a first load to the inertia simulator to simulate at least one or more dynamic system loads, and the second load actuator supplies a second load to the inertia simulator to simulate at least one or more steady-state system loads. The test system control supplies the first actuator commands and the second actuator commands.

Abstract: A fault-tolerant position feedback filter may be used in an actuation control system to limit the authority of a first position signal, should the first position signal become erroneous, and thereby prevent a postulated runaway condition of an acuator. The filter includes a difference function, a limited integrator, and a summer The difference function is coupled to receive a first position signal and a combined position error signal and is operable to supply a first position error signal representative of a mathematical difference between the first position signal and the combined position signal. The limited integrator is coupled to receive the first position error signal and operable to supply an integrated position error signal that is limited in magnitude to a predetermined limit. The summer is coupled to receive the integrated position error signal and a second position signal and is operable to supply the combined position error signal.

Abstract: A portable electromechanical actuator test system includes a command generator, a rechargeable battery system, an electronic power supply, and a power controller, all disposed within a portable housing. The command generator at least selectively supplies test actuator commands to, and receives operational feedback signals from, an electromechanical actuator (EMA) controller. The rechargeable battery system and electronic power supply each supply electric power. The power controller is coupled to receive the electric power supplied from both the rechargeable battery system and the electronic power supply, and is operable to at least selectively supply electric power to the EMA controller and to an EMA that is controlled by the EMA controller.

Abstract: An electromechanical actuator test system includes an inertia simulator, a first load actuator, a second load actuator, and a test system control. The inertia simulator simulates the inertia of at least a portion of a system that is moved by a test actuator. The first load actuator supplies a first load to the inertia simulator to simulate at least one or more dynamic system loads, and the second load actuator supplies a second load to the inertia simulator to simulate at least one or more steady-state system loads. The test system control supplies the first actuator commands and the second actuator commands.