Abstract: A method of detecting a failure of a brake actuator is provided. The method includes monitoring an angular position of a motor controlling the brake actuator. Also included is monitoring a linear position of a linear translation arrangement of the brake actuator, wherein the linear position of the linear translation arrangement is controlled by a gear assembly in communication with the motor and the linear translation arrangement. Further included is comparing the linear position of the linear translation arrangement with the angular position of the motor. Yet further included is determining whether the linear position of the linear translation arrangement is within a predetermined range of linear positions corresponding to a plurality of angular positions.

Abstract: Systems and methods for reducing the speed of an aircraft are disclosed herein. An electronic brake control system may include a first braked wheel of a landing gear system, a brake pedal electronically coupled to the first braked wheel, and a first actuator. The first actuator may be configured to deliver a scalable clamping force on the first braked wheel via a brake stack. The first actuator may be configured to deliver an emergency maximum clamping force on the first braked wheel in response to the electronic brake control unit being in an emergency condition braking mode and a signal being received proportional to the brake pedal displacement. The emergency maximum clamping force results in the first actuator being driven in an overdriven state.

Abstract: Systems and methods for indicating conditions for the appropriate inflation and/or deflation of tires are disclosed. Some systems and methods include measuring a variable affecting the internal gas temperature of a tire, calculating by the processor an estimated internal gas temperature of a tire, and determining whether a tire is appropriate to inflate and/or deflate.

Abstract: Systems and methods for identification of brake suppliers and vehicle models based on electrical resistance of the brake control unit are disclosed herein. Based on calculated values, both the brake supplier and model of vehicle can be determined.

Abstract: Described herein is a system and method to enable braking system operation independent of conventional aircraft signals, such as those tied to the hibernation commands. Stated another way, the present disclosure relates to the enablement of a braking system in response to an initiation signal. In this way, the crew has the ability to force the braking system out of a hibernation mode into an “emergency type” braking mode if desired. The concepts described herein may be applicable to an electric braking system and to a hydraulic braking system.

Abstract: A method of determining a status of a brake actuator of a brake assembly includes sensing one or more activations of the brake actuator, storing the one or more activations in a computer memory, sensing a depth of a parameter of the one or more activations, storing the depth of the parameter of the one or more activations in the computer memory, and determining a status of the brake actuator based on the depth of the parameter of the one or more activations.

Abstract: A brake measurement system that utilize angular and/or linear displacement sensors to measure movement of a member operatively coupled to a movable member of a brake, wherein displacement of the movable member of the brake is indicative of brake wear. The system can include a twisted spline member operatively coupled to a moveable member of a brake assembly, and an angular displacement sensor operatively coupled to the twisted spline member. Movement of the moveable member is converted by the twisted spline member into an angular displacement sensed by the angular displacement sensor.

Abstract: An assembly mounted to a surface, the assembly includes a component; and a plurality of fingers connected to the component and in contact with the surface to provide a low impedance path between the component and the surface.

Abstract: A method includes measuring a brake temperature of an aircraft brake using a sensor; determining a brake heat sink mass of the aircraft brake using a wear measuring device; and calculating a turnaround threshold based upon the measured brake temperature and the determined brake heat sink mass.

Abstract: A safety analysis zone of an aircraft includes a first aircraft component. Also included is a wired arrangement disposed proximate the first aircraft component for monitoring and controlling a second aircraft component. Further included is a wireless system for monitoring and controlling the second aircraft component.

Abstract: An assembly mounted to a surface, the assembly includes a component; and a plurality of fingers connected to the component and in contact with the surface to provide a low impedance path between the component and the surface.

Abstract: A method of detecting a failure of a brake actuator is provided. The method includes monitoring an angular position of a motor controlling the brake actuator. Also included is monitoring a linear position of a linear translation arrangement of the brake actuator, wherein the linear position of the linear translation arrangement is controlled by a gear assembly in communication with the motor and the linear translation arrangement. Further included is comparing the linear position of the linear translation arrangement with the angular position of the motor. Yet further included is determining whether the linear position of the linear translation arrangement is within a predetermined range of linear positions corresponding to a plurality of angular positions.

Abstract: A method of determining a status of a brake actuator of a brake assembly includes sensing one or more activations of the brake actuator, storing the one or more activations in a computer memory, sensing a depth of a parameter of the one or more activations, storing the depth of the parameter of the one or more activations in the computer memory, and determining a status of the brake actuator based on the depth of the parameter of the one or more activations.

Abstract: A brake measurement system comprising a measurement mechanism for measuring brake wear operatively coupled to a moveable member of a brake assembly is provided. The system further includes a displacement sensor and a visual indicator. The displacement sensor is operatively coupled to the measurement mechanism, wherein movement of the moveable member is converted by the measurement mechanism into a displacement sensed by the displacement sensor. The visual indicator is operatively connected to the measurement mechanism, wherein the visual indicator displays the movement of the moveable member and consequently the wear of the brake stack at a point on the exterior of an aircraft brake housing for inspection.

Abstract: A brake measurement system comprising a measurement mechanism for measuring brake wear operatively coupled to a moveable member of a brake assembly is provided. The system further includes a displacement sensor and a visual indicator. The displacement sensor is operatively coupled to the measurement mechanism, wherein movement of the moveable member is converted by the measurement mechanism into a displacement sensed by the displacement sensor. The visual indicator is operatively connected to the measurement mechanism, wherein the visual indicator displays the movement of the moveable member and consequently the wear of the brake stack at a point on the exterior of an aircraft brake housing for inspection.

Abstract: A brake measurement system that utilize angular and/or linear displacement sensors to measure movement of a member operatively coupled to a movable member of a brake, wherein displacement of the movable member of the brake is indicative of brake wear. The system can include a twisted spline member operatively coupled to a moveable member of a brake assembly, and an angular displacement sensor operatively coupled to the twisted spline member. Movement of the moveable member is converted by the twisted spline member into an angular displacement sensed by the angular displacement sensor.

Abstract: A parking brake monitor and adjustment control system controls parking brake operation of an electromechanically actuated brake system which applies a parking brake force to a wheel. The system includes a monitor circuit for producing an output signal which intermittently causes the brake system to readjust the parking brake force applied to the wheel.

Abstract: A parking brake monitor and adjustment control system controls parking brake operation of an electromechanically actuated brake system which applies a parking brake force to a wheel. The system includes a monitor circuit for producing an output signal which intermittently causes the brake system to readjust the parking brake force applied to the wheel.