Abstract: A brake wear component is disclosed. In various embodiments, the component includes a linear position sensor disposed within a housing and configured to contact a pressure plate of a brake mechanism; a bias element coupled to the linear position sensor and configured to bias the linear position sensor a distance away from the pressure plate during a deactivated state; and an actuating mechanism coupled to the linear position sensor and configured to translate the linear position sensor toward the pressure plate during an activated state.

Abstract: Systems and methods for shutoff valve control are provided. The system may receive a first hardware logic input, a second hardware logic input, and a weight-on-wheels (WOW) status wherein each of the first hardware logic input, the second hardware logic input, and the WOW status report a binary true or a false. The system may open the shutoff valve when each of the first hardware logic input, the second hardware logic input, and the WOW status report true. The system may close the shutoff valve when any of the first hardware logic input, the second hardware logic input, and the WOW status report false.

Abstract: A method of performing prognostics on a hydraulic brake system of an aircraft may include determining, during primary braking mode and by a hydraulic brake controller, a first status of a first brake pressure sensor adjacent a brake assembly. The method may also include, in response to determining that the first status of the first brake pressure sensor is valid, determining, during park braking mode and by the hydraulic brake controller, a second status of a second brake pressure sensor adjacent a park valve assembly. In response to determining that the first status of the first brake pressure sensor is degraded, the method may include outputting, by the hydraulic brake controller, at least one of an inspection indicator and a maintenance indicator.

Abstract: A brake control system (BCS) may comprise a first controller, a second controller in electronic communication with the first controller, and a valve comprising a first coil and a second coil. The first controller may be configured to actuate the valve via the first coil. The second controller may be configured to actuate the valve via the second coil. The first controller may be configured to disable the second controller to take over control of the valve.

Abstract: Systems and methods for aircraft braking are disclosed. The systems and methods may comprise a control mode executive configured to receive a pedal input and calculate a gear deceleration command comprising a desired deceleration rate based on the pedal input; a pedal deceleration controller in electronic communication with the control mode executive configured to receive the gear deceleration command from the control mode executive and calculate a gear pedal command based on at least one of the gear deceleration command and a deceleration feedback; and a pedal executive in electronic communication with the pedal deceleration controller configured to receive the gear pedal command, and generate a pedal braking command based on the gear pedal command.

Abstract: Braking control systems and methods, such as for an aircraft, use a dump valve to rapidly decrease hydraulic pressure applied to a brake actuator during a wheel skid condition. In response to the wheel speed recovering, the dump valve is commanded closed and the brake control system returns to normal braking. The dump valve and a servo-valve may work harmoniously for locked wheel brake control.

Abstract: A system for performing brake testing during flight of an aircraft, in accordance with various embodiments, includes a landing gear having at least one wheel assembly. The system further includes a brake configured to apply a braking force to the at least one wheel assembly. The system further includes a brake controller configured to determine a landing event indicating that the aircraft is approaching a landing, control the brake to apply a testing brake force to the at least one wheel assembly in response to determining the landing event, and determine an operational status of the brake based on the testing brake force.

Abstract: A wheel speed sensor may comprise a magnet; an induction coil coupled to the magnet; a rotor comprising a plurality of teeth, wherein the magnet is disposed proximate the plurality of teeth; a gear system coupled to the rotor comprising an initial gear, wherein the initial gear may be configured to be coupled to a wheel and configured to rotate at a speed equal to a wheel rotational speed of the wheel. The gear system may be configured to cause a rotor rotational speed of the rotor to be greater than the wheel rotational speed in response to the wheel rotating.

Abstract: Systems and methods for aircraft autobraking are disclosed. The systems and methods may allow for autobraking in both manned and autonomous aircrafts, and may assist in maintaining a desired course during autobraking. The systems and methods may include an aircraft control mode executive module configured to receive manual and/or autonomous brake signal inputs and deceleration signal inputs. The systems and methods may also include various modules configured to aid in calculating, transmitting, and executing pedal brake commands on a braking system, such as, an autobrake controller, a pedal balance controller, an autobrake pedal executive module, a pedal executive module, and/or a pedal braking controller.

Abstract: Braking control systems and methods, such as for an aircraft, use a dump valve to rapidly decrease hydraulic pressure applied to a brake actuator during a wheel skid condition. In response to the wheel speed recovering, the dump valve is commanded closed and the brake control system returns to normal braking. The dump valve and a servo-valve may work harmoniously for locked wheel brake control.

Abstract: A brake control system may comprise an inertial sensor coupled to an axle and configured to measure a linear acceleration of the axle and an antiskid control (ASK) in electronic communication with the inertial sensor, wherein at least one of the inertial sensor or the ASK calculate a linear velocity of the axle based on the linear acceleration, and the ASK uses the linear velocity to calculate a wheel slip speed.

Abstract: Braking control systems, such as for an aircraft, use a hydraulic failure isolation valve intermediate an accumulator power source and a dual valve assembly for mechanical operation when a hydraulic power source experiences a disruption.

Abstract: Braking control systems and methods, such as for an aircraft, use a first pressure sensor and a second pressure sensor from a non-primary braking system to validate the first pressure sensor. In response to the first pressure sensor being validated, a health status of a servo valve is monitored based on predetermined characteristics about the servo valve, including electrical current input into the servo valve and hydraulic pressure output from the servo valve.

Abstract: A method for controlling brakes includes receiving, by a controller, a first wheel speed from a first wheel speed sensor of a first wheel arrangement, receiving, by the controller, a second wheel speed from a second wheel speed sensor of a second wheel arrangement, calculating, by the controller, a pressure correction, and adjusting, by the controller, a pressure command for at least one of the first wheel arrangement and the second wheel arrangement.

Abstract: A method of performing prognostics on a hydraulic brake system of an aircraft may include determining, during primary braking mode and by a hydraulic brake controller, a first status of a first brake pressure sensor adjacent a brake assembly. The method may also include, in response to determining that the first status of the first brake pressure sensor is valid, determining, during park braking mode and by the hydraulic brake controller, a second status of a second brake pressure sensor adjacent a park valve assembly. In response to determining that the first status of the first brake pressure sensor is degraded, the method may include outputting, by the hydraulic brake controller, at least one of an inspection indicator and a maintenance indicator.

Abstract: A BCU for determining a health status of a LRU having a coil includes a non-transitory memory configured to store instructions and a controller coupled to the non-transitory memory. The controller is designed to receive a temperature from a temperature sensor, to receive a direct current (DC) voltage that is applied to the coil of the LRU, and to receive a detected current corresponding to an amount of current flowing through the coil. The controller is further designed to determine a calculated resistance of the coil based on the detected current and the DC voltage and to determine a compensated resistance of the coil based on the temperature and the calculated resistance of the coil. The controller is further designed to determine the health status of the LRU by comparing the compensated resistance of the coil to a nominal resistance of the coil.

Abstract: Braking control systems and methods, such as for an aircraft, use a first pressure sensor and a second pressure sensor from a non-primary braking system to validate the first pressure sensor. In response to the first pressure sensor being validated, a health status of a servo valve is monitored based on predetermined characteristics about the servo valve, including electrical current input into the servo valve and hydraulic pressure output from the servo valve.

Abstract: Braking control systems, such as for an aircraft, use a hydraulic failure isolation valve intermediate an accumulator power source and a dual valve assembly for mechanical operation when a hydraulic power source experiences a disruption.

Abstract: Systems and methods for aircraft braking are disclosed. The systems and methods may comprise a control mode executive configured to receive a pedal input and calculate a gear deceleration command comprising a desired deceleration rate based on the pedal input; a pedal deceleration controller in electronic communication with the control mode executive configured to receive the gear deceleration command from the control mode executive and calculate a gear pedal command based on at least one of the gear deceleration command and a deceleration feedback; and a pedal executive in electronic communication with the pedal deceleration controller configured to receive the gear pedal command, and generate a pedal braking command based on the gear pedal command.

Abstract: A method for controlling brakes may comprise receiving, by a controller, a yaw rate from an inertial sensor, calculating, by the controller, a force correction, calculating, by the controller, a pressure correction, and adjusting, by the controller, a pressure command for a brake control device.