A system for performing frequency response health monitoring of a servo valve prior to flight of an aircraft may comprise: the servo valve; and a brake controller in electrical communication with the servo valve, the brake controller configured to: determine the brake controller is powering up, supply a variable current to the servo valve to perform the frequency response health monitoring to the servo valve in response to determining the brake controller is powering up, and determine a health status of the servo valve based on the frequency response health monitoring.

A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

A method of parking an aircraft is disclosed including flight crew pedal braking to cause a brake force to be applied to the aircraft wheel brakes to slow the aircraft to a stationary state in which it is ready to be parked. Flight crew then activate a parking brake device and then release the pedal braking. An electronic control device, forming part of the aircraft’s braking system for example, automatically intervenes, following the manual release of the pedal braking, to cause a brake force to continue to be applied to the wheels. This may be until sufficient brake force is applied, as a result of the activation of the parking brake device, to hold the aircraft in its parked state or may be for a predetermined period of time, say, ten seconds.

A system and method are provided for continuous monitoring and controlling of aircraft braking that can reduce brake wear and aircraft operating costs through the retention of carbon brake powder from the brakes or addition of carbon powder in a device mounted with respect to the brake disk stack. The use of carbon powder reduces brake wear by providing small particles between the brake disks, acting as a buffer between the brake disks when the brake stack is clamped together. Moreover, when carbon powder or small particles are used at application, such use reduces the roughness of the carbon surface and reduces the number of large particles from braking off the carbon surface, thereby reducing brake wear. Adaptive or selective braking may be used in conjunction with carbon powder to further reduce carbon brake wear.

A braking system for an aircraft is disclosed herein. The braking system may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem and a hydraulic braking subsystem. During a flight, one of the electric braking subsystem and the hydraulic braking subsystem may be selected as a primary braking system. The braking system may be configured to command braking of a brake assembly by the hydraulic braking subsystem and the electric braking subsystem during an RTO phase of the flight. The braking system may be configured to command braking of a brake assembly by a secondary braking system in response to a failure of a primary braking system during the RTO phase of the flight.

A braking system for an aircraft may comprise: a brake assembly including a brake stack; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly; and a controller in operable communication with the electric braking subsystem, the controller configured to perform a wear depth measurement process, the wear depth measurement process comprising: determine a reference position of the electric brake actuator; command the electric brake actuator to extend toward the brake stack; receive a force measurement from a load cell in response to the electric brake actuator contacting the brake stack; determine a linear travel distance of the electric brake actuator based on an end position determined from the force measurement; and determine a wear depth based on calculating a difference between the linear travel distance and a prior linear travel distance of the electric brake actuator.

An aircraft includes a brake lever for receiving a pilot braking input as a lever travel of the brake lever, a braking wheel operatively coupled with the brake lever to brake the aircraft based on the lever travel, a brake actuator operatively coupled with the braking wheel to apply a braking force in response to a braking pressure provided to the brake actuator, and a brake pressure circuit. The brake pressure circuit is configured for: estimating a maximum braking pressure above which the braking wheel will skid with respect to a ground surface; scaling a lever gain of the brake lever to command the maximum braking pressure at a full travel of the brake lever such that a remaining brake lever travel indicates the amount of braking capability remaining for the aircraft; and braking the braking wheel based on the lever gain and the lever travel.

An aircraft includes a brake lever for receiving a pilot braking input as a lever travel of the brake lever, a braking wheel operatively coupled with the brake lever to brake the aircraft based on the lever travel, a brake actuator operatively coupled with the braking wheel to apply a braking force in response to a braking pressure provided to the brake actuator, and a brake pressure circuit. The brake pressure circuit is configured for: estimating a maximum braking pressure above which the braking wheel will skid with respect to a ground surface; scaling a lever gain of the brake lever to command the maximum braking pressure at a full travel of the brake lever such that a remaining brake lever travel indicates the amount of braking capability remaining for the aircraft; and braking the braking wheel based on the lever gain and the lever travel.

An aircraft automatic braking system, comprising: a first functional module arranged in order to implement a state machine that includes a first branch comprising first states corresponding to a landing of the aircraft, a second branch comprising second states corresponding to a rejected take-off of the aircraft, and transitions, the first states, the second states and the transitions being defined independently of deceleration rates; a second functional module arranged in order to define a target deceleration of the aircraft at least on the basis of the deceleration rates and a current state of the state machine; and a third functional module arranged in order to define, at least on the basis of the current state and the target deceleration, an automatic braking command in order to control actuators of wheel brakes of the aircraft.

A system for performing frequency response health monitoring of a servo valve prior to flight of an aircraft may comprise: the servo valve; and a brake controller in electrical communication with the servo valve, the brake controller configured to: determine the brake controller is powering up, supply a variable current to the servo valve to perform the frequency response health monitoring to the servo valve in response to determining the brake controller is powering up, and determine a health status of the servo valve based on the frequency response health monitoring.