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 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 brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.

There is provided a pivot turn load alleviation (PTLA) brake system for alleviating structural loads on a pivoting main landing gear of an aircraft in a pivot turn maneuver. The PTLA brake system includes a brake control system operatively coupled to at least two main landing gear, each having two or more wheels. The PTLA brake system further includes a PTLA brake inhibit subsystem coupled to the brake control system. The subsystem inhibits braking of one or more of the two or more wheels of the pivoting main landing gear, in the pivot turn maneuver, so that at least one wheel of the two or more wheels is in an unbraked state, and a remaining number of the two or more wheels are in a braked state. The PTLA brake system alleviates structural loads, and reduces wear on the at least one wheel that is in the unbraked state.

There is provided a pivot turn load alleviation (PTLA) brake system for alleviating structural loads on a pivoting main landing gear of an aircraft in a pivot turn maneuver. The PTLA brake system includes a brake control system operatively coupled to at least two main landing gear, each having two or more wheels. The PTLA brake system further includes a PTLA brake inhibit subsystem coupled to the brake control system. The subsystem inhibits braking of one or more of the two or more wheels of the pivoting main landing gear, in the pivot turn maneuver, so that at least one wheel of the two or more wheels is in an unbraked state, and a remaining number of the two or more wheels are in a braked state. The PTLA brake system alleviates structural loads, and reduces wear on the at least one wheel that is in the unbraked state.

An aircraft system for an aircraft having a controller configured to determine, based on a criterion indicative of an aircraft condition or a runway condition, a maximum braking level able to be applied to a brake of the aircraft in an emergency braking mode.

An aircraft brake control system accommodates desired yaw for steering, while substantially eliminating undesired yaw. The system assesses brake command signals from the pilot, signals corresponding to aircraft parameters, and signals based on brake control parameters, and determines therefrom an amount of yaw desired by the pilot. The instantaneous yaw rate is monitored and compared to the desired yaw rate. An error signal corresponding to the difference between instantaneous and actual yaw rates is calculated and that error signal is employed to modify a braking differential between right and left brakes to eliminate or substantially reduce the undesired yaw.

An aircraft brake control system accommodates desired yaw for steering, while substantially eliminating undesired yaw. The system assesses brake command signals from the pilot, signals corresponding to aircraft parameters, and signals based on brake control parameters, and determines therefrom an amount of yaw desired by the pilot. The instantaneous yaw rate is monitored and compared to the desired yaw rate. An error signal corresponding to the difference between instantaneous and actual yaw rates is calculated and that error signal is employed to modify a braking differential between right and left brakes to eliminate or substantially reduce the undesired yaw.