A brake assembly may comprise a brake stack including a plurality of rotors and a plurality of stators. A piston assembly may be configured to apply a force to the brake stack. A brake control valve may be mounted to the piston assembly and fluidly coupled to a fluid inlet of the piston assembly.

A brake assembly may comprise a brake stack including a plurality of rotors and a plurality of stators. A piston assembly may be configured to apply a force to the brake stack. A brake control valve may be mounted to the piston assembly and fluidly coupled to a fluid inlet of the piston assembly.

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.

A braking system includes a brake stack; a first brake cavity operably coupled to the brake stack, the first brake cavity including a first plurality of brake actuators; a second brake cavity operably coupled to the brake stack, the second brake cavity including a second plurality of brake actuators; and a brake control module, the brake control module being configured to activate either the first plurality of brake actuators or both the first plurality of brake actuators and the second plurality of brake actuators in response to an input brake load.

A braking system includes a brake stack; a first brake cavity operably coupled to the brake stack, the first brake cavity including a first plurality of brake actuators; a second brake cavity operably coupled to the brake stack, the second brake cavity including a second plurality of brake actuators; and a brake control module, the brake control module being configured to activate either the first plurality of brake actuators or both the first plurality of brake actuators and the second plurality of brake actuators in response to an input brake load.

An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.

An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.

The present disclosure provides a skid control system that includes a brake control device configured to convert a current command value to create a braking pressure, wherein the braking pressure is applied to a hydraulically actuated brake and/or an electrically actuated brake. A deceleration control unit receives a filtered wheel speed value and/or a filtered wheel acceleration value from the wheel assembly. A brake control algorithm unit retrieves a noise threshold value corresponding with the at least one of the filtered wheel speed value or the filtered wheel acceleration value. A pressure control unit receives a feedback pressure from the hydraulically actuated brake and/or an electrically actuated brake, wherein the pressure control unit either increases or decreases the current command value in response to a difference between the pressure command value and a feedback pressure being either less than or greater than the noise threshold value.

The present disclosure provides a skid control system that includes a brake control device configured to convert a current command value to create a braking pressure, wherein the braking pressure is applied to a hydraulically actuated brake and/or an electrically actuated brake. A deceleration control unit receives a filtered wheel speed value and/or a filtered wheel acceleration value from the wheel assembly. A brake control algorithm unit retrieves a noise threshold value corresponding with the at least one of the filtered wheel speed value or the filtered wheel acceleration value. A pressure control unit receives a feedback pressure from the hydraulically actuated brake and/or an electrically actuated brake, wherein the pressure control unit either increases or decreases the current command value in response to a difference between the pressure command value and a feedback pressure being either less than or greater than the noise threshold value.