An apparatus for controlling braking of a vehicle having a plurality of brake-packs. The apparatus includes a controller configured to receive a first plurality of input values having a first scatter value; calculate an adjustment factor for each brake-pack based on the received first plurality of input values; output a control signal to cause each brake-pack of the plurality of brake-packs to be applied at a pressure based on the adjustment factor calculated for that brake-pack; and receive a second plurality of input values having a second scatter value. Each input value relates to a different one of the plurality of brake-packs. The adjustment factors are calculated such that the second scatter value is less than or equal to the first scatter value.

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.

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.

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

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 disc stack. The use of carbon powder reduces brake wear by providing small particles between the brake discs, acting as a buffer between the brake discs 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 system for detecting aircraft brake failure using retract braking may comprise a landing gear including a wheel, a brake coupled to the wheel, and a wheel sensor coupled to the wheel. A brake controller may be coupled to the brake and the wheel sensor. The brake controller may be configured to receive a begin retract braking signal, command the brake to apply a braking force to the wheel, calculate a wheel speed characteristic using data from the wheel sensor, and determine whether the wheel speed characteristic indicates a failure of the brake.

A method for measurement of contact maintaining control valve current for a hydraulic actuator may comprise sending, by a brake controller, a current signal to an electromechanical valve assembly, receiving, by the brake controller, a pressure feedback signal, increasing, by the brake controller, a value of the current signal, and determining, by the brake controller, a contact current value based upon the pressure feedback signal.

An antiskid controller for controlling braking operation of a wheel of a vehicle based on an output signal provided by a wheel speed sensor coupled to the wheel may comprise a delay toggle, a switch logic for switching between an initial rate and a running rate, and a linear control used for calculating an antiskid correction signal, wherein the linear control receives one of the initial rate and the running rate, depending on a state of the switch logic. The linear control receives the initial rate upon initialization of the antiskid controller. The linear control receives the running rate after a predetermined duration or after the linear control has converged on a desired solution.