A brake system is disclosed. The brake system includes a brake stack having a stack closure pressure, a force member positioned within a cylinder, a valve configured to control fluid pressure of the brake system, and one or more pressure transducers that generate a proportional electrical signal representative of the fluid pressure within the cylinder. The brake system also includes one or more processors in electronic communication with the valve, the one or more pressure transducers, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the stack closure pressure of the brake stack.

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.

A system for multi-mode autobrake control may comprise a wheel speed sensor and a BCU electrically coupled to the wheel speed sensor. A tangible, non-transitory memory may be configured to communicate with the BCU and may have instructions stored thereon that, in response to execution by the BCU, cause the BCU to perform operations comprising receiving a wheel speed signal from the wheel speed sensor, inputting the wheel speed signal into an antiskid filter and a nominal filter, calculating an estimated aircraft deceleration rate, and determining an autobrake pressure command based on the estimated aircraft deceleration rate.

A system for multi-mode autobrake control may comprise a wheel speed sensor and a BCU electrically coupled to the wheel speed sensor. A tangible, non-transitory memory may be configured to communicate with the BCU and may have instructions stored thereon that, in response to execution by the BCU, cause the BCU to perform operations comprising receiving a wheel speed signal from the wheel speed sensor, inputting the wheel speed signal into an antiskid filter and a nominal filter, calculating an estimated aircraft deceleration rate, and determining an autobrake pressure command based on the estimated aircraft deceleration rate.

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.

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.

Aircraft braking system architecture comprising: a brake comprising electromechanical actuators (1, 2); a principal control channel (6) and an alternative control channel (7) comprising electrical components that are at least partly different and adapted to provide respectively a principal braking control function and an alternative braking control function that are at least partly different; power modules (15, 16) comprising electrical components that are at least partly different and adapted to generate electrical power supply currents (I1, I2) on the basis of principal control signals or alternative control signals; a surveillance unit (8) adapted to ensure that in normal operation the principal control signals are used and that in the event of a fault the alternative control signals are used to generate the electrical power supply currents.

Aircraft braking system architecture comprising: a brake comprising electromechanical actuators (1, 2); a principal control channel (6) and an alternative control channel (7) comprising electrical components that are at least partly different and adapted to provide respectively a principal braking control function and an alternative braking control function that are at least partly different; power modules (15, 16) comprising electrical components that are at least partly different and adapted to generate electrical power supply currents (I1, I2) on the basis of principal control signals or alternative control signals; a surveillance unit (8) adapted to ensure that in normal operation the principal control signals are used and that in the event of a fault the alternative control signals are used to generate the electrical power supply currents.

Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage.