Aircraft electric braking system

Abstract

An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC; wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).

Description

technical field

[0001] The invention relates to an electric braking system for an aircraft. Background technique

[0002] Electric systems are gradually replacing hydraulic systems on many commercial and military aircraft. Current "brake-by-wire" aircraft systems may have an overall centralized architecture where pilot inputs are interpreted and command and monitoring signals are communicated via a data bus as analog / discrete signals to the Brake Control Unit (BCU). An exemplary centralized architecture is described in US 2008 / 0030069A1.

[0003] The BCU interprets commands from the aircraft cockpit controls and avionics, and calculates braking force commands for each actuated landing gear wheel of the aircraft. This can include quick cycle skid control.

[0004] Each brake wheel will have at least one electromechanical actuator (EMA) for providing a clamping force to the brakes for that wheel, which brake wheel converts the clamping force into a braking torque. An elect...

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