An aircraft brake control system 200 for controlling a plurality of brakes on wheels 221,222 of a retractable landing gear 210 wherein each braked wheel includes a brake actuator 241,242 and a wheel speed sensor 231,232. The system includes a controller 250 configured to receive aircraft control parameters and provide brake commands to the brake actuator of each wheel. The controller is configured to activate pre-retraction braking in response to an aircraft control parameter indicating that landing gear retraction is required and to execute a functional brake test during pre-retraction braking. The brake actuators are connected via hydraulic lines 261,262 to hydraulic servos 281,282.
Aircraft brake control system
2021-02-03
Patent
Elektronische Ressource
Englisch