An aircraft brake temperature control system (BTCS) 100 for controlling a temperature of a brake 220 of a landing gear 201 of the aircraft 200. The BTCS 100 includes a controller 110 configured to cause at least one fluid moving device 230, 231, 232 to drive a flow of fluid onto the brake 220, selectively in one of a plurality of modes, to control the temperature of the brake 220. The BTCS 100 may be incorporated into an aircraft system 1000 with at least one fluid moving device 230, 231, 232, wherein the aircraft system is on an aircraft 200.
Aircraft brake temperature control system
26.03.2024
Patent
Elektronische Ressource
Englisch