An aircraft brake temperature control system (BTCS) 100 and method for controlling a temperature of a brake 220 of a landing gear of an aircraft 200. The system 100 comprises a controller 110 that is configured to cause a thermal management system 2000 to regulate the temperature of the brake 220 based on selection of an objective from a plurality of objectives 121, 122, 141, 142 for regulating the temperature of the brake. The objectives may relate to the performance or lifespan of brakes; reduction of noise, vibration and harshness (NVH) of the aircraft; and/or temporal conditions, such as flight duration or turn around time (see e.g. fig. 6). The system may include a data recorder 130 and analyser 131 to determine regimes to be used to fulfil the objectives. Also claimed is a temperature control system comprising a controller configured to determine the extent of operation of at least one forced convection device (e.g. fans 230, 231, 232) and/or natural convection device (e.g. external air inlet 240 and/or exhaust 250 vents) configured to move fluid along a surface of an aircraft brake, based on at least one non-thermal aircraft or flight condition.
Aircraft brake temperature control system
2022-06-15
Patent
Elektronische Ressource
Englisch