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.


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    Title :

    Aircraft brake temperature control system


    Contributors:
    USTAV OZA (author) / KURT BRUGGEMANN (author) / ROB HURLEY (author)

    Publication date :

    2022-06-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF / B64C AEROPLANES , Flugzeuge



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