An aircraft wheel braking arrangement may comprise a landing gear structure (122, 222, 422), a torque tube (120) extending in an outboard direction from the landing gear structure (122, 222, 422), and an actuator housing (150, 250, 450) disposed outboard from the torque tube (120). An actuator piston may extend in an inboard direction from the actuator housing (150, 250, 450) for applying a force to a brake stack (131) surrounding the torque tube (120). In various embodiments, a back plate (131) is non-integral to the torque tube (120) and may be disposed inboard of an end plate of the brake stack (131) or the landing gear structure (122, 222, 422) itself may act as the back plate (131). The back plate (131) and/or the end plate may provide a direct thermal path from the brake stack to a landing gear structure (122, 222, 422).


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    Titel :

    AIRCRAFT BRAKE TORQUE AND CLAMP FORCE REACTION THROUGH LANDING GEAR STRUCTURE


    Weitere Titelangaben:

    BREMSMOMENT- UND KLEMMKRAFTREAKTION EINES FLUGZEUGS DURCH EINE FAHRWERKSSTRUKTUR
    RÉACTION DE COUPLE DE FREINAGE D'AÉRONEF DE FORCE DE SERRAGE PAR L'INTERMÉDIAIRE D'UNE STRUCTURE DE TRAIN D'ATTERRISSAGE


    Beteiligte:
    WHITTLE SCOTT (Autor:in)

    Erscheinungsdatum :

    07.07.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF / F16D COUPLINGS FOR TRANSMITTING ROTATION , Nicht schaltbare Kupplungen



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