The invention discloses a normal aircraft brake system. The normal aircraft brake system comprises a travel switch, a hydraulic brake valve, an electric valve, an electro-hydraulic servo valve, an antiskid control box and a speed sensor, wherein the hydraulic brake valve is mounted near a pedal mechanism below a cockpit baseplate; and the antiskid control box is mounted in a main gear cabin. The travel switch controls the on/off of the electric valve; and the electric valve is mounted on a hydraulic pipeline at the downstream of the hydraulic brake valve. The electro-hydraulic servo valve is mounted on a hydraulic pipeline at the downstream of the electric valve. The normal aircraft brake system can satisfy the increasing take-off line brake requirement of a traditional normal aircraft brake system, is reasonable in structure, simple and feasible, accords with the ergonomic principle, facilitates to relieve the driver burden, and can eliminate the accident potential due to communication of a take-off line brake switch caused by wrong actions.


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    Titel :

    Normal aircraft brake system


    Beteiligte:
    HE YONGLE (Autor:in) / WANG HONGLING (Autor:in) / ZHAO YAJUN (Autor:in)

    Erscheinungsdatum :

    2015-07-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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