An anti-icing system according to the present invention includes: a piccolo tube (11) that includes a flow path through which heated gas flows in the longitudinal direction from a rear end to a front end, and a plurality of ejection holes (16) provided along the longitudinal direction to make the flow path communicate with an outside; and an engine serving as a supply source (18) that supplies the heated gas toward the piccolo tube. The piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes.


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    Titel :

    ANTI-ICING SYSTEM AND AIRCRAFT


    Weitere Titelangaben:

    ENTEISUNGSSYSTEM UND FLUGZEUG
    SYSTÈME ANTIGIVRAGE ET AÉRONEF


    Beteiligte:
    MORISHITA MASATOSHI (Autor:in) / TSUJITA MASANORI (Autor:in) / WATANABE SATOSHI (Autor:in) / UEFUJI YOICHI (Autor:in) / KAWAI KAZUHIRO (Autor:in) / ISHIDA TOSHIYUKI (Autor:in) / ICHIKAWA GENTO (Autor:in) / FUJITA GO (Autor:in)

    Erscheinungsdatum :

    2022-09-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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