A heated leading edge structure for an aircraft is presented, the heated leading edge structure comprising: a leading edge panel having an outer surface configured to be contacted by an ambient flow and an inner surface opposite the outer surface; a rear panel at least partially disposed at a distance from the inner surface; a closed chamber inside the leading edge structure; a heating device attached inside the chamber; and an air delivery device in fluid communication with the heating device, where the air delivery device is configured to deliver air from inside the chamber through the heating device to be heated and back to the chamber such that a circulating flow of heated air is generated inside the chamber.

    提出了一种用于飞行器的加热前缘结构,该加热前缘结构包括:前缘面板,该前缘面板具有被配置成由环境流接触的外表面以及与该外表面相反的内表面;后面板,该后面板至少部分地布置成与该内表面相距一段距离;在该前缘结构内部的封闭腔室;附接在该腔室内部的加热装置;以及与该加热装置处于流体连通的空气输送装置,其中,该空气输送装置被配置成将空气从该腔室内部输送通过该加热装置以被加热并返回至该腔室,使得在该腔室内部产生经加热的空气的循环流。


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    Title :

    Heated leading edge structure for aircraft


    Additional title:

    用于飞行器的加热前缘结构


    Contributors:

    Publication date :

    2024-05-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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