A leading-edge slat (6) for an aircraft (62) is proposed, which comprises a front skin (10), a back skin (12), a spar (14) and an air inlet (16) for receiving air at an elevated temperature for de-icing or anti-icing. In the slat, at least one air chamber is created, which is supplied with said air. A first portion (28) of the back skin (12) is attached to the spar (14) at a distance to the bottomsection (20), wherein a second portion (31) of the back skin (12) is attached to the top section (22). Thereby, a region in front of the fixed leading edge (2) is created, into which air from air outlets (48) integrated into the back skin (12) can be exhausted outside of the slat (6).

    本发明提出了用于飞行器(62)的前缘缝翼(6),该前缘缝翼包括前蒙皮(10)、后蒙皮(12)、翼梁(14)、以及接纳升温空气以用于除冰或防冰的进气口(16)。在该缝翼中,形成了至少一个气室,该气室被供给有所述空气。后蒙皮(12)的第一部分(28)在距底部区段(20)一定距离处附接至翼梁(14),其中,后蒙皮(12)的第二部分(31)附接至顶部区段(22)。由此,形成了位于固定式前缘(2)的前面的区域,在该区域中来自集成到后蒙皮(12)中的出气口(48)的空气可以排出到缝翼(6)外部。


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    Title :

    LEADING-EDGE SLAT FOR AN AIRCRAFT


    Additional title:

    用于飞行器的前缘缝翼


    Contributors:

    Publication date :

    2020-05-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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



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