A wing leading edge device is proposed, comprising a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the firstspanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the backskin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.
提出了一种机翼前缘装置,所述机翼前缘装置包括流动本体,所述流动本体具有:前侧,所述前侧由第一展向边缘和第二展向边缘界定;后侧,所述后侧由所述第一展向边缘和所述第二展向边缘界定;前蒙皮,所述前蒙皮被布置在所述前侧上;后蒙皮,所述后蒙皮被布置在所述后侧上;以及至少一个加强组件,所述至少一个加强组件在所述第一展向边缘的区域中在所述前蒙皮和所述后蒙皮之间,其中,所述前蒙皮连续延伸并且在所述第一展向边缘和所述第二展向边缘之间没有中断,并且覆盖所述至少一个加强组件。
A WING LEADING EDGE DEVICE AND A WING HAVING SUCH A WING LEADING EDGE DEVICE
机翼前缘装置和具有这种机翼前缘装置的机翼
2020-09-04
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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