The invention discloses an aircraft tail vane and a preparation method. The aircraft tail vane comprises a vane body. Comprising a rudder body; the rudder body comprises a supporting framework and two first skins; the supporting framework is provided with a through groove and at least one exhaust hole communicated with the through groove, and the through groove is used for reducing the weight of the supporting framework; the two first skins are arranged on the two opposite sides of the supporting framework correspondingly and seal the through groove. According to the aircraft tail vane, the exhaust hole communicated with the through groove is formed in the supporting framework of the vane body, so that the external pressure of the vane body can be kept consistent with the pressure in the through groove, and the situation that normal use is affected due to the fact that the vane body deforms in the flight process of an aircraft is avoided.
本申请公开了一种飞行器尾舵及制备方法,飞行器尾舵包括舵体;包括舵体;所述舵体包括支撑骨架和两个第一蒙皮;所述支撑骨架开设有通槽和与至少一个所述通槽连通的排气孔,所述通槽用于减轻所述支撑骨架的重量;两个所述第一蒙皮分别设置在所述支撑骨架相背的两侧,并封闭所述通槽。该飞行器尾舵中舵体的支撑骨架上设置有与通槽连通的排气孔,以使舵体的外部压力与通槽中的压力能够保持一致,从而避免飞行器在飞行过程中,舵体发生变形而影响正常使用的情况发生。
Aircraft tail vane and preparation method
一种飞行器尾舵及制备方法
18.02.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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