The invention provides an aircraft leading edge structure. The aircraft leading edge structure comprises a leading edge skin, a leading edge cabin upper wall plate, a leading edge cabin lower wall plate and an auxiliary beam assembly. The auxiliary beam assembly is provided with a first connecting end and a second connecting end which are oppositely arranged, the leading edge skin and the leading edge cabin upper wall plate are installed and connected to the first connecting end, and the leading edge skin and the leading edge cabin lower wall plate are installed and connected to the second connecting end. The leading edge skin and the leading edge cabin upper wall plate can move relative to the first connecting end. When the leading edge structure of the airplane encounters bird impact, the leading edge skin, the leading edge cabin upper wall plate and the leading edge cabin lower wall plate can relatively move and rub with one another, the instantaneous pressure caused by impact force to the structure can be relieved through the relative movement, part of impact energy can be consumed through the generated friction, part of impact energy can be absorbed through bending deformation of the structure, and the impact force can be reduced. And the damage to the structure is reduced. The auxiliary beam assembly does not need to be designed to be large in size, the effect of resisting bird impact is achieved, and meanwhile the purpose of weight reduction can be achieved.
本发明提供了一种飞机前缘结构,包括:前缘蒙皮、前缘舱上壁板、前缘舱下壁板以及辅助梁组件。辅助梁组件具有相对设置的第一连接端和第二连接端,前缘蒙皮和前缘舱上壁板安装连接于第一连接端上,前缘蒙皮和前缘舱下壁板安装连接于第二连接端上。前缘蒙皮和前缘舱上壁板可相对第一连接端移动。当飞机的前缘结构遇到鸟撞冲击时,前缘蒙皮、前缘舱上壁板及前缘舱下壁板会发生相对移动并相互摩擦,相对移动可以缓解冲击力对结构造成的瞬间压力,产生的摩擦能够消耗部分冲击能量,结构发生弯曲变形可以吸收部分冲击能量,减轻结构受到的损伤。辅助梁组件无需设计较大的尺寸,在达到抗鸟撞冲击效果的同时,可实现减重的目的。
Aircraft leading edge structure
飞机前缘结构
2024-03-01
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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