The invention provides a supersonic aircraft and an air inlet structure thereof, and the air inlet structure comprises a shell which comprises a bottom wall and a side wall connected to the bottom wall; and at least part of each separation channel assembly is located in the shell, the separation channel assembly and the bottom wall of the shell are arranged in a spaced mode to define an air inlet channel, and each separation channel assembly is detachably connected with the side wall. An air inlet is defined by one end of the bottom wall and the side wall, and an air outlet is defined by the partition channel assembly and the corresponding outer edge of the side wall. Because each separation channel assembly and the shell are of an independent module structure and can be assembled in a detachable mode, the cost is low, the maintainability is good, special process machining is not needed, the structural deformation is small, and the size of each module structure is detectable and measurable. When the shell or any separation channel assembly is damaged, only the damaged part needs to be replaced, and the whole air inlet structure does not need to be scrapped.
本发明提供了一种超音速飞行器及其进气结构,进气结构包括:壳体,包括底壁和连接于底壁的侧壁;以及至少一个隔道组件,每个隔道组件的至少部分位于壳体内并与壳体的底壁间隔设置以围成进气通道,每个隔道组件与侧壁可拆卸连接。底壁的一端与侧壁围成有进气口,隔道组件与侧壁的对应外边缘围成有出气口。由于每个隔道组件与壳体均为独立的模块结构,且可通过可拆卸方式进行组装,其成本低、维修性好,无需特殊工艺加工,结构变形小,各个模块结构尺寸可检、可测。在壳体或者任一隔道组件发生损坏时,只需更换损坏的部件即可,无需报废整个进气结构。
Supersonic aircraft and air inlet structure thereof
一种超音速飞行器及其进气结构
22.04.2025
Patent
Elektronische Ressource
Chinesisch