The invention discloses a bulge structure, an air inlet channel and an aircraft. The bump structure comprises a flexible skin, a hard annular side wall, a negative Poisson's ratio honeycomb and a hard base, the flexible skin is designed by adopting a plurality of design points, the initial molded surface of the flexible skin is a better molded surface corresponding to the minimum working Mach number, and the flexible skin comprises a central area, an inner-layer annular area, a middle-layer annular area and an outer-layer annular area from inside to outside, the outer side boundary lines of the central area, the inner-layer annular area and the middle-layer annular area are contour lines of a better molded surface corresponding to the maximum working Mach number, and the heights of the contour lines corresponding to the outer side boundary lines of the central area, the inner-layer annular area and the middle-layer annular area are sequentially reduced. The bulge structure is beneficial to improving the aerodynamic performance of the air inlet duct of the air vehicle under multiple working Mach numbers, so that the air inlet duct can take both subsonic speed performance and supersonic speed performance into account, and the aerodynamic performance of the air inlet duct of the air vehicle under a non-working Mach number is improved.
本发明公开了一种鼓包结构、进气道和飞行器。该鼓包结构包括柔性蒙皮、硬质环形侧壁、负泊松比蜂窝和硬质底座,柔性蒙皮采用多个设计点设计,其初始型面为最小工作马赫数对应的较优型面,柔性蒙皮包括由内向外的中心区域、内层环形区域、中层环形区域和外层环形区域,中心区域、内层环形区域和中层环形区域的外侧边界线均为最大工作马赫数对应的较优型面的等高线,且中心区域、内层环形区域和中层环形区域的外侧边界线分别对应的等高线的高度依次减小。该鼓包结构有利于提升飞行器鼓包进气道在多个工作马赫数下的气动性能,使其能够兼顾亚声速性能和超声速性能,并提升飞行器鼓包进气道在非工作马赫数下的气动性能。
Bump structure, air inlet channel and aircraft
鼓包结构、进气道和飞行器
2024-09-13
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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