The pneumatic stealth and drag reduction structure comprises a nose, the rear end of the nose is fixedly connected with the front end of a fuselage, wings are fixedly arranged on the left side and the right side of the middle of the fuselage, rectification wrappers are fixedly arranged at the ends, close to the fuselage, of the wings, and winglets are fixedly arranged at the ends, away from the fuselage, of the wings; according to the technical scheme, front fuselage design, high-subsonic-speed area law and optimized spindle fuselage design, high-subsonic-speed wing section selection and optimization and medium-aspect-ratio wing design are adopted, and therefore the high-subsonic-speed area law and optimized spindle fuselage design can be achieved, and the high-subsonic-speed area law and optimized spindle fuselage design can be achieved, and the high-subsonic-speed area law and optimized high-subsonic-speed wing section selection and optimization and medium-aspect-ratio wing design can be achieved. Due to the rectification design of the connecting positions of the wings and the fuselage and the design of the S-shaped air inlet channels and the separation channels with the high total pressure recovery coefficient, high-subsonic-speed stealth aerodynamic appearance building of the unmanned aerial vehicle is achieved.
本发明公开一种高亚音速无人机的气动隐身及减阻结构,包括如下结构:机头,所述机头的后端与机身的前端固定连接,所述机身中部左右两侧均固设有机翼,所述机翼靠近机身一端固设有整流包皮,所述机翼远离机身一端固设有翼梢小翼;所述机身的后端左右对称设有尾翼,所述机身的顶部固设有进气道,所述进气道的进气端下方与机身的上方预设有隔道,本技术方案中前机身设计,高亚音速面积律及优化纺锤体式机身设计,高亚音速翼型选择及优化,中等展弦比机翼设计,机翼机身连接处整流设计,高总压恢复系数的S形进气道及隔道设计,实现无人机的高亚音速隐身的气动外形组建。
Pneumatic stealth and drag reduction structure of high-subsonic-speed unmanned aerial vehicle
一种高亚音速无人机的气动隐身及减阻结构
2024-12-03
Patent
Electronic Resource
Chinese
IPC: | B64U |
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