The invention discloses a waverider precursor hypersonic air inlet channel with double-cantilever pre-injection. The waverider precursor hypersonic air inlet channel comprises an air inlet channel inner wall face, a lip cover located on the air inlet channel inner wall face, a compression face extending forwards from the air inlet channel inner wall face and a waverider lower surface directly connected with the compression face. The inner wall surface of the air inlet channel and the lip cover jointly define an inner channel of the air inlet channel; the equal straight section extends backwards from the inner channel; the sweepback side plate is arranged on one side of the air inlet channel inner channel and one side of the equal straight section; an air inlet channel of the wave rider upper surface is integrated with the aircraft; cantilever structures are arranged on the last-stage compression face of the front body of the wave-rider front body air inlet channel and the inner wall face of a lip cover, fuel is jetted through the structures, the flow coefficient and the total pressure recovery coefficient of the air inlet channel are guaranteed, meanwhile, the fuel and incoming flow air are fully mixed in advance through the long front body of the hypersonic speed air inlet channel and an inner channel, and therefore the fuel efficiency is improved. Combustible mixed gas beneficial to combustion is provided for a combustion chamber connected to the rear portion of the gas inlet channel.
本发明公开了一种带有双悬臂预喷注的乘波前体高超声速进气道,包括进气道内壁面、位于进气道内壁面上的唇罩、自所述进气道内壁面向前延伸的压缩面以及与压缩面直接连接的乘波体下表面;所述进气道内壁面与所述唇罩共同围成进气道内通道;由所述内通道向后沿伸的等直段;设置在所述进气道内通道及等直段一侧的后掠侧板;以及进气道与飞行器实现一体化的乘波体上表面;在乘波前体进气道的前体最后一级压缩面及唇罩内壁面设置悬臂结构,通过该结构喷注燃料,在保证进气道流量系数以及总压恢复系数的同时,利用高超声速进气道较长的前体以及内通道实现燃料与来流空气的提前充分混合,为进气道后方所连接的燃烧室提供利于燃烧的可燃混合气。
Wave-rider precursor hypersonic air inlet channel with double-cantilever pre-injection
一种带有双悬臂预喷注的乘波前体高超声速进气道
2023-11-24
Patent
Electronic Resource
Chinese
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