The invention discloses a supersonic air inlet channel arranged under the abdomen. Comprising a supersonic air inlet channel front body compression face (2) located on the lower belly of a supersonic missile body (1), and an air inlet channel body is connected to the rear portion of the supersonic air inlet channel front body compression face (2). A coordinate system is established on the symmetry plane of the supersonic missile body (1), the XY coordinate plane is the symmetry plane, and the X axis, the Y axis and the Z axis are the heading direction, the vertical direction and the transverse direction respectively; the supersonic air inlet channel front body compression surface (2) is in a variable curved surface design, three-level local isentropic compression is adopted in the X-axis direction, and corresponding compression angles delta 1, delta 2 and delta 3 are designed according to equal-strength compression. A missile belly lower air inlet layout form is adopted, the space of a missile head can be made, installation of components such as a guide head is facilitated, meanwhile, the flowing direction of low-energy flow of a boundary layer can be effectively changed through the variable-curved-surface compression surface design, the low-energy flow of the boundary layer can be effectively eliminated, and the performance of an air inlet channel is improved.
本发明公开了一种腹下布局超声速进气道。包括位于超声速导弹躯体(1)下腹的超声速进气道前体压缩面(2),超声速进气道前体压缩面(2)后方接进气道主体;在超声速导弹躯体(1)对称面上建立坐标系,其中:XY坐标平面为对称面,X、Y、Z轴分别为航向、竖向、横向;超声速进气道前体压缩面(2)为变曲面设计,其沿X轴方向采用三级局部等熵压缩,对应的各压缩角δ1、δ2、δ3按等强度压缩设计。本发明采用导弹腹下进气布局形式,可让出导弹头部空间,有利于导引头等元器件安装,同时变曲面压缩面设计可有效改变附面层低能流流动方向,有效排除附面层低能流,提升进气道性能。
Supersonic air inlet channel arranged under abdomen
一种腹下布局超声速进气道
2023-03-14
Patent
Electronic Resource
Chinese