The invention discloses a subsonic aircraft air inlet channel which comprises an air inlet channel opening face, the bottom of the air inlet channel opening face is connected with an aircraft body and is integrally fused with the machine body, the rear end of the air inlet channel opening face communicates with an air inlet channel inner channel, a flow separation plate is fixedly supported in the air inlet channel inner channel, and the air inlet channel opening face is surrounded by a lip cover; the front side of the air inlet opening face is provided with a similar triangular step compression surface, the similar triangular step compression surface is fixed on the machine body, and the lip cover is in smooth connection with the machine body and the similar triangular step compression surface. According to the structure, a boundary layer separation channel independently arranged on the machine body is canceled, and a bulge protruding out of the surface of the machine body is replaced by the similar triangular step compression surface; meanwhile, by means of integrated fusion of the sweepback lip cover, the air inlet channel opening face, the similar triangular step compression face and the machine body, the boundary layer of the machine body can be effectively eliminated, the high total pressure recovery coefficient and the low flow field distortion index of the air inlet channel are kept, and meanwhile the attack angle and sideslip angle characteristics of the air inlet channel can be considered.

    本发明公开了一种亚声速飞行器进气道,包括进气道口面,所述进气道口面底部连接机身,且与机身一体化融合,所述进气道口面后端连通进气道内通道,所述进气道内通道内部支撑固定有隔流板,所述进气道口面上包围有唇罩,所述进气道口面前侧设有类三角形台阶压缩面,所述类三角形台阶压缩面固定于机身上,所述唇罩与机身和类三角形台阶压缩面光滑连接。本结构取消机体上独立布置的边界层隔道,并且以类三角形台阶压缩面来替代突出机身表面的鼓包;同时,通过后掠形的唇罩以及进气道口面、类三角形台阶压缩面与机身的一体化融合,可有效排除机身边界层,保持进气道较高的总压恢复系数和较低的流场畸变指数的同时可以兼顾进气道的攻角、侧滑角特性。


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    Titel :

    Subsonic aircraft air inlet channel


    Weitere Titelangaben:

    一种亚声速飞行器进气道


    Beteiligte:
    ZHANG HONGLEI (Autor:in) / LIN JING (Autor:in)

    Erscheinungsdatum :

    2021-07-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Zero-length, slotted-lip inlet for subsonic military aircraft

    GLASGOW, E. / BECK, W. / WOOLLETT, R. | AIAA | 1980


    Zero-Length Slotted-Lip Inlet for Subsonic Military Aircraft

    E. R. Glasgow / W. E. Beck / R. R. Woollett | AIAA | 1982


    Top-mounted inlet system feasibility for transonic-subsonic fighter aircraft applications

    Williams, T. L. / Hunt, B. L. / Smeltzer, D. B. et al. | NTRS | 1981