The invention provides a high-speed aircraft vertical tail and a vertical tail optimization design method. The high-speed aircraft vertical tail comprises a full-moving control surface, a fixed control surface and a connecting rotating shaft, wherein the full-moving control surface is rotatably connected with the fixed control surface through the connecting rotating shaft, and an included angle isformed between the connecting rotating shaft and the vertical surface of the chord plane of the vertical tail. By applying the technical scheme, the technical problems that in the prior art, when thevertical tail rotates around the vertical rotating shaft, in order to meet the maneuvering performance requirement of low-speed flight, the mass of the vertical tail is increased and the flight stability is reduced can be solved.

    本发明提供了一种高速飞行器立尾及立尾优化设计方法,该高速飞行器立尾包括包括全动舵面、固定舵面和连接转轴,全动舵面通过连接转轴与固定舵面可转动地连接,连接转轴与立尾弦平面的垂直面之间呈夹角设置。应用本发明的技术方案,能够解决现有技术中立尾绕垂直转轴转动时为了满足低速飞行的机动性能需求导致的立尾质量增加和飞行稳定性降低的技术问题。


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    Titel :

    High-speed aircraft vertical tail and vertical tail optimization design method


    Weitere Titelangaben:

    一种高速飞行器立尾及立尾优化设计方法


    Beteiligte:
    YOU LIANXING (Autor:in) / WANG QUANPING (Autor:in)

    Erscheinungsdatum :

    2020-05-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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