The invention belongs to the field of aircraft design, and relates to an aerodynamic layout of a supersonic tailless aircraft, aiming at a supersonic tailless layout aircraft, aiming at improving course stability, reducing supersonic resistance, reducing subsonic speed head lowering torque and improving cruise performance, parts such as a front body, an afterbody and a tail tip of the aircraft are optimized and designed respectively. The optimization design method is suitable for all supersonic tailless layout aircrafts, a fuselage comprises a front body and a rear body, the front body generally refers to the nose position of the aircraft, the rear body generally refers to the structure of the aircraft from the gravity center to the tail, and a middle fuselage is arranged between the front body and the rear body.

    本申请属于飞行器设计领域,为一种超音速无尾飞机气动布局,针对超音速无尾布局飞机,以增大航向稳定性、降低超音速阻力、降低亚音速低头力矩,改善巡航性能为目标,分别对飞机前体、后体、尾尖等部件开展优化设计。本申请中的优化设计方法适用于所有超音速无尾布局飞机,机身包括前体和后体,前体泛指飞机的机头位置,后体泛指飞机从重心到末尾之间的结构,前体与后体之间为中机身。


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    Titel :

    Aerodynamic layout of supersonic tailless aircraft


    Weitere Titelangaben:

    一种超音速无尾飞机气动布局


    Beteiligte:
    ZHAN GUANG (Autor:in) / SHI JUNZHI (Autor:in) / LIU XIAODONG (Autor:in) / LEE HYE-KYUNG (Autor:in) / YI RAN (Autor:in)

    Erscheinungsdatum :

    11.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge




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