The invention provides a subsonic velocity flat fusion body layout aircraft, and relates to the technical field of aviation aircraft design, the tail contour edge of an inner wing body and the contour edges of two outer wing bodies are designed and arranged by adopting an edge parallel rule, and the aircraft has the stealth characteristic; the head edge of the inner wing body forms an inner wing body rear slight angle, the front edge of the outer wing body forms an outer wing section rear sweepback angle, and the double-sweepback layout is adopted to adapt to high-speed flight and low-speed flight; the inner wing body adopts a trailing edge symmetrical airfoil profile or a slight rear unloading airfoil profile, and the outer wing body adopts an airfoil profile combining front edge loading and rear edge slightly larger rear unloading, so that torque self-balancing of a cruise design point is realized; the inner wing body is provided with a backpack intake and exhaust system, so that the stealth characteristic is ensured; an air inlet channel and an exhaust nozzle of the air inlet and exhaust system are both in S-bend internal flow profile design. An outlet of the exhaust nozzle is designed in a shape-preserving mode, and fusion of various air inlet and exhaust systems can be achieved. And a mode of combining multiple characteristics is adopted for design, the stealth characteristic and the aerodynamic characteristic are considered, and the better comprehensive characteristic is achieved.

    本发明提供一种亚声速扁平融合体布局飞行器,涉及航空飞行器设计技术领域,内翼体的尾部轮廓边缘和两个外翼体轮廓边缘采用边缘平行法则设计布局,具有隐身特性;内翼体的头部边缘形成内翼体后略角,外翼体的前部边缘形成外翼段后掠角,采用双后掠布局适应较高速度飞行和低速飞行;内翼体采用后缘对称翼型或轻微后卸载翼型,外翼体采用前缘加载和后缘略大后卸载相组合的翼型,实现巡航设计点的力矩自配平;内翼体设置背负式进排气系统,保证隐身特性;进排气系统的进气道和尾喷管均采用S弯内流型面设计;尾喷管出口进行保形设计,可实现多种进排气系统的融合。采用多种特征相互组合的方式进行设计,兼顾隐身特性与气动特性,具有更好的综合特性。


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    Titel :

    Subsonic velocity flat fusion body layout aircraft


    Weitere Titelangaben:

    一种亚声速扁平融合体布局飞行器


    Beteiligte:
    YU YONGGANG (Autor:in) / LAN QINGSHENG (Autor:in) / ZHOU ZHU (Autor:in) / HUANG YONG (Autor:in) / SHAO YUANPEI (Autor:in) / LIU HONGYANG (Autor:in) / ZENG LEI (Autor:in) / CHEN XIAN (Autor:in) / LIU JIN (Autor:in) / WEI JIANFENG (Autor:in)

    Erscheinungsdatum :

    2023-01-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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