The invention provides a drag reduction and heat protection structure of a hypersonic aircraft. The drag reduction and heat protection structure comprises a drag reduction rod and a cooling device, the drag reduction rod is installed on the head portion of the blunt end, the cooling device is arranged in the blunt end, and the blunt end is made of porous medium materials. And the cooling device is used for storing and releasing a coolant. The drag reduction and heat protection structure of the hypersonic aircraft is simple in structure and has excellent drag reduction effect and heat protection performance.

    本发明提供了一种高超声速飞行器减阻防热结构,包括:减阻杆和冷却装置;所述减阻杆安装在钝头的头部,所述冷却装置设于所述钝头的内部,且所述钝头采用多孔介质材料制成;所述冷却装置用于储存和释放冷却剂。本方案提供的高超声速飞行器减阻防热结构结构简单,兼具优异的减阻效果和防热性能。


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    Titel :

    Resistance reduction and heat protection structure of hypersonic flight vehicle


    Weitere Titelangaben:

    一种高超声速飞行器减阻防热结构


    Beteiligte:
    ZHANG HAOTIAN (Autor:in) / PANG SONGJIAN (Autor:in) / LU QIANG (Autor:in) / LI HAIYAN (Autor:in) / WANG YONGXIN (Autor:in) / WAN GUANGHENG (Autor:in) / WANG SIHUI (Autor:in) / MAO HONGXIA (Autor:in) / BAO XINGDONG (Autor:in) / WANG ZHENHUA (Autor:in)

    Erscheinungsdatum :

    28.01.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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