The invention relates to the technical field of aircrafts, and discloses a wing rotation hot air ice preventing and removing structure which comprises a heat exchange cavity formed in an aircraft wing, and the heat exchange cavity extends in the length direction of the aircraft wing; an air inlet channel is formed in one axial side of the heat exchange cavity, and air enters the heat exchange cavity through the air inlet channel and forms circumferential rotational flow; the tail end of the heat exchange cavity is further provided with an air outlet channel, and air in the heat exchange cavity is exhausted outwards through the air outlet channel. The technical problem that the closer to the tail end, the poorer the anti-icing and deicing effects of an aircraft wing in the related technology can be solved.

    本发明涉及飞行器技术领域,公开了一种机翼旋转热气防除冰结构,包括设置在飞机机翼的换热腔室,换热腔室沿飞机机翼的长度方向延伸;换热腔室轴向的一侧具有进气通道,气体通过进气通道进入换热腔室内,并形成周向旋流;换热腔室的末端还具有出气通道,换热腔室内的气体通过出气通道向外排出。本发明可以解决相关技术中的飞机机翼存在的越靠近末端,防除冰效果越差的技术问题。


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    Titel :

    Wing rotating hot air ice preventing and removing structure


    Weitere Titelangaben:

    一种机翼旋转热气防除冰结构


    Beteiligte:
    LIU YUYANG (Autor:in) / YANG SHENGKE (Autor:in) / WANG QIANG (Autor:in) / YI XIAN (Autor:in)

    Erscheinungsdatum :

    28.01.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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