The staged composite cooling structure for the aircraft rudder comprises a pressure pump, the rudder is arranged at the airflow output end of the pressure pump, a micro-channel is formed in the position, close to a connector of the pressure pump, in the rudder, and an inner space is formed in the position, at the tail end of the micro-channel, in the rudder; ribs are arranged at the tail end, close to the micro-channel, of the inner cavity of the inner space, a plurality of air film holes are formed in the supporting end face of the rudder, and the air film holes are connected with the interior and the exterior of the rudder. The composite cooling technology has the advantages that the composite cooling technology method is applied to the rudder design, innovation is achieved, and when the flight Mach number of an aircraft is larger than 6 after the rudder with the composite cooling technology is introduced, the highest temperature of a corresponding structure can be reduced, so that the reliability of the rudder of the aircraft is improved, and the service life of the rudder of the aircraft is prolonged.

    本发明公开了针对飞行器方向舵的分阶段复合冷却结构,包括压力泵,所述压力泵的气流输出端设置有方向舵,所述方向舵内近压力泵的接口处设置有微通道,所述微通道的末端且在方向舵的内部设置有内部空间,所述内部空间的内腔且近微通道的末端设置有肋,所述方向舵的支撑端面设置有若干气膜孔,且若干所述气膜孔连接方向舵内外部。优点:该发明将复合冷却技术方法应用于方向舵设计极具创新性,并且在引入带有该复合冷却技术的方向舵后飞行器的飞行马赫数大于6时,可以降低对应结构的最高温度,从而提高飞行器方向舵的可靠性和使用寿命。


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    Title :

    Staged composite cooling structure and method for aircraft rudder


    Additional title:

    针对飞行器方向舵的分阶段复合冷却结构及方法


    Contributors:
    ZHANG ZONGWEI (author) / MA ZHAOSEN (author) / LIU CONG (author) / LI BAIQING (author)

    Publication date :

    2022-12-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F25D REFRIGERATORS , Kühlschränke



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