The invention provides a divergence and air film double-cooling system applied to the surface of a nose cone of a reciprocating hypersonic aircraft. The system mainly comprises a hypersonic aircraft nose cone surface, a divergent cooling system and an air film cooling system, the surface of the nose cone of the hypersonic aircraft is divided into two areas which are a stationary point area containing stationary points and a non-stationary point area not containing stationary points, the nose cone surface stationary point area adopts divergent cooling, a cooling agent is liquid water, the nosecone surface non-stationary point area adopts gas film cooling, the cooling agent is nitrogen, and the divergent cooling system and the gas film cooling system work independently. The cooling requirements of the stationary point area and the non-stationary point area can be met at the same time, the cooling efficiency of the stationary point area is not lower than 90%, the cooling efficiency of the non-stationary point area is not lower than 60%, and the weight of the cooling agent needing to be carried by the aircraft can be effectively reduced.

    本发明提供了一种应用于可往返式高超声速飞行器头锥表面的发散与气膜双冷却系统。该发明主要包括高超声速飞行器头锥表面、发散冷却系统、气膜冷却系统,所述高超声速飞行器头锥表面分为两个区域,包含驻点的驻点区和不包含驻点的非驻点区,所述头锥表面驻点区采用发散冷却,冷却剂为液态水,所述头锥表面非驻点区采用气膜冷却,冷却剂为氮气,所述发散冷却系统与所述气膜冷却系统独立工作。本发明不仅能同时满足驻点区与非驻点区的冷却需求,驻点区冷却效率不低于90%,非驻点区冷却效率不低于60%,还能有效的降低飞行器所需要携带的冷却剂的重量。


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    Titel :

    Divergence and air film double-cooling system applied to surface of nose cone of reciprocating hypersonic aircraft


    Weitere Titelangaben:

    一种应用于可往返式高超声速飞行器头锥表面的发散和气膜双冷却系统


    Beteiligte:
    LI YULONG (Autor:in) / ZHOU YING (Autor:in) / WANG LINGHUA (Autor:in) / YU QUN (Autor:in)

    Erscheinungsdatum :

    2020-09-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64G Raumfahrt , COSMONAUTICS



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