The invention discloses a heatproof leading edge grid rudder under a medium-high heat flow condition, and belongs to the technical field of thermal protection. According to the method, the problems that although a grid rudder heat-proof coating is friendly in construction process and suitable for a grid rudder object, the anti-scouring capacity is low, and reentry high dynamic pressure cannot be resisted are solved, the safety of heat protection measures of a grid rudder body structure is ensured, and heat-proof structure damage to a heat-proof layer/body structure interface under high dynamicpressure scouring is avoided. Although the ends are exposed in incoming flow air to cause the pneumatic heating problem of the end body structure, due to the fact that the rear body is protected by the heat-proof layer, the temperature of the structure body of the grid is low, the high temperature of the ends can be transmitted to the grid structure body, and the heated high-temperature pressureof the ends is delayed. By the adoption of the thermal protection scheme, the process friendliness of the low-density thermal protection coating can be achieved, meanwhile, the technical problem thatthe thermal protection layer of the grid rudder grating body is not resistant to high dynamic pressure scouring is solved, and flight safety is guaranteed.

    一种中高热流条件下防热前缘栅格舵,属于热防护技术领域。本发明解决了栅格舵防热涂层虽然施工工艺友好,适合于栅格舵对象,但是抗冲刷能力低,不能抵抗再入高动压的难题,确保了栅格舵本体结构的热防护措施的安全性,避免在高动压冲刷下防热层/本体结构界面发生防热结构破坏。虽然端头裸露在来流空气中,造成端头本体结构的气动加热问题,但是由于后体受到了防热层的保护,栅格的结构本体温度较低,端头的高温可以向栅格结构本体传递,延缓了端头受热的高温压力。采用本发明热防护方案,即能够发挥低密度防热涂层的工艺友好性,同时避免了栅格舵格栅本体防热层不耐高动压冲刷的技术难题,确保了飞行安全。


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    Titel :

    Heatproof leading edge grid rudder under medium-high heat flow condition


    Weitere Titelangaben:

    一种中高热流条件下防热前缘栅格舵


    Beteiligte:
    DU TAO (Autor:in) / WANG GUOHUI (Autor:in) / GONG YUKUN (Autor:in) / YANG JIANMIN (Autor:in) / MA HUITING (Autor:in) / CUI ZHAOYUN (Autor:in) / ZHANG RAN (Autor:in) / MOU YU (Autor:in) / GAO JIAYI (Autor:in) / LI ZHOUYANG (Autor:in)

    Erscheinungsdatum :

    2021-02-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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