The invention discloses a hypersonic-speed folding airfoil gap airflow partition structure which solves the problems that after a folding airfoil is unfolded and locked, high-speed hot airflow circulates along a folding gap, so that local hot flow and temperature at the folding gap are high. The device mainly comprises a lower wing surface, an upper wing surface, a high-temperature-resistant elastic spacer, a mounting screw and the like. A groove is formed in one side of the end face of the tip of the lower wing face in the chord direction, one end of the high-temperature-resistant elastic spacer is inserted into the groove, and the other end of the high-temperature-resistant elastic spacer protrudes out of the surface of the groove by 3-5 mm. And when the upper wing surface is unfolded to an unfolding locking position, the root part of the end surface of the upper wing surface extrudes and bends the high-temperature-resistant elastic spacer to form an airflow partition. A high-speed airflow channel of the folding gap of the folding airfoil is partitioned, the locking mechanism is prevented from being heated by high-speed airflow and being damaged at high temperature, the locking mechanism is particularly suitable for the structural design of the hypersonic folding airfoil, the application range of the folding airfoil is effectively widened, and the structural reliability is improved.

    本发明公开了一种高超声速折叠翼面缝隙气流隔断结构,解决了折叠翼面展开锁紧后高速热气流沿折叠缝隙流通,造成折叠缝隙处局部热流高、温度高的问题。主要有下翼面、上翼面、耐高温弹性隔片及其安装螺钉等组成。下翼面稍部端面一侧沿弦向设有凹槽,耐高温弹性隔片一端插入凹槽中,另一端凸出凹槽表面3mm~5mm。当上翼面展开至展开锁定位置时,上翼面端面根部将耐高温弹性隔片挤压弯曲,形成气流隔断。本发明对折叠翼面折叠缝隙高速气流通路形成隔断作用,避免锁紧机构被高速气流加热而产生高温破坏,特别适合于高超声速折叠翼面结构设计,有效提高了折叠翼面的使用范围,提升了结构可靠性。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Hypersonic speed folding airfoil gap airflow partition structure


    Weitere Titelangaben:

    一种高超声速折叠翼面缝隙气流隔断结构


    Beteiligte:
    HAN YAN (Autor:in) / LI XUEFENG (Autor:in) / ZHANG YONGLI (Autor:in) / LI HAO (Autor:in) / MA XINGPU (Autor:in) / CHEN HAO (Autor:in) / LI XIAOPENG (Autor:in) / NAN GUANGZHI (Autor:in) / MA YINGCHAO (Autor:in) / LI YAO (Autor:in)

    Erscheinungsdatum :

    2023-12-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    Wide-speed-range hypersonic aircraft airfoil profile multi-objective optimization design method and compromise airfoil profile

    LI CHUNNA / GUO XIAO / YANG LIANBO et al. | Europäisches Patentamt | 2022

    Freier Zugriff

    Straight airfoil folding mechanism

    TANG CHANGNING / YANG XIAODONG / LIN XINGLONG | Europäisches Patentamt | 2021

    Freier Zugriff

    High-bearing hypersonic-speed folding rudder adapting to thermal deformation

    ZHANG YONGLI / HAN YAN / LI XIAOPENG et al. | Europäisches Patentamt | 2023

    Freier Zugriff

    CONSTRUCTION OF OPTIMUM AIRFOIL FOR HYPERSONIC AIRCRAFT

    GALAKTIONOV ALEKSEJ JUR EVICH / LIKHACHEVA EKATERINA SERGEEVNA | Europäisches Patentamt | 2015

    Freier Zugriff

    Bionic airfoil of flapping-wing aircraft and folding flapping structure of bionic airfoil

    WANG HAO / ZHOU ZHUJING / ZHU YAOYONG et al. | Europäisches Patentamt | 2023

    Freier Zugriff