The invention discloses a hypersonic speed combined resistance and heat reduction structure based on reverse jet flow and active cooling, and belongs to the technical field of resistance and heat reduction. Nozzles are arranged at the passivated leading edge of the aircraft, and reverse jet flow is implemented. And the nozzles are symmetrically arranged up and down relative to the center line of the passivated leading edge of the aircraft in a matrix form. A convection cooling loop, a gas jet loop and an internal supporting space are arranged in the airplane passivated leading edge. The convection cooling loops are arranged on the upper surface and the lower surface of the passivation front edge respectively, the cross section of a flow channel, close to one end of a nozzle, of each convection cooling loop is in a step shape, and cooling media circulate in the convection cooling loops through pumps. One end of each gas jet loop is connected with the nozzle, the other end of each gas jet loop is connected with the internal jet device, gas jetted by the internal jet device is jetted out of the nozzle through the gas jet loops, and the gas jet loops are located on the upper side and the lower side of the center line respectively and gradually incline towards the center line from the internal jet device to the nozzle. According to the invention, strong heating heat flow caused by shock wave-shock wave interference in passivation leading edge areas of various aircrafts is reduced.

    基于逆向喷流与主动冷却的高超声速组合减阻降热结构,属于减阻降热技术领域。在飞机钝化前缘位置排布喷口,实施逆向喷流。喷口以矩阵形式相对于飞机钝化前缘中心线上下对称排布。飞机钝化前缘内设有对流冷却回路、气体喷流回路和内部支撑空间;对流冷却回路分别开设于钝化前缘的上、下表面,对流冷却回路靠近喷口一端的流道横截面呈现阶梯状,对流冷却回路中通过泵循环冷却介质;气体喷流回路一端连接喷口,另一端连接内部喷流装置,内部喷流装置喷出的气体经过气体喷流回路从喷口喷出,气体喷流回路分别位于中心线上下两侧,且从内部喷流装置到喷口逐渐向中心线倾斜。本发明实现降低各类飞行器钝化前缘区域因激波‑激波干扰而导致的强加热热流。


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    Titel :

    Hypersonic speed combined resistance and heat reducing structure based on reverse jet flow and active cooling


    Weitere Titelangaben:

    基于逆向喷流与主动冷却的高超声速组合减阻降热结构


    Beteiligte:
    WANG ZHAN (Autor:in) / LI JIAWEI (Autor:in) / ZHANG ANKUN (Autor:in) / SHEN XUAN (Autor:in) / LI XIANKAI (Autor:in) / ZHOU YONGJIAN (Autor:in) / HE MOFAN (Autor:in) / SHENG FAJIA (Autor:in)

    Erscheinungsdatum :

    2022-11-01


    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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