The invention relates to the technical field of thermal protection of hypersonic flight vehicles, and provides a hypersonic flight vehicle nose cone and a hypersonic flight vehicle with the same. The nose cone comprises a conical outer shell and a conical inner shell, the outer shell is connected with the middle of the head end of the inner shell through a connecting pipe, and a jet hole penetrating through the head ends of the inner shell and the outer shell is formed in the middle of the connecting pipe; the tail end of the outer shell and the tail end of the inner shell are sealed through a tail plate to form a heat dissipation outer cavity, side ribs are arranged in the radial direction to divide the outer cavity into a plurality of sub-cavities, capillary structure layers are arranged on the inner walls of the sub-cavities, and the sub-cavities are filled with alkali metal working media. A rear end cover is arranged at the tail of the inner shell, a cooling pipe is arranged in a middle mounting hole of the rear end cover, a hemispherical head is arranged at the head end of the cooling pipe, and an impact jet pipe is radially arranged on the portion, located in the inner shell, of the cooling pipe. Coupling among heat pipe dredging passive heat protection, concave cavity passive heat protection, jet flow impact active heat protection and reverse jet flow active heat protection modes can be expanded according to the aerodynamic heat environment through a simple structure, and the heat protection efficiency and effect are improved.
本发明涉及高超声速飞行器热防护技术领域,提供一种高超声速飞行器头锥及具有该头锥的高超声速飞行器。该头锥包括锥形的外壳体、内壳体,外壳体与内壳体头端中部通过连接管连接,连接管中部设有贯穿内外壳体头端的喷流孔;外壳体与内壳体尾端通过尾板密封,形成疏热外腔且沿径向设侧肋将外腔分隔为多个子腔室,子腔室内壁设毛细结构层,子腔室内充有碱金属工质;内壳体尾部设后端盖,后端盖中部安装孔内设冷却管,冷却管头端设半球形头部,冷却管位于内壳体内的部分沿径向设冲击射流管。本发明能够以简单结构实现根据气动热环境展开热管疏导被动防热、凹腔被动防热、射流冲击主动防热、逆向喷流主动防热方式间的耦合,提高热防护效率与效果。
Hypersonic aircraft nose cone and hypersonic aircraft with same
一种高超声速飞行器头锥及具有该头锥的高超声速飞行器
2023-02-03
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Active thermal protection system for hypersonic aircraft nose cone
European Patent Office | 2020
|NTIS | 1964
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