The invention discloses a high-thermal-conductivity spontaneous sweating heat-proof end, and belongs to the technical field of thermal protection of high-speed aircrafts. The end comprises a heat dredging structure, a heat transfer structure, a sweating working medium, a storage tank, a pressure switch, a spiral vapor-liquid separator, a metal pipeline and a porous structure. The sweating working medium is arranged in the storage tank, and the storage tank is connected with the spiral vapor-liquid separator through the pressure switch. One end of the heat transfer structure is connected with the heat dredging structure, and the other end of the heat transfer structure extends into the sweating working medium. The porous structure is arranged in an end stagnation point area, one end of the metal pipeline is communicated with the spiral vapor-liquid separator, and the other end of the metal pipeline is communicated with the porous structure. Pneumatic heating serves as a power source, the power of the power source is adjusted through heat dredging and heat transfer, and high-heat-conduction spontaneous perspiration cooling of the end structure is achieved.
本发明公开了一种高导热自发汗防热端头,属于高速飞行器热防护技术领域。端头包括热疏导结构、传热结构、发汗工质、储存罐、压力开关、螺旋汽液分离器、金属管路、多孔结构。发汗工质置于储存罐内,储存罐通过压力开关与螺旋汽液分离器连接。热疏导结构呈球锥状,传热结构一端与热疏导结构连接,另一端伸入发汗工质中。多孔结构置于端头驻点区域,金属管路一端与螺旋汽液分离器连通,另一端与多孔结构连通。本发明以气动加热作为动力源,通过热疏导和热传递调节动力源功率,实现了端头结构的高导热自发汗冷却。
High-thermal-conductivity spontaneous-sweating heatproof end
一种高导热自发汗防热端头
2025-02-11
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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