The invention relates to the technical field of hypersonic flight vehicle thermal protection, and discloses a hypersonic flight vehicle ultra-high temperature end thermal sealing structure which comprises a first thermal resistance adapter plate fixed to the near end of an end cap of an flight vehicle and a second thermal resistance adapter plate fixed to the front end of an aluminum alloy shell of the flight vehicle. The first thermal resistance adapter plate and the second thermal resistance adapter plate are fixedly connected through a connecting screw. The edge of the end cap and the edgeof the aluminum alloy shell are in lap joint through a labyrinth groove. The outer wall of the aluminum alloy shell is sequentially provided with an aerogel heat insulation layer and a cabin outer heat protection layer from inside to outside. According to the invention, the end cap is connected with the cabin aluminum alloy shell through the adapter plates; the connecting face of the aluminum alloy shell and the end cap is of a lap joint labyrinth groove structure, the outer surface connecting face and the inner surface lap joint face are staggered in position, the influence of thermal expansion of the cabin body heat-proof layer is reduced, and therefore the thermal strain of the cabin body heat-proof layer is reduced, heat transfer of hot air flow into the cabin body is reduced, thermalsealing is effectively achieved, and safety and reliability of the structure are guaranteed.
本发明涉及高超声速飞行器热防护技术领域,公开了一种高超声速飞行器超高温端头热密封结构,包括固定于飞行器端头帽近端的热阻转接板一和固定于飞行器的铝合金壳体前端的热阻转接板二;热阻转接板一与热阻转接板二之间通过连接螺钉固定连接;端头帽边缘与铝合金壳体边缘对接部位通过迷宫槽搭接;铝合金壳体外壁由内至外依次设置有气凝胶隔热层和舱体外防热层。本发明的端头帽与舱体铝合金壳体采用转接板连接,铝合金壳体与端头帽连接面为搭接迷宫槽结构,外表面连接与内表面搭接面位置错开,减小舱体防热层受热膨胀的影响,从而减小舱体防热层热应变,并减少热气流向舱体内部传热,有效实现了热密封,保证了结构的安全可靠。
Hypersonic flight vehicle ultra-high temperature end thermal sealing structure
一种高超声速飞行器超高温端头热密封结构
2020-05-08
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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