Hypersonic flight vehicle ultra-high temperature end thermal sealing structure

Abstract

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.

Description

technical field [0001] The invention relates to the technical field of thermal protection for hypersonic aircraft, in particular to a heat sealing structure for an ultra-high temperature end of a hypersonic aircraft. Background technique [0002] When a hypersonic vehicle returns to the atmosphere and re-enters the atmosphere, it faces a very harsh aerodynamic heating environment, such as image 3 As shown, the maximum surface temperature of the aircraft reaches about 2500K, and the aerodynamic heating time of the aircraft tip and the windward side is long when facing the aerodynamic thermal environment, and the total heating amount is large; at the same time, in order to adapt to long-term safe flight, the airborne electronic devices The operating temperature environment inside the aircraft is extremely demanding. Under the harsh internal and external thermal environment conditions, how to ensure the local and overall thermal safety of hypersonic aircraft has become one of ...

AI Technical Summary

Problems solved by technology

[0003] In general, according to the characteristics of aerodynamic heating on the surface of hypersonic vehicles, the thermal protection requirements of different aircraft positions are different, and the materials used are different. layer + airgel heat insulation layer + aluminum alloy load-bearing frame" heat-proof design, these heat-proof designs can better ensure the safety of the aircraft structure, but the heat seal of the ultra-high temperature metal terminal, the outer wall and the inner wall of the cabin problem is difficult to solve effectively

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