An active thermal protection structure for pulsating heat pipes coupled with ablation-resistant materials

Abstract

A pulsating heat pipe active thermal protection structure coupled with ablative resistant materials comprises a thermal grooming device and ablative resistant materials, wherein the ablative resistantmaterials are coated on the periphery of the thermal grooming device and comprise an inner layer and an outer layer; the inner layer is a flexible foam, and the outer layer is a high thermal conductivity carbon / carbon material; the thermal grooming device comprises a cooling panel, a pulsating heat pipe group and a phase change cold storage box; the cooling panel is bonded with the ablative resistant materials; the pulsating heat pipe group is welded with the cooling panel; the phase change cold storage box is welded with the cooling panel and fixed with the end frame of the aircraft; and thepulsating heat pipe extends into the phase change cold storage box. The pulsating heat pipe active thermal protection structure coupled with ablative resistant materials combine ablation-resistant material with the thermal grooming device. By means of the active thermal protection structure of the sharp lead edge of the aircraft, ablation is reduced or no ablation occur, and the aerodynamic shapeof the aircraft is changed little, and the aerodynamic characteristic of the aircraft with high lift-to-drag ratio is maintained, and the problem of material failure caused by the local high heat ofthe aircraft is solved, and the extreme distribution of temperature is avoided, and the long-time heat insulation is realized.

Description

technical field [0001] The invention relates to an active thermal protection structure of a pulsating heat pipe coupled with an ablation-resistant material, and belongs to the technical field of aircraft thermal protection. Background technique [0002] In the shape design of future aerospace vehicles, it will become an inevitable trend to replace the blunt leading edge with a sharp leading edge with low resistance. When the aircraft is flying at hypersonic speed, due to the effect of air viscosity, the air flow in the boundary layer of the object surface produces strong friction. As a result, the kinetic energy of the gas is irreversibly converted into heat energy. Strong pneumatic heating. The aircraft with sharp leading edge shape has great advantages in aerodynamic performance, but it will bring problems of high heat flux density and difficult heat protection. [0003] The blunt body technology and ablation heat protection theory have played an extremely important role...

AI Technical Summary

Problems solved by technology

[0004] 1. In view of the problem of high heat flux density at the leading edge of the rudder / wing, thermal protection is generally carried out by taking away heat by ablation. After ablation, the aerodynamic shape of the aircraft changes, the radius of the leading edge becomes larger, and the lift-to-drag ratio of the aircraft increases. Significantly reduced, which brings great difficulties to the calculation of aerodynamic force and the precise control of the aircraft, and cannot be reused

[0005] 2. During the service process of the aircraft, it is often subjected to extreme thermal environment at the end and leading edge, while the environment in the large area and the leeward area is relatively mild. Such conditions cause uneven surface temperature and local high heat and other thermal distribution of the aircraft. It brings great difficulties to the design of aircraft heat-proof structure, limits the selection of materials, and reduces the quality-effectiveness ratio of heat-proof structure design.

[0006] 3. In order to adapt to the long-term flight of future aircraft, the heat-proof structure needs to have the function of long-term heat insulation, while the traditional heat-proof scheme needs to increase the thickness and weight accordingly to achieve long-term heat insulation, which restricts the lightweight design of the aircraft Require

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