Hydrogel sweating and cooling system

Abstract

The invention relates to a hydrogel sweating and cooling system. The device is provided with a porous wall surface, a support body, a hydrogel coolant and a water supply mechanism, the porous wall surface and the support body form an accommodating cavity mechanism for accommodating a hydrogel cooling agent; the water supply mechanism is used for providing an expansion water source for the hydrogel coolant. When the temperature rises, the hydrogel coolant is heated to lose water, and water vapor seeps out of a sweating cooling air film from holes in the porous wall surface while performing convection heat exchange in the containing cavity mechanism, so that heat transfer of high-temperature airflow to the wall surface is blocked while the temperature is reduced, and the efficient and stable cooling effect is achieved. In addition, the hydrogel coolant can absorb moisture from the water supply mechanism in real time so as to achieve the effect of continuous cooling.

Description

technical field [0001] The invention relates to the technical field of high temperature wall thermal protection, in particular to a hydrogel sweat cooling system applied to a hypersonic aircraft. Background technique [0002] Advanced space vehicles are in high-speed flight, such as figure 2 As shown in the figure, the outer casing is heated by aerodynamics and the inside of the engine is heated by gas, and the temperature will reach more than 3000K. The local shock wave disturbance and uneven heat flow make the thermal environment of the aircraft more severe. With the development goals of high thrust, high Mach, and long endurance, thermal protection has become a key problem restricting the development of high-speed aircraft. The original passive thermal protection relies on material heat sinks, ablative heat-proof or high-temperature-resistant materials for heat insulation, which increases the structural volume of the aircraft, and the aerodynamic shape changes with the h...

AI Technical Summary

Problems solved by technology

The original passive thermal protection relies on material heat sink, ablation heat protection or heat insulation of high temperature resistant materials, which increases the structural volume of the aircraft, and the aerodynamic shape changes with the heating; the commonly used active regenerative cooling uses fluid convection heat transfer to absorb heat. Cooling the high-temperature parts of the aircraft, the system is relatively complex, and the convective heat transfer efficiency is limited; the traditional phase change sweating cooling is prone to problems such as steam blockage and temperature oscillation due to the instability of the liquid phase change, and it is difficult to adjust when the flight attitude changes

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