Condensing and radiating heating panel

Abstract

The invention discloses a condensing and radiating heating panel, which is composed of a hollow heat conduction panel, a capillary structure and a gas-liquid two-phase fluid; the capillary structure is composed of sintering cores and liquid-sucking cores; the sintering cores are lined at the periphery of the inner surface of the hollow heat conduction panel and the inside surface of the heating surface of the hollow heat conduction panel; the liquid-sucking cores are filled in the hollow part of the hollow heat conduction panel and closely connected with the sintering cores; the gas-liquid two-phase fluid is soaked in the pore structures of the liquid-sucking cores and the sintering cores; the inside surface of a radiating surface of the hollow heat conduction panel is provided with a drainage layer which is closely connected with the liquid-sucking cores; the external surface of a radiating condensing surface is a fractal surface which is a self-affine fractal structure surface and provided with at least two levels of concave-convex structures; and the liquid-sucking core structure is of a porous foam honeycomb structure. The heating panel can efficiently spread heat generated by airborne electric equipment of an aircraft under the condition of no-pump drive, thus ensuring efficient, safe and stable operation of the airborne equipment in the spacecraft.

Description

technical field [0001] The invention relates to a heat dissipation device for a spacecraft thermal control system in a microgravity environment, in particular to a capillary self-circulation-based condensation radiation heat dissipation plate. Background technique [0002] A reliable and efficient thermal control system is one of the primary prerequisites for ensuring the safe flight of aerospace vehicles. With the rapid development of aerospace vehicle manufacturing technology, the thermal reliability indicators of its on-board electronic and electrical equipment are becoming more and more stringent. Higher requirements are put forward for the heat dissipation capacity of the heat exchange device and the heat dissipation performance of the spacecraft surface. Due to the existence of moving parts, the traditional cooling device that relies on the consumption of pump power for heat transfer greatly increases the difficulty of the thermal control system of the spacecraft. It i...

AI Technical Summary

Problems solved by technology

Due to the existence of moving parts, the traditional heat dissipation device that relies on the consumption of pump power for heat transfer greatly increases the difficulty of the thermal control system of the spacecraft. It is urgent to develop a heat dissipation system that can realize heat transfer without pump drive.

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