Air-ground dual-purpose composite heat insulation structure based on air cooling screen

Abstract

The invention discloses an air-ground dual-purpose composite heat insulation structure based on an air cooling screen. The structure is installed outside a low-temperature storage tank and is characterized by comprising a polyurethane foam heat insulating layer and a variable-density heat insulating layer, the polyurethane foam heat insulating layer adheres to the outer wall of the low-temperature storage tank, and the outer wall of the polyurethane foam heat insulating layer is coated with the variable-density heat insulating layer; the variable-density heat insulating layer is composed of three layers, namely the low-density layer, the intermediate-density layer and the high-density layer in sequence starting from the outer wall of the polyurethane foam heat insulating layer, and the three layers are of the same thickness and are machined from eight heat insulating layers, fourteen heat insulating layers and twenty heat insulating layers in sequence. By the adoption of the structure, heat leakage of the low-temperature storage tank of a spacecraft is reduced passively to the minimum, so that evaporation of low-temperature propellant is reduced and the in-orbit life of the spacecraft is prolonged; furthermore, the structure has the advantage of being light.

Description

technical field [0001] The invention belongs to the technical field of heat insulation of low-temperature storage tanks of spacecraft, and in particular relates to a ground-air dual-purpose composite heat insulation structure based on an air-cooled screen. Background technique [0002] The non-destructive storage of cryogenic propellants plays a decisive role in the continuous deepening of future deep space exploration missions. The low-temperature propellant has a low boiling point, and evaporation is inevitable whether it is in low-earth orbit or on the surface of the moon or Mars. Vaporization of the cryogenic propellant leads to an increase in pressure inside the tank, posing a risk of damage to the tank. Therefore, to effectively control the evaporation of low-temperature propellants and realize zero-evaporation storage is one of the key issues that need to be solved urgently in the current low-temperature propellant storage technology. The main ways to achieve zero-e...

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Problems solved by technology

It uses the interlayer between the metal shell and the low-temperature tank to provide a vacuum environment for its low-temperature tank, but the weight of the metal shell cannot be ignored, which poses a problem for meeting the overall quality requirements of the spacecraft

The multi-layer insulation layer plays a role in reducing heat leakage during the radiation heat transfer under vacuum conditions, but when it is on the ground, the multi-layer insulation layer cannot play the role of heat insulation, and the problem of heat leakage will occur at this time

In the high vacuum of space, the multi-layer heat insulation layer can reduce the effect of radiation heat insulation, but the density of the existing multi-layer heat insulation layer is fixed. Increase the density of the multi-layer heat insulation layer, but this will increase the overall weight of the heat insulation structure, which cannot meet the quality and cost requirements of the spacecraft, that is, the contradiction between quality and heat insulation effect

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