Heat insulation component for heat control of a Mars landing machine, and manufacturing method thereof

Abstract

The invention discloses a heat insulation component for heat control of a Mars Landing machine. The heat insulation component comprises a thin layer structure, structure support pieces, first aerogel blocks, second aerogel blocks, honeycombs and skins, wherein the second aerogel blocks are filled inside the honeycombs and clamped between the upper skin and the lower skin so as to form a honeycomb plate, the first aerogel blocks and the structure support pieces are arranged on the first surface of the honeycomb plate, the thin layer structure is covered on the outer surface of the first aerogel blocks, and both the first aerogel blocks and the second aerogel blocks are composite SiO2 aerogel materials. The invention further discloses a manufacturing method for the heat insulation component. By utilizing the heat insulation component based on SiO2 aerogel, the problem that the aerogel material is difficult to use due to poor mechanical property is solved, and the heat insulation component is excellent in heat insulation performance and capable of effectively meeting requirement on heat insulation under the environment on the surface of the Mars, has obvious effect of light weight, can reduce the weight of a Mars lander, and is resource saving.

Description

technical field [0001] The invention relates to a thermal insulation component, in particular to a thermal insulation component for thermal control of a Mars lander and a preparation method thereof. Background technique [0002] CO exists on the surface of Mars 2 Atmosphere, severe dust storm, wind speed of 2~20m / s, temperature range -130℃~+30℃, affected by the thermal environment on the surface of Mars, there are convection, radiation and contact with the Martian surface between the Mars lander and the external environment. Heat transfer and other heat transfer methods. In order to cope with the Martian surface thermal environment with drastic temperature changes and various heat exchange methods, its thermal insulation device is very important. However, in a thermal environment with gas convection, the thermal insulation effect of the traditional spacecraft's multilayer thermal insulation components is significantly reduced, and the multilayer can no longer meet the ther...

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Problems solved by technology

[0004] Aiming at the defects in the prior art, the purpose of the present invention is to provide a thermal insulation assembly for thermal control of a Mars lander and a preparation method thereof. Thermal insulation problems under the condition of extremely limited environment, energy, weight and other resources

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