Thermal insulation component for thermal control of Mars lander and preparation 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 heat insulation component, in particular to a heat insulation component for thermal control of a Mars lander and a preparation method thereof. Background technique [0002] CO on the surface of Mars 2 Atmosphere, harsh sandstorms, wind speed of 2-20m / s, and temperature range of -130°C to +30°C. Affected by the thermal environment on the surface of Mars, there are convection, radiation, and contact with the Martian ground between the Mars lander and the external environment. Various heat transfer methods such as heat conduction. In order to cope with the thermal environment on the surface of Mars where the temperature changes drastically and there are multiple heat transfer methods, the heat insulation device is very critical. However, in the thermal environment with gas convection, the heat insulation effect of traditional spacecraft multi-layer heat insulation components is significantly reduced, and the multi-layer can no...

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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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