Thermal insulation component for thermal control of Mars lander and preparation method thereof

A technology for thermal insulation components and landers, which is applied in the fields of aerospace vehicle heat protection devices, aerospace safety/emergency devices, etc., to achieve the effect of saving resources, excellent thermal insulation performance, and meeting thermal insulation requirements

Active Publication Date: 2016-03-16
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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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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  • Thermal insulation component for thermal control of Mars lander and preparation method thereof

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Embodiment Construction

[0032] The embodiments of the present invention are described in detail below: this embodiment is implemented under the premise of the technical solution of the present invention, and detailed implementation methods and specific operating procedures are provided. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention, and these all belong to the protection scope of the present invention.

[0033] Such as figure 1 As shown, this embodiment firstly provides a thermal insulation assembly for thermal control of a Mars lander, including a thin-layer structure 1, a structural support 2, a first airgel block 3, and a second airgel block 4. Honeycomb 5 and skin 6; the honeycomb core is filled with the second airgel block 4, and the honeycomb 5 is sandwiched between the upper and lower layers of skin 6 to form a honeycomb panel. The second airgel block 4 and the The skin 6 is bonded b...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/58
Inventor 李聪航江世臣姚正平王海涛盛松
Owner SHANGHAI SATELLITE ENG INST
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