Thermotropic phase-change thermal-control skin based on near-field thermal radiation and application thereof in spacecraft

A thermally induced phase change and thermal radiation technology, applied in sputtering coating, ion implantation coating, metal material coating process, etc., can solve thermally induced phase change material deposition, performance degradation, small emissivity adjustment range question

Active Publication Date: 2019-08-02
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the reported thermal phase change thermal control technology has one or more problems as follows: (1) The thermal phase change material is deposited on the outermost layer of the device
At this time, when the thermally induced phase change material is directly exposed to outer space, the complex space environment such as atomic oxygen and proton electron

Method used

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  • Thermotropic phase-change thermal-control skin based on near-field thermal radiation and application thereof in spacecraft
  • Thermotropic phase-change thermal-control skin based on near-field thermal radiation and application thereof in spacecraft
  • Thermotropic phase-change thermal-control skin based on near-field thermal radiation and application thereof in spacecraft

Examples

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Embodiment 1

[0058] A kind of heat-induced phase change thermal control skin, including base 1, inner layer film system 2, outer layer film system 3 and optical solar reflector 4 from bottom to top, and between inner layer film system 2 and outer layer film system 3 has The spacer 5, the spacer 5 forms a vacuum gap 6 with a pitch of micronano scale between the inner layer film system 2 and the outer layer film system 3, and the inner layer film system 2 contains a thermally induced phase change Thermally induced phase change film layer composed of materials.

[0059] Specifically, the material of substrate 1 is SiO 2 , the inner film system 2 is single-layer VO 2 The thin film, with a film thickness of 200nm, is coated by magnetron sputtering. The CMO-based OSR produced by the British Point-source company is selected as the optical solar reflector 4, its infrared emissivity ε = 0.87, and the solar spectral absorptivity α s =0.085, the outermost layer of the selected optical solar reflec...

Embodiment 2

[0062] A kind of heat-induced phase change thermal control skin, including base 1, inner layer film system 2, outer layer film system 3 and optical solar reflector 4 from bottom to top, and between inner layer film system 2 and outer layer film system 3 has The spacer 5, the spacer 5 forms a vacuum gap 6 with a pitch of micronano scale between the inner layer film system 2 and the outer layer film system 3, and the inner layer film system 2 contains a thermally induced phase change Thermally induced phase change film layer composed of materials.

[0063] Specifically, the material of substrate 1 is SiO 2 , the inner film system 2 is single-layer VO 2 Thin film, with a film thickness of 100nm, is coated by magnetron sputtering. The CMO-based OSR produced by the British Point-source company is selected as the optical solar reflector 4, its infrared emissivity ε = 0.87, and the solar spectral absorptivity α s = 0.085. Plating a layer of silver (Ag) base film and a layer of in...

Embodiment 3

[0066] A kind of heat-induced phase change thermal control skin, including base 1, inner layer film system 2, outer layer film system 3 and optical solar reflector 4 from bottom to top, and between inner layer film system 2 and outer layer film system 3 has The spacer 5, the spacer 5 forms a vacuum gap 6 with a pitch of micronano scale between the inner layer film system 2 and the outer layer film system 3, and the inner layer film system 2 contains a thermally induced phase change Thermally induced phase change film layer composed of materials.

[0067] Specifically, the material of the substrate 1 is SiC, and the inner film system 2 includes an inner layer of VO 2 film and an outer layer of SiC film, where VO 2 The film thickness of the film is 100 nm, the film thickness of the SiC film is 20 nm, and the film is deposited by magnetron sputtering. The CMO-based OSR produced by the British Point-source company is selected as the optical solar reflector 4, its infrared emissi...

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Abstract

The invention relates to a thermotropic phase-change thermal-control skin based on near-field thermal radiation and an application thereof in a spacecraft. The thermotropic phase-change thermal-control skin comprises a substrate, an inner-layer film system, an outer-layer film system and a protective layer from bottom to top, a spacer is arranged between the inner-layer film system and the outer-layer film system, and a vacuum gap with the interval of micro-nano magnitude is formed between the inner-layer film system and the outer-layer film system; and the inner-layer film system comprises athermotropic phase-change film layer composed of a thermotropic phase-change material; and the protective layer has high infrared emissivity or high infrared emissivity and low solar spectrum absorption rate. On one hand, the thermotropic phase-change thermal-control skin has good space environment adaptability, the problem of performance degradation caused by direct exposure of the phase-change material to the space environment is solved, and on the other hand, a large emissivity adjusting range in a narrow-temperature region can be provided, and the thermotropic phase-change thermal-controlskin can be applied to the spacecraft.

Description

technical field [0001] The invention relates to the technical field of thermal control devices, in particular to a thermal phase change thermal control skin based on near-field thermal radiation and its application in spacecraft. Background technique [0002] Spacecraft will face complex and changeable space thermal environment during its orbital operation, and its thermal environment will change drastically with the difference of thermal boundary conditions and internal thermal state. Effective thermal control of the spacecraft to keep it in an appropriate temperature range under any working conditions is a key factor to ensure the normal, continuous and reliable operation of the spacecraft. [0003] Among various thermal control technologies, thermal phase change thermal control utilizes the characteristics of optical properties of thermal phase change materials that change with temperature to intelligently and autonomously adjust the emissivity of thermal control devices ...

Claims

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Application Information

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IPC IPC(8): C23C14/35C23C14/08C23C14/10C23C14/06
CPCC23C14/0635C23C14/083C23C14/086C23C14/10C23C14/35
Inventor 赵军明徐德宇裘俊
Owner HARBIN INST OF TECH
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