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Preparation method of conductive thermal control coating with low solar absorption rate and high emissivity on aluminum alloy surface

A technology of solar absorptivity, aluminum alloy surface, applied in surface reaction electrolytic coating, metal material coating process, coating, etc. applied effect

Active Publication Date: 2019-07-26
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention aims to solve the technical problem that the existing aluminum alloy surface treatment technology cannot prepare an integrated film layer of conductive thermal control coating that meets the requirements of space ultraviolet radiation and electron radiation, and provides a low solar absorption rate on the surface of aluminum alloy Preparation method of high emissivity conductive thermal control coating

Method used

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  • Preparation method of conductive thermal control coating with low solar absorption rate and high emissivity on aluminum alloy surface
  • Preparation method of conductive thermal control coating with low solar absorption rate and high emissivity on aluminum alloy surface
  • Preparation method of conductive thermal control coating with low solar absorption rate and high emissivity on aluminum alloy surface

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specific Embodiment approach 1

[0015] Specific implementation mode 1: The preparation method of the thermal control coating with low solar absorption rate and high emissivity on the surface of aluminum alloy of this embodiment is carried out according to the following steps:

[0016] 1. Surface pretreatment of aluminum alloy parts: immerse the aluminum alloy parts in a sodium hydroxide solution with a concentration of 15-100g / L, then keep it warm for 15-100s at 70-90°C, and rinse with clean water for 3-5 times. Rinse 3-5 times with distilled water and dry;

[0017] 2. Preparation of electrolyte: the concentration of the main film-forming agent is 10g / l-100g / l, the concentration of the auxiliary film-forming agent is 1g / l-10g / l, the concentration of the pH regulator is 5g / l-20g / l, zinc salt The concentration of the complexing agent is 10g / l~80g / l, the concentration of the complexing agent is 20g / l~100g / l, weigh the main film forming agent, auxiliary film forming agent, pH regulator, zinc salt, complexing age...

specific Embodiment approach 2

[0020] Embodiment 2: This embodiment differs from Embodiment 1 in that the models of the aluminum alloys described in step 1 are 2024, 6061 and 7075 aluminum alloys. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0021] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the main film-forming agent described in step 2 is one or both of sodium tripolyphosphate and sodium silicate in any ratio. Others are the same as in the first or second embodiment.

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Abstract

The invention provides a preparation method of an aluminum alloy surface conductive thermal control coating with low solar absorptivity and high emissivity, and relates to the preparation method of the aluminum alloy surface conductive thermal control coating. The preparation method aims at solving the technical problems that a conductive thermal control coating integrated film meeting the requirements of space ultraviolet radiation and electron radiation cannot be prepared with the existing aluminum alloy surface treatment technology. The method includes the steps of 1, surface pre-treatmentof an aluminum alloy part; 2, preparation of electrolyte; 3, pulse micro-arc oxidation; and 4, magnetron sputtering. The thickness of the prepared aluminum alloy surface conductive thermal control coating with low solar absorptivity and high emissivity is 20-100 micrometers, and the roughness of the prepared aluminum alloy surface conductive thermal control coating with low solar absorptivity andhigh emissivity is 2.0-12.0 micrometers; and the solar absorptivity is 0.35-0.42, the emissivity is 0.88-0.92, the value of alpha s / epsilon is about 0.4, the surface resistivity is 1*10<-5> Ohm.cm, the dual requirements of thermal control and static resistance of spacecrafts are met, and the conductive thermal control coating can be used for spacecraft structures.

Description

technical field [0001] The invention relates to a preparation method of a conductive thermal control coating on the surface of an aluminum alloy. Background technique [0002] Due to environmental factors such as solar radiation and particle irradiation, the spacecraft operating in orbit can easily form high temperature and temperature gradients on its surface and on the surface of the equipment in the star, which will lead to the deterioration of the internal working environment, causing the spacecraft to be damaged or not working properly. , therefore, the spacecraft must be carefully designed for thermal control. The thermal control coating is a main way to achieve passive thermal control. s ) and emissivity (ε) to adjust the surface temperature of the spacecraft, the average temperature of the outer surface of the spacecraft is related to α s The / ε value is proportional to the relationship, and the thermal control coating with low absorption rate and high emissivity ca...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C28/04C23C14/08C23C14/35C25D11/06C25D11/16
CPCC23C14/081C23C14/35C23C28/042C25D11/06C25D11/16
Inventor 吴晓宏李涛卢松涛李杨秦伟
Owner HARBIN INST OF TECH
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