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A kind of preparation method of composite thermal control coating on alloy surface

A technology of thermal control coating and surface compounding, applied in the direction of surface reaction electrolytic coating, device for coating liquid on the surface, coating, etc., to achieve the effect of reducing cost, ensuring binding force, and improving binding force

Active Publication Date: 2021-04-02
NO 12 RES INST OF CETC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0012] The invention prepares a composite thermal control coating with low solar absorptivity and high emissivity on the surface of the alloy by spraying inorganic thermal control white paint on the surface of micro-arc oxidation, which can not only overcome the disadvantages of micro-arc oxidation and inorganic thermal control white paint thermal control coating Disadvantages, and it is easy to make its surface solar absorptivity α S If it falls below 0.2, this method becomes the optimal technical choice for the surface treatment of radiators of space power devices, and this method is suitable for the treatment of low-absorption and high-radiation composite thermal control coatings on the surface of alloys and magnesium alloys

Method used

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  • A kind of preparation method of composite thermal control coating on alloy surface
  • A kind of preparation method of composite thermal control coating on alloy surface
  • A kind of preparation method of composite thermal control coating on alloy surface

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Embodiment 1

[0063] In this embodiment, a 2A12 aluminum alloy test piece with a size of 60×60×2mm is selected to prepare a composite thermal control coating on the surface of the alloy, including the following steps:

[0064] 1. Surface pretreatment of aluminum alloy parts:

[0065] It is mainly to remove the oil and oxide layer on the surface of the parts to expose the clean surface. The cleaning is mainly alkaline cleaning.

[0066] The aluminum alloy parts are immersed in a sodium hydroxide solution with a mass fraction of 1%-10% for 1-2 minutes, superwashed in deionized water for 1-10 minutes, rinsed with deionized water for 4-6 times, dehydrated and dried.

[0067] 2. Micro-arc oxidation:

[0068] Prepare a composite electrolyte system, in which disodium hydrogen phosphate is 60g / L, sodium phosphate 8g / L, potassium silicate 50g / L and sodium silicate 20g / L, and KOH is added to adjust the pH to 8-9, which will be processed in step 1 The final aluminum alloy parts are placed in the tan...

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Abstract

The invention discloses a preparation method of a composite thermal-control coating on an alloy surface. The preparation method comprises the following steps that micro-arc oxidation treatment is conducted on an alloy part; priming paint is sprayed on a film formed through micro-arc oxidation treatment; and finish paint is sprayed on the priming paint, so that the composite thermal-control coatingis obtained. According to the preparation method of the composite thermal-control coating on the alloy surface, inorganic thermal-control white paint is sprayed on the surface subjected to micro-arcoxidation to prepare the composite thermal-control coating, with low solar absorptivity and high emissivity, on the alloy surface so that the defects of a micro-arc oxidation coating and an inorganicthermal-control white paint coating can be overcome, and the solar absorptivity alpha S of the alloy surface can be easily decreased to be less than 0.2; and the preparation method becomes the optimaltechnique choice for surface treatment of radiators of spatial power devices.

Description

technical field [0001] The invention relates to an alloy surface composite thermal control coating treatment technology. More specifically, it relates to a method for preparing a composite thermal control coating on an alloy surface. Background technique [0002] When space power devices are in orbit, due to the long-term exposure to the alternating changes of solar radiation and the shady side, the temperature on the sunny side is as high as 200 ° C, and the temperature on the back side is too low, and the ambient temperature experienced can be as high as hundreds of degrees. In addition, due to environmental factors such as solar radiation and particle irradiation, high temperature and temperature gradients are easily formed on the surface and on the surface of the equipment in the star, which will lead to deterioration of the internal working environment and damage or malfunction of the spacecraft. , the spacecraft must be carefully designed for thermal control. The ther...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C25D11/06C25D11/16C25D11/30B05D3/02B05D3/04B05D3/10B05D3/12B05D7/00B05D7/14
CPCB05D3/0218B05D3/0486B05D3/102B05D3/12B05D7/14B05D7/586B05D2202/20B05D2202/25C25D11/026C25D11/06C25D11/16C25D11/30
Inventor 陈廷伟瞿波梁晓峰田志英梁文龙宋磊
Owner NO 12 RES INST OF CETC
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