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Organic thermal control coating with low solar absorptivity and preparation method

A technology of solar absorption ratio and thermal control coating, which can be applied to coatings, devices for coating liquid on surfaces, special surfaces, etc. Achieve the effect of improving stability and reducing solar absorption ratio

Active Publication Date: 2022-01-28
BEIJING SATELLITE MFG FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] (α S =0.16~0.24), the performance of the coating degrades greatly under the influence of vacuum-ultraviolet radiation environment (Δα S =0.30~0.60) makes it necessary to increase the heat dissipation area and reduce the heat dissipation accuracy during the thermal design of the spacecraft, which cannot meet the development needs of the current high-precision and long-life spacecraft

Method used

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Examples

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Effect test

preparation example Construction

[0036] The preparation method of the above-mentioned low solar absorption ratio organic thermal control coating specifically includes the following steps:

[0037] 1) Preparation of primer coating: add diluent, zinc orthotitanate filler and glass beads to the space-stable silicone resin, mix and sand evenly;

[0038] 2) Preparation of intermediate coating: add diluent, rare earth oxide filler and glass beads to steric stable silicone resin, mix and sand evenly;

[0039] 3) Preparation of top coat paint: add diluent, zinc oxide filler and glass beads to the steric stable silicone resin, mix and sand evenly;

[0040] 4) Coating preparation: Spray the surface treatment agent on the surface of the substrate and cure it at room temperature for 0.5-1 hour. Spray the base coat paint and cure it at room temperature for 0.5~1h. Spray the middle coat paint and cure it at room temperature for 0.5~1h. The organic thermal control coating with low solar absorption ratio can be obtained b...

Embodiment 1

[0051] The specific preparation method of the low solar absorption ratio organic thermal control coating of the present embodiment comprises the following steps:

[0052] 1) Preparation of primer coating: Add zinc orthotitanate filler with a particle size of 1 μm, butyl acetate diluent and glass beads with a particle size of 1 μm to the RTV silicone resin, and disperse by ball milling for 0.5 h. According to the mass ratio: the zinc orthotitanate filler is 3 times that of the silicone resin, the butyl acetate is 1.1 times the total mass of the silicone resin and zinc orthotitanate, and the glass beads are 1.2 times the total mass of the silicone resin and zinc orthotitanate .

[0053] 2) Intermediate coating preparation: Add europium oxide filler with a particle size of 3 μm, butyl acetate diluent and glass beads with a particle size of 1 μm to the RTV silicone resin, and disperse by ball milling for 0.5 h. According to the mass ratio: the europium oxide filler is 3 times tha...

Embodiment 2

[0063] The specific preparation method of the low solar absorption ratio organic thermal control coating of the present embodiment comprises the following steps:

[0064] 1) Preparation of primer coating: Add zinc orthotitanate filler with a particle size of 2 μm, xylene diluent and glass beads with a particle size of 2 μm into the RTV silicone resin, and disperse by ball milling for 1.5 h. According to the mass ratio: the zinc orthotitanate filler is 4 times of the organic silicon resin, the xylene is 1.2 times of the total mass of the organic silicon resin and the zinc orthotitanate, and the glass beads are 1.3 times of the total mass of the organic silicon resin and the zinc orthotitanate.

[0065] 2) Preparation of middle coat paint: add lanthanum oxide filler with a particle size of 4 μm, xylene diluent and glass beads with a particle size of 2 μm to the RTV silicone resin, and disperse by ball milling for 1.5 h. According to the mass ratio: the lanthanum oxide filler is ...

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Abstract

The invention relates to an organic thermal control coating with low solar absorptivity and a preparation method. The coating comprises a bottom coating, a middle coating and a surface coating. The bottom coating, the middle coating and the surface coating all take space-stable organic silicon resin as an adhesive; zinc orthotitanate is selected as a coating filler in the bottom coating, the zinc orthotitanate is spherical, the particle size is 1-3 microns, the purity is greater than or equal to 99.99%, and the pigment-agent ratio is 3-5; the middle coating adopts a rare earth oxide as a coating filler, the rare earth oxide is one or more of lanthanum oxide, europium oxide, yttrium oxide, samarium oxide and gadolinium oxide, the rare earth oxide is spherical, the particle size is 3-5 microns, the purity is greater than or equal to 99.99%, and the pigment-agent ratio is 3-5; the surface coating selects zinc oxide as a coating filler, the zinc oxide is spherical, the particle size of the filler is 50-200nm, the purity is greater than or equal to 99.99%, and the pigment ratio is 1.5-3.5. The scattering capability of different spectral energy of sunlight and the vacuum ultraviolet radiation stability are greatly improved, so that the design requirements of high precision and long service life of a modern novel spacecraft can be met.

Description

technical field [0001] The invention relates to a low solar absorption ratio organic thermal control coating and a preparation method thereof, belonging to the technical field of spacecraft thermal control materials. Background technique [0002] The thermal control coating is an important part of the passive thermal control system of the spacecraft. It is the main means to realize the heat exchange between the spacecraft and the space environment. It can maintain the surface energy absorption and radiation of the spacecraft through the thermal radiation performance of the coating itself. balance, so that the spacecraft reaches the ideal operating temperature. Low solar absorption ratio organic thermal control coating is widely used in spacecraft, which can effectively scatter the energy of sunlight, and has good construction and substrate adaptability. With the vigorous development of modern aerospace technology, the depth and breadth of spacecraft exploration tasks contin...

Claims

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Application Information

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IPC IPC(8): B05D5/06B05D1/38B05D7/24
CPCB05D5/06B05D5/061B05D1/38B05D7/586B05D7/24B05D2601/20B05D2518/10
Inventor 张杭张家强白晶莹崔庆新王兵存张立功孙浩然郑琰
Owner BEIJING SATELLITE MFG FACTORY
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