Low-absorption and low-emission thermal control coating with solar absorption ratio changing along with incident angle and preparation method of low-absorption and low-emission thermal control coating

Abstract

The invention provides a low-absorption and low-emission thermal control coating with a solar absorption ratio changing along with an incident angle and a preparation method of the low-absorption and low-emission thermal control coating. The low-absorption and low-emission thermal control coating comprises the following components in parts by mass: 100 parts of a binder; 120 to 160 parts of filler; 2-3 parts of a catalyst; 5-7 parts of a curing agent; 400 to 500 parts of an organic solvent; 0.51 to 5.5 parts of a surface modifier; wherein the adhesive is hydroxymethyl organic silicon resin, and the molecular weight of the adhesive is 2000 to 10000; the surface modifier is boric acid and a KH550 silane coupling agent; the coating is implemented by adopting an air spraying method, and the thickness is not less than 25 microns. The coating has different solar absorptivity under different solar incident angle conditions, and particularly, the absorptivity under a large incident angle condition is remarkably increased, so that the problem that the temperature is reduced or a large temperature gradient is formed between the coating and a high-temperature part due to the fact that heat flow input of a conventional coating is sharply reduced when the solar oblique incident angle is large is solved. And the high-precision thermal control performance and the structural precision of the surface of the spacecraft are influenced.

Description

technical field [0001] The invention belongs to the technical field of thermal control coatings for spacecraft, in particular to a low-absorption and low-emission thermal control coating whose solar absorption ratio changes with incident angles and a preparation method thereof. Different solar absorption ratios. Background technique [0002] Under space environmental conditions, the thermal control coating on the surface of the spacecraft controls the heat flow into and out of the spacecraft and maintains the surface and internal temperature of the spacecraft. The solar absorption ratio is the ability of the coating to absorb solar heat radiation, and the hemispherical emissivity reflects the ability of the coating to radiate heat to the deep cold space. Affected by the high-vacuum environment, when the spacecraft is working in orbit, the coating will absorb solar radiation and cause the temperature of the spacecraft to rise, and the radiation heat leakage of the coating to...

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the deficiencies in the prior art, the inventor has carried out intensive research and provided a low-absorption and low-emission thermal control system whose solar absorption ratio changes with the incident angle The coating and its preparation method, the coating has different solar absorption ratios under different solar incidence angles, especially the absorptivity significantly increases under the conditions of large incidence angles, which solves the problem of conventional coatings with relatively large oblique incidence angles of the sun. When the heat flow input decreases sharply when it is large, the temperature drops or a large temperature gradient is formed with the high-temperature part, which in turn affects the high-precision thermal control performance and structural accuracy of the spacecraft surface.

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