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A thermal control method for a star-sensitive assembly

An assembly, star-sensing technology, applied in the field of satellite temperature control, can solve the problem of inability to realize the thermal control of star-sensing assemblies, and achieve the effect of low cost and reducing temperature fluctuations

Active Publication Date: 2016-08-24
AEROSPACE DONGFANGHONG SATELLITE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical solution of the present invention is to overcome the deficiencies of the prior art and provide a thermal control method for star-sensitive assemblies. The present invention combines traditional thermal control means such as spraying high-emissivity SR107 by using C-C graphite and other materials as thermal conductive materials. White paint, F46 film, multi-layer heat insulation material, heating sheet, and FRP heat insulation pad solve the problem of thermal control of star-sensitive assemblies that cannot be realized by traditional thermal control methods, and lay a foundation for the normal operation of star-sensitive assemblies in orbit

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  • A thermal control method for a star-sensitive assembly

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Embodiment Construction

[0022] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0023] Such as figure 1 As shown, a thermal control method of a star-sensitive assembly of the present invention comprises the following steps:

[0024] (1) The hood of the star-sensitive assembly is sprayed with anti-static white paint ACR-1, and other parts of the star-sensitive assembly are blackened;

[0025] (2) if figure 2 with image 3 As shown, paste the position of the heating plate on the star-sensitive bracket and the star-sensitive flange of the star-sensitive assembly. figure 2 Paste 2 heaters on the Zhongxingmin bracket, one on the surface of the bracket, one on the back of the cooling surface, on the image 3 Indicates the pasting position of the heating plate on the flange, and the shaded area indicates the adding position of the heating plate;

[0026] (3) A 4mm C-C graphite material is placed between the star s...

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Abstract

A thermal control method for a star-sensitive assembly of the present invention comprises the following steps: spraying anti-static white paint ACR-1 on the shading cover in the star-sensitive assembly, and blackening treatment on other parts of the star-sensitive assembly; Heaters are pasted on the sensitive bracket and the three flanges respectively; C-C graphite material is placed between the star-sensitive assembly and the satellite body; the star-sensitive assembly and the satellite body are installed through glass fiber reinforced plastic gaskets; the star-sensitive assembly A heat dissipation surface is provided on the shaded surface of the star sensitive bracket and the hood, and the coating is applied; except for the heat dissipation surface in the above steps, other parts of the star sensitive assembly are covered with 10 units of multilayer heat insulation components, and the outer surface of the multilayer is Polyimide film. The invention solves the thermal control problem of the star-sensitive assembly which cannot be realized by the traditional thermal control method, and lays a foundation for the normal operation of the star-sensitive assembly on orbit.

Description

technical field [0001] The invention relates to a thermal control method of a star sensor assembly, which is suitable for satellites whose star sensor flanges and supports require thermal control, and belongs to the technical field of satellite temperature control. Background technique [0002] At present, star sensors are gradually used in China for attitude measurement and orbit control. Star sensors are high-precision satellite attitude measurement devices, and their working reliability plays a vital role in satellite attitude control. The star sensor is usually installed outside the satellite. The satellite is affected by factors such as direct sunlight, infrared radiation, and sunlight reflection during the orbit, and its operating temperature changes accordingly. The measurement accuracy of the star sensor optical system is relatively sensitive to temperature. The accuracy of attitude determination is mainly affected by the measurement error of the star sensor. In ord...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22G01C21/24
Inventor 徐志明黎明
Owner AEROSPACE DONGFANGHONG SATELLITE