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NoveL thermaL controL device for spatiaL fLexibLe mechanism

A flexible mechanism and thermal control technology, which is applied in the direction of electric heating devices, aerospace safety/emergency devices, space vehicle radiation protection devices, etc., to achieve the effect of meeting the rotation requirements

Active Publication Date: 2018-11-23
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problems of low temperature compensation, high temperature protection and radiation resistance of space flexible mechanisms that cannot be solved under conventional thermal control measures, the present invention provides a new type of thermal control device for space flexible mechanisms, which is suitable for flexible mechanisms with various shapes outside the cabin Low temperature compensation, high temperature protection and anti-radiation requirements for overall cladding

Method used

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  • NoveL thermaL controL device for spatiaL fLexibLe mechanism

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Embodiment Construction

[0014] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0015] Such as figure 1 As shown, the embodiment of the present invention provides a novel thermal control device for a space flexible mechanism, including a film-type temperature-control heating belt 3 that is fully bonded to the mechanism through GD414C silicone rubber 4, and wrapped around the film-type temperature-control heating belt 3 The copper-nickel plain weave conductive cloth 2 and the F46 thin-film silver-plated secondary surface mirror 1 wound on the outermost surface also include a t...

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Abstract

The invention discLoses a noveL thermaL controL device for a spatiaL fLexibLe mechanism, which comprises a fiLm type temperature controL heating beLt, copper nickeL pLain conductive cLoths and a F46 fiLm siLver pLating secondary surface mirror. The fiLm type temperature controL heating beLt is adhered and wound on the fLexibLe mechanism through GD414C siLicon rubber; 6 Layers of copper nickeL pLain conductive cLoth are wound on the fiLm type temperature controL heating beLt; a Layer of F46 fiLm siLver pLating secondary surface mirror is wound on the surface of the copper nickeL pLain conductive cLoths. By utiLizing the copper nickeL pLain conductive cLoth and the F46 fiLm siLver pLating secondary surface mirror, the spatiaL fLexibLe mechanism is integraLLy covered, not onLy can the externaL heat fLow be prevented, but aLso the irradiation is resisted, meanwhiLe, the power of the temperature controL heating beLt can be effectiveLy reduced and the energy can be saved. Moreover, the fiLmtype temperature controL heating beLt, the copper nickeL pLain conductive cLoth and the F46 fiLm siLver pLating secondary surface mirror are fLexibLe, and can be appLied to spatiaL fLexibLe mechanismswith various structures, incLuding rotating cabLes and the Like.

Description

technical field [0001] The invention relates to thermal control products for space vehicles, in particular to a novel thermal control device for space flexible mechanisms. Background technique [0002] The thermal control measures of conventional satellite extravehicular space flexible mechanisms (such as extravehicular cables, flexible waveguides, etc.) are mainly to cover the outer surface with multi-layer heat insulation components. However, due to the rotation requirements of some external cables or movable flexible waveguides, a certain temperature needs to be maintained to meet the rotation requirements, and low temperature compensation must be performed. At this time, conventional measures cannot meet the thermal control requirements. Some flexible waveguides outside the cabin have high internal heat consumption, and the multi-layer heat insulation components cannot dissipate internal heat dissipation, and conventional thermal control measures cannot meet the thermal ...

Claims

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Application Information

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IPC IPC(8): B64G1/52B64G1/54H05B1/02H05B3/58H05K9/00G02B5/08
CPCB64G1/52B64G1/54G02B5/08H05B1/0202H05B3/58H05K9/0081
Inventor 孙伟伟赵吉喆杜忠选顾燕萍徐涛翟载腾曹建光
Owner SHANGHAI SATELLITE ENG INST
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