Simply constructed heat transfer device for stand-alone radiating of space vehicle

A space vehicle and heat transfer technology, which is applied to the cooling system of the power plant, etc., can solve the problems of complex system and occupy a lot of overall resources, and achieve the effect of good heat transfer effect, sufficient heat transfer capacity and high reliability.

Inactive Publication Date: 2011-06-01
SHANGHAI SATELLITE ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the above-mentioned deficiencies such as the complexity of the prior art system and the large occupation of overall resources, the purpose of the present invention is to provide a simple heat transfer device for the heat dissipation of a space vehicle stand-alone

Method used

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  • Simply constructed heat transfer device for stand-alone radiating of space vehicle
  • Simply constructed heat transfer device for stand-alone radiating of space vehicle
  • Simply constructed heat transfer device for stand-alone radiating of space vehicle

Examples

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Embodiment Construction

[0016] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings.

[0017] figure 1 It is a schematic structural diagram of a simple heat transfer device used for heat dissipation of a single aircraft of a space vehicle according to the present invention, figure 1 B is figure 1 A-direction view of A; the unit includes:

[0018] The contact area between the hot end heat spreader 3 and the stand-alone mounting plate 4 and between the cold end heat spreader 7 and the radiator 8 is coated with thermally conductive silicone grease, and the hot end heat spreader 3 and the cold end heat spreader 7 are installed with external stickers The area of ​​the heat pipe 5 is slotted, and the outer heat pipe 5 is fixed by the hot end cover plate 2 and the cold end cover plate 6; The filler, the thermally conductive filler is indium foil with a thickness of 0.017mm, which is coated with vacuum silicone grease and installed between ...

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PUM

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Abstract

The invention discloses a simply constructed heat transfer device for stand-alone radiating of a space vehicle, which comprises an outer stuck heat pipe [5], a heat end heat-expansion plate [3], a cold end heat-expansion plate [7], a radiator [8], a heat end cover plate [2] and a cold end cover plate [6], wherein the outer stuck heat pipe [5] transmits the heat of the stand-alone [1] to the radiator [8]; the heat end cover plate [2] and the cold end cover plate [6] are used for fixing the outer stuck heat pipe [5]; and the heat end heat-expansion plate [3] and the cold end heat-expansion plate [7] are used for enhancing the heat transfer effect of the outer stuck heat pipe [5]. According to the invention, the problem of radiating an efficient heat transfer channel of the stand-alone of the space vehicle is solved, and the beneficial effects such as low cost, high reliability, good heat transfer effect and the like, are achieved.

Description

technical field [0001] The invention relates to a simple heat transfer device for dissipating heat from a single aircraft of a space vehicle. Background technique [0002] In the thermal control system of the spacecraft, it is often necessary to take thermal insulation or heat dissipation measures for some instruments and components, and to adjust the temperature of the single machine as much as possible within the temperature index range suitable for its work. For most single machines in the satellite, the heat dissipation requirements can be guaranteed by opening the cooling surface on the single machine installation board. But for some special stand-alone machines, such as satellite gyroscopes, drive mechanisms, etc., stand-alone machines require high installation accuracy, high power consumption, and high temperature indicators. In order to meet its electrical performance requirements, its installation location often cannot take into account the heat dissipation require...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/10
Inventor 姚正平于迎军胡明亮
Owner SHANGHAI SATELLITE ENG INST
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