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A cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft

A countercurrent loop and cylindrical technology, which is applied in the field of spacecraft thermal control, can solve problems such as difficult liquid reservoir temperature detection, achieve the effects of increasing the contact area, saving on-orbit resources, and improving heat transfer

Active Publication Date: 2021-07-09
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In addition, the temperature sensor of the traditional loop heat pipe reservoir is pasted on the outer wall of the reservoir, making it difficult to accurately detect the temperature of the reservoir

Method used

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  • A cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft
  • A cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft
  • A cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft

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Embodiment Construction

[0025] Aiming at the problem of backflow of working medium caused by the temperature change of the cooling surface of the existing space loop heat pipe system from high to low, a cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft is proposed, which has good heat transfer performance. At the same time, it can effectively prevent the backflow of liquid-phase working fluid.

[0026] like Figure 1 to Figure 5 As shown, the cylindrical anti-backflow loop heat pipe capillary pump assembly for spacecraft includes: backflow compensation device 1, serpentine tube 5, temperature measuring tube 11, backflow tube 4, liquid return tube 10, capillary core 6, evaporator 7, storage Liquid container 12;

[0027] The liquid reservoir 12 is connected to the evaporator 7, part of the capillary 6 is installed in the liquid reservoir 12, and the other part is installed in the evaporator 7; the bottom port of the backflow compensation device 1 is connected to the liqui...

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PUM

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Abstract

A cylindrical anti-reverse flow loop heat pipe capillary pump assembly for spacecraft, comprising: a reverse flow compensation device, a serpentine tube, a temperature measuring tube, a reverse flow tube, a liquid return tube, a capillary core, an evaporator, and a liquid storage device; The evaporator is connected, part of the capillary wick is installed in the accumulator, and the other part is installed in the evaporator; the bottom port of the countercurrent compensation device is connected to the liquid return pipe; the A port of the countercurrent compensation device is connected to one end of the serpentine tube, and the serpentine tube It is located inside the accumulator, surrounding the capillary core, and the other end of the serpentine tube extends into the capillary core; the B port of the countercurrent compensation device is connected to one end of the countercurrent pipe; the other end of the countercurrent pipe has several through holes, which are inserted into the accumulator. And communicate with the inside of the accumulator; the temperature measuring tube is inside the accumulator. The invention has an anti-backflow structure, which has good heat transfer performance and can effectively prevent the back-sucking and reverse-flow of the liquid phase working medium, realizes the temperature measurement inside the liquid storage tank, and the temperature measurement of the liquid storage tank is more accurate.

Description

technical field [0001] The invention relates to a loop heat pipe capillary pump assembly and belongs to the technical field of spacecraft thermal control. Background technique [0002] Loop heat pipe (LHP) is a two-phase fluid loop system that uses capillary force to drive the circulation of working fluid to complete heat exchange. It quickly transfers the heat from the heat source to the heat sink through flexible pipes. When the evaporator is loaded with driving heat, the internal liquid-phase working medium becomes gas-phase working medium, and pressure is generated at the same time. The pressure pushes the gas-phase working medium into the gas-phase pipeline, and enters the condensation pipeline on the heat dissipation surface along the gas-phase pipeline, and condenses into gas-liquid two-phase working medium and liquid-phase working medium in turn in the condensation pipeline, and the liquid-phase working medium flows along the liquid phase. The line enters the evapor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F28D15/04F28D15/02F28D15/06
CPCF28D15/0266F28D15/043F28D15/06
Inventor 杨涛刘昭高腾赵石磊赵振明孟庆亮张焕冬申春梅黄伟史娇红姜海滨曹东晶
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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