Phase-change material and metal micro-expansion-based dual-drive space thermal switch for spacecraft

Abstract

The invention discloses a phase-change material and metal micro-expansion-based dual-drive space thermal switch for a spacecraft. The dual-drive space thermal switch comprises a heat sink plate, a phase-change material storage shell, a phase-change material, a storage shell cover plate and a support shell, the heat sink plate is installed at the lower end of the supporting shell, the upper end ofthe phase-change material storage shell is connected with the upper end of the supporting shell, and the lower end of the phase-change material storage shell is located in the supporting shell. The phase-change material is positioned in the phase-change material storage shell; the storage shell cover plate is hermetically mounted on an opening in the upper end of the phase-change material storageshell and is sealed; the outer diameter below the upper end of the phase-change material storage shell is smaller than the inner diameter of the supporting shell; the phase-change material storage shell is filled with the phase-change material; the lower end of the heat sink plate is tightly attached to the inner side end of a heat dissipation panel of the spacecraft spaceborne instrument; and thephase-change material storage shell and the storage shell cover plate are tightly attached to the outer side hot end face of a heating device in the spacecraft spaceborne instrument. According to theinvention, the problem of insufficient driving force in the existing equipment is effectively solved, and higher thermal conductivity when the thermal switch is switched on and lower thermal conductivity when the thermal switch is switched off can be ensured.

Description

technical field [0001] The invention relates to the technical field of thermal control equipment for spacecraft, in particular to a dual-drive space thermal switch for spacecraft based on phase change materials and metal micro-expansion. Background technique [0002] With the continuous advancement of aerospace technology, the size of satellite (satellite)-borne instruments is in the trend of miniaturization, high power consumption and modularization. The deeper the depth, the greater the fluctuation of the peak heat flux and heat consumption when the corresponding instruments are working. Therefore, the requirements for the thermal control of the control instruments and the operating temperature of the key components used by the spacecraft are also getting higher and higher. The heat transfer process of thermal controls inside most spacecraft is mainly radiation and heat conduction. Heat conduction and radiation heat transfer also affect the heat distribution and temperatur...

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the structural limitation of space thermal switches used in existing spacecraft, micro-expansion thermal switches are prone to cold welding or contact thermal resistance reduction. Instrument temperature control, and paraffin-driven thermal switch, because the driving force of paraffin expansion to accommodate its metal shell is not strong, resulting in the tightness of the contact surface with the heat sink (that is, the metal sheet that is in contact with the hot end surface of the thermal control equipment, etc.) Not enough, the heat conduction is small when it is turned on, and there are complex structures, high design and manufacturing costs, which are not conducive to the multi-scenario application of the product, and the application has limitations. The present invention provides a thermal switch that combines the advantages of metal micro-expansion, And use n-hexadecane with better phase change performance as the basic material. In the application, it can not only effectively solve the problem of insufficient driving force, but also ensure that the thermal switch has a higher thermal conductivity when it is turned on and a better thermal conductivity when it is turned off. Low thermal conductivity, filling the phase change material as the driving source, can also effectively smooth the temperature mutation phenomenon after the thermal switch is turned on, and the structure is simple and compact, and the phase change material and metal material are more replaceable, which is convenient for designing into a module It can design a series of thermal switches with wider temperature control range, effectively reduce the complexity of design, greatly increase the usability of thermal switches, and enrich the product use scenarios based on phase change materials and metal micro-expansion spacecraft. Dual drive space heat switch

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