Truss heat pipe and hoop heat pipe coupling heat transfer assembly for spacecraft

Abstract

The invention discloses a truss heat pipe and hoop heat pipe coupling heat transfer assembly for a spacecraft. The assembly comprises a heat exchanger shell (2), a heat exchanger core, a packaging end(1), a transfer joint (4) and end covers (3). The heat exchanger shell (2) and a loop heat pipe condensation pipeline are coupled in a coil pipe welding manner, the heat exchanger core and the heat exchanger shell (2) are coupled in an inserting manner of circumferential fins (11), one end of the heat exchanger core is connected with a truss heat pipe shell (5) through the transfer joint (4), theother end of the heat exchanger core is sealed through the packaging end (1), the heat exchanger core is mounted in the heat exchanger shell (2), inner side fins of the heat exchanger shell (2) and outer side fins (11) of the heat exchanger core are coupled in an inserted manner, the coupling portion is coated with thermally conductive silicone grease, and the two ends of the heat exchanger shell(2) are packaged through the end covers (3), and the heat exchanger core, the transfer joint (4), the truss heat pipe shell (5) and the packaging end (1) are in sealed connection, so that a seal system is formed.

Description

technical field [0001] The invention belongs to the technical field of vapor-liquid phase change heat transfer for spacecraft, and relates to a heat transfer component for coupling a truss heat pipe and a loop heat pipe. Background technique [0002] With the development of spacecraft towards a comprehensive and integrated system, the increase in the number of spacecraft payloads and the multi-channel and multi-angle development of a single load have increasingly put forward higher demands on power consumption resources. Due to the limitation of orbital power generation, it is impossible to meet the increasing demand for power consumption resources without limit. In this case, the concept of spacecraft thermal management highlights its advantages. An important feature of the spacecraft thermal management concept is to conduct unified allocation and comprehensive utilization of the spacecraft's thermal environment and subsystem thermal behavior from a system perspective, so a...

AI Technical Summary

Problems solved by technology

This leads to, on the one hand, due to the long pipeline required, the flow resistance that the loop heat pipe capillary pump needs to overcome is very large, which will reduce its maximum heat transfer power; Welding coupling cannot be realized between the condensing pipes and the composite panel, and the heat conduction resistance between the condensing pipe and the composite panel is very large, which reduces the heat consumption efficiency of the refrigerator

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