Abstract

This paper presents fabrication and testing of a multiple-evaporator and multiple-condenser loop heat pipe (MLHP) with polytetrafluoroethylene (PTFE) porous media as wicks. The MLHP has two evaporators and two condensers in a loop heat pipe in order to adapt to various changes of thermal condition in spacecraft. The PTFE porous media was used as the primary wicks to reduce heat leak from evaporators to compensation chambers. The tests were conducted under an atmospheric condition. In the tests that heat loads are applied to both evaporators, the MLHP was stably operated as with a LHP with a single evaporator and a single condenser. The relation between the sink temperature and the thermal resistance was experimentally evaluated. In the test with the heat load to one evaporator, the heat transfer from the heated evaporator to the unheated evaporator was confirmed. In the heat load switching test, in which the heat load is switched from one evaporator to another evaporator repeatedly, the MLHP could be stably operated. The loop operation with the large temperature difference between the heat sinks was also tested. From this result, the stable operation of the MLHP in the various conditions was demonstrated. It was also found that a flow regulator which prevents the uncondensed vapor from the condensers is required at the inlet of the common liquid line when one condenser has higher temperature and cannot condense the vapor in it.

Highlights

  • As sophistication and diversification of recent space mission, the thermal requirements for spacecraft are getting stricter

  • This research focuses on multiple-evaporator and multiple-condenser loop heat pipes (MLHPs) which have multiple evaporators and condensers in a LHP

  • A small MLHP with PTFE wicks was newly designed and fabricated, and basic performance of the MLHP was experimentally evaluated in an atmospheric condition

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Summary

Introduction

As sophistication and diversification of recent space mission, the thermal requirements for spacecraft are getting stricter. Under such background, a heat transport device with no electric power, named loop heat pipe (LHP) is under development. Ku et al [7] [8] have developed a miniature MLHP with titanium wicks and ammonia as the working fluid, and comprehensive test programs were executed in order to apply a miniature MLHP to ST-8 program. The basic characteristics and advantages of the MLHP for spacecraft thermal control were explained. The test results of the MLHP including the heat loads applied to both evaporators, to only one evaporator, and switched from one evaporator to another evaporator were presented. The test result when the sink temperature on the condensers was different under a constant heat load was presented

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