小川 博之

Loop Heat Pipes (LHPs) have been used in thermal control of spacecraft as next generation heat transport devices. Recently, multiple-evaporators LHP (MLHP) is under studied since the MLHP supplies autonomous thermal control function. However, some physical phenomena in the MLHP have not been clarified yet. The purpose of this study is to clarify thermal behavior of the MLHP under the microgravity. The MLHP used in this research has two evaporators and one condenser. Distilled water is used as the working fluid. 40W/40W, 80W/80W, 120W/0W, 0W/120W heat load were applied during the test. This experiment was conducted under microgravity for about 20 seconds, which was realized by parabolic flight. The vapor-liquid distribution in the wick core and the compensation chamber (CC) under the microgravity is presented. The effect of the microgravity for the working the MLHP is also discussed. The heat distributions in the MLHP when one and both evaporators were heated is also clarified

第30回宇宙構造・材料シンポジウム（2014年12月1日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)), 相模原市, 神奈川県資料番号: SA6000043001レポート番号: A01

大気球シンポジウム 平成26年度（2014年11月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県著者人数: 37名資料番号: SA6000021002レポート番号: isas14-sbs-002

A lunar long duration method which utilizes a characteristic of a very low thermal conductivity of lunar regolith has been proposed. The principle of this method is to put heater in desired depth of the regolith and heat up the regolith layer during lunar daytime. Because of the very low thermal conductivity of regolith, stored heat in regolith propagates gradually and raises the surface temperature at cold lunar night. By this method, a lunar lander will be kept warm passively during cold lunar night. In this paper, a temporospatially small-scale experimental apparatus which simulate lunar surface environment was fabricated and thermal cycling condition and heater setting position was calculated by comparing lunar environment, and thermophysical properties of the lunar regolith and regolith simulant used in this work. The feasibility of a passive thermal control method with no electrical power during lunar night time was evaluated.

Thermal performance of an O-shaped Oscillating Heat pipe (OHP) for balloon-borne General Anti-Particle Spectrometer (GAPS) experiment has been investigated. The developed OHP is a closed type and O-shaped for using the gravity assist. R410A is selected as the working fluid for the use at low temperatures. At -50 deg-C, we achieved a thermal conductance of 20 W/K for 150 W heat input with 32 loops and -40 deg-C heating section. We also found for the first time that this large-scale OHP can be operated at low temperatures. It is found that this OHP can satisfy the GAPS thermal control requirement.

平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県形態: カラー図版あり形態: PDF著者人数: 18名資料番号: AA0061856051レポート番号: STCP-2012-051