Abstract
This study describes the proposal, fabrication, testing, and demonstration of a new thermal control device called a heat storage panel (HSP) for micro/nano-satellites. The HSP consisted of a phase change material (PCM) and a thin panel-shaped container made of a high-thermal-conductivity pitch-based carbon-fiber-reinforced polymer (CFRP). The internal PCM was used to increase the apparent heat capacity with a small mass gain, whereas the high-thermal-conductivity CFRP was used to enhance heat dissipation. The HSP was examined using thermal vacuum tests and thermal analysis. The HSP's continuous phase change reduced the temperature fluctuation in the space chamber. Furthermore, the HSP was loaded and examined on a Japanese micro-satellite called Hodoyoshi-4. In this on-orbit test, the HSP functioned as designed, and the temperature profile obtained on orbit agreed well with the thermal analysis. These results show the HSP's high potential for the thermal control of micro/nano-satellites.
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