Study on a Functional Thermal Control Systems for High-power Micro-satellite
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Previously, high-power micro-satellite below ~100 kg is developed for high-functional spacecraft operated. Generally, only thermal analysis is applied to thermal design for micro-satellite due to small-power consumption, or passive control is sometimes applied as thermal control. But they are not suitable for high-power micro-satellites. Our final goal is to construct a functional and high-power thermal control system for micro-satellite: 100W, 3U. The feature of this proposal system are no power supply, simple configuration and positive control to realize variable control. In this present study, we propose a 3U satellite as a testbed of 100W thermal control system with a pitch type CFRP, a micro loop heat pipe and a flexible redeployable radiator. The proposal satellite try not only to verify these thermal control devices, but also to do a water phase change experiment under microgravity environment aimed at thermal mission for 100W class. The detail of this experiment is to observe the temperature change through the cyclic phase change of water from solid to liquid and from liquid to gas during temperature change depending on orbital. Furthermore, we do a basic design of satellite, a construction of thermal control system, a fabrication of thermal test model and a space environment mock test. In this report, we simulate a feasibility of their missions by thermal mathematical model and predict a temperature change in orbital. The results of simulation show that a solar input to paddle becomes up to 180 W and that paddle can absorb the heat energy from the sun up to 97W. The result for the phase change of water becomes the temperature change from -10ºC to100ºC and reveals the possibility of the phase change test. The temperature of bus equipment is also within the permissible temperature range. In conclusion, these results show the feasibility of our proposal mission.