![]() Gaier JR, Jaworske DA (2007) Lunar dust on heat rejection system surfaces: problems and prospects. NASA/TM-2008-215492Īgui JH, Nakagawa M (2005) Dust on the Moon and Mars. Gaier JR, Siamidis J, Panko SR, et al (2008) The effect of simulated lunar dust on the absorptivity, emissivity, and operating temperature on AZ-93 and Ag/FEP thermal control surfaces. Liu Z, Xiang Y, Si D, et al (2014) Design and verification of thermal control system for Chang’E-3 probe. China Astronautic Publishing House, Beijing Ouyang Z (2005) Introduction to lunar science. Therefore, there will different thermal measures for different temperature range. ![]() The temperature range is different, for example, general electronic equipment is from −20 ☌ to 55 ☌ and inner structure of the lunar lander is from −100 ☌ to 80 ☌ before landing. The requirements of mass and power consumption of thermal control subsystem shall be as low as possible. ![]() The major function of thermal control subsystem is to maintain the structure and instruments of the lunar lander within acceptable temperature range throughout lifetime by controlling the heat exchange between interior of the lunar lander and external environment with thermal material and devices. It’s necessary to take proper thermal control measures to make sure appropriate temperature range of structure and instruments to achieve mission objectives. ![]() The external environment and operation modes of instruments in different phases are different. Compared with Earth orbit and circumlunar spacecraft, lunar soft-landing probes will go through complicated phases including launching, LTO, lunar orbit, powered descent, landing and operation on lunar surface. ![]()
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