Abstract
Aiming at the temperature control demand of the near space solar unmanned aerial vehicle (UAV) payload cabin, this paper establishes the thermodynamic model of the payload cabin through thermal characteristic analysis, and proposes a system design method of structural thermal control integration. The thermal design of the payload cabin is carried out by means of thermal control such as uniform temperature, heat insulation, coating and active temperature control. The design weight of the whole payload cabin is only 7kg. The results of thermal analysis show that the temperature of the equipment in the cabin meets the requirement of the target during the whole UAV mission period, which verifies the correctness of the thermal design method. Compared with the traditional active temperature control scheme, the low temperature level increases by 3°C under the same heating power. The heat dissipation of the payload cabin is mainly convective heat transfer, but with the increase of altitude, the proportion of radiation heat dissipation is gradually increased. The research results can provide reference for the thermal design of similar aircraft.
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