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High altitude long endurance unmanned air vehicle has been in low temperature environment for a long time. For the demands of thermal control for flight vehicle's propellant tank , this project focus on the optimal design of thermal control system. Due to the high emphasis paying on reducing vehicle weight, and highly reliability level, environmental adaptability requirements, the thermal control system is designed difficulty. The heat transfer analysis model was established for the structure and the heater efficiency. The calculation and analysis of heat rate were conducted with different schemes and configurations, the functional optimization design method in this paper can be applied in propellant tank thermal control system.