Abstract:
In view of the large temperature difference and difficulty in thermal control caused by the scattered spacecraft propulsion pipelines, a design scheme based on passive thermal control supplemented by electrically heated active thermal control was proposed in combination with the temperature requirements and boundary environmental conditions of propulsion pipelines. The thermal environment of propulsion pipelines was analyzed and determined, and its heat transfer model was established. Through the simulation analysis and the thermal balance test of the whole device, different working conditions were selected to verify the thermal control design results that the temperatures of the oxidant and the combustion agent pipelines of the propulsion system were maintained within the range of 8
℃ to 20
℃. The scheme can be used as a guide and reference for the design and analysis of thermal control of propulsion pipelines for various spacecrafts.