航天器动力管路热控设计与试验研究

针对某航天器动力系统管路布局分散造成系统温差大、控温难的问题，结合动力管路温度指标要求和边界环境条件，采用以被动热控措施为主、辅以电加热主动热控措施的设计方案。分析确立动力管路的热环境，建立换热模型；通过仿真分析和整器热平衡试验，选取不同工况，验证了动力系统氧化剂管路和燃烧剂管路温度均维持在8～20 ℃范围内的热控设计结果。该方案对各类航天器的动力管路热控设计和分析有一定的指导和借鉴作用。

Thermal control design and experimental study of spacecraft propulsion pipelines

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.