Study on thermal analysis simulation and test of propellant refueling process for optical module

光学舱推进剂补加过程的热分析仿真与试验研究

¹ Beijing Institute of Spacecraft System Engineering, Beijing 100094, China
² National Key Laboratory of Spacecraft Thermal Control, Beijing 100094, China

Received: 13 June 2023

Abstract

Propellant refueling is important for long-term operation of the optical module in orbit. However, its thermal environment is harsher than on previous missions. Therefore, thermal control of the entire process is required. In order to solve the complex heat transfer of propellant refueling process, an integrated thermal model is established, which includes all the equipment such as the compressor, liquid cooler and loop heat pipe. The thermal analysis simulation and system-level thermal tests is presented. Firstly, the heat transfer relationship and temperature variation are analyzed by comparing the results of transient thermal analysis and thermal test in high and low temperature conditions. Then, a variable thermal conductivity simulation method is studied for the transient process from inoperative to operative of the vertical heat pipe due to gravitational factors in the thermal test. Finally, an optimized design scheme for high temperature refueling is proposed and pre-demonstrated in orbit. The results indicate that the transient simulation results are in a good agreement with the test results under the high and low temperatures, which verifies the accuracy and validity of the analysis method and simulation model. When preheating the compressor and starting two sets of loop heat pipes during on-orbit refueling, the maximum temperature of compressor is below 34.1°C, and the total power consumption of preheating is 50 Wh, which meet the design requirement. The investigation provides an important reference for designing the propellant refueling process in the docking of the optical module to the China Space Station (CSS).

摘要

推进剂补加是确保光学舱在轨长寿命工作的重要功能, 补加过程面临的热环境条件比以往任务恶劣, 全过程热控制十分必要。针对光学舱推进剂补加过程的复杂传热新问题, 建立包含压气机、液冷模块和环路热管等部件的光学舱平台集成热数学模型, 进行热分析仿真研究, 并开展系统级热试验。对比高温和低温2种补加条件的瞬态热分析和热试验结果, 研究传热关系和温度变化规律; 针对热试验中垂直热管因重力因素从不运行至运行的瞬态过程, 提出一种变热导率仿真方法; 提出高温补加优化设计方案并进行在轨预示。结果表明: 瞬态仿真结果与试验结果吻合良好, 验证了热分析方法和仿真模型的准确性和有效性; 在轨补加采用压气机本体预热并启动2套环路热管, 压气机的最高温度≤34.1℃, 预热总功耗50 Wh, 满足指标要求。研究结果对于光学舱停靠空间站期间的推进剂补加流程设计具有一定参考价值。