航天器动力管路热控设计与试验研究  

Thermal control design and experimental study of spacecraft propulsion pipelines

作　　者：王领华[1] 张皓 王骞[1] 吕建伟[1] 吴勇 赵允宁 刘辰 WANG Linghua;ZHANG Hao;WANG Qian;LÜ Jianwei;WU Yong;ZHAO Yunning;LIU Chen(China Academy of Launch Vehicle Technology,Beijing 100076,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China;Capital Aerospace Machinery Co.,Ltd.,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京卫环境工程研究所,北京100094 [3]首都航天机械有限公司,北京100076

出　　处：《航天器环境工程》2023年第1期1-5,共5页Spacecraft Environment Engineering

基　　金：国家重点研发计划项目“某航天器热控系统研制”。

摘　　要：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。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.

关 键 词：航天器 动力管路 热设计 仿真分析 热平衡试验 

分 类 号：V433[航空宇航科学与技术—航空宇航推进理论与工程]