航天器动力管路热控设计与试验研究王领华1，张皓2，王骞1，吕建伟1，吴勇3，赵允宁3，刘辰3（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）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。关键词：航天器；动力管路；热设计；仿真分析；热平衡试验中图分类号：V433文献标志码：A文章编号：1673-1379(2023)01-0001-05DOI:10.12126/see.2022093ThermalcontroldesignandexperimentalstudyofspacecraftpropulsionpipelinesWANGLinghua1,ZHANGHao2,WANGQian1,LÜJianwei1,WUYong3,ZHAOYunning3,LIUChen3(1.ChinaAcademyofLaunchVehicleTechnology,Beijing100076,China;2.BeijingInstituteofSpacecraftEnvironmentEngineering,Beijing100094,China;3.CapitalAerospaceMachineryCo.,Ltd.,Beijing100076,China)Abstract:Inviewofthelargetemperaturedifferenceanddifficultyinthermalcontrolcausedbythescatteredspacecraftpropulsionpipelines,adesignschemebasedonpassivethermalcontrolsupplementedbyelectricallyheatedactivethermalcontrolwasproposedincombinationwiththetemperaturerequirementsandboundaryenvironmentalconditionsofpropulsionpipelines.Thethermalenvironmentofpropulsionpipelineswasanalyzedanddetermined,anditsheattransfermodelwasestablished.Throughthesimulationanalysisandthethermalbalancetestofthewholedevice,differentworkingconditionswereselectedtoverifythethermalcontroldesignresultsthatthetemperaturesoftheoxidantandthecombustionagentpipelinesofthepropulsionsystemweremaintainedwithintherangeof8℃to20℃.Theschemecanbeusedasaguideandreferenceforthedesignandanalysisofthermalcontrolofpropulsionpipelinesforvariousspacecrafts.Keywords:spacecraft;propulsionpipeline;thermaldesign;simulationanalysis;thermalbalancetest收稿日期：2022-09-02...
