一种并网式载人航天器控温回路系统设计  

Design of Manned Spacecraft Thermal Control Loop System with Coupled Structure

作　　者：靳健[1] 侯永青[1] 

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《航天器工程》2014年第2期71-79,共9页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：提出了一种单舱辐射器并网和组合体舱间并网相结合的载人航天器控温回路系统,能够实现单舱层次功能备份和舱间层次功能备份。建立了单舱和组合体控温回路系统非稳态仿真分析模型,对正常工作模式和几种不同故障工作模式下各舱回路控温点温度、设备温度、流量分配和航天器热负荷水平进行了分析。结果表明,对于单舱辐射器并网回路,在单条辐射器支路故障情况下,系统总散热能力损失不超过28.5%,单舱外回路完全故障时启动舱间并网回路,故障舱段可维持的热负荷水平占标准工作模式热负荷水平的63.5%,表明双层次并网控温回路系统可将设备温度有效控制在指标要求范围内,并能显著提高载人航天器所能承受的热负荷水平,提高系统的可靠性。A thermal control loop with coupled radiator loops and inter-cabin loops for manned spacecraft is proposed, which can obtain the advantage of intra-cabin backup and inter-cabin back- up. An unsteady simulation model of the thermal control loop is developed. Based on this model, characteristics of the coupled thermal control loop under various working patterns are analyzed, including the temperature of controlling points and equipment, flux distribution, heat load level of cabin. According to the results, heat dissipation loss is less than 28. 5% when one radiator loop fails. When the radiator loops totally fail, the maintainable heat load can reach 63.5% of that in the standard mode by using the inter-cabin coupled loops. The results show that coupled structure can improve the reliability of thermal control loop dramatically and increase the heat load level of cabin when failures happen to loop.

关 键 词：载人航天器 热负荷 控温回路 并网回路 

分 类 号：V443[航空宇航科学与技术—飞行器设计]