摘要
介绍了大型液氮液氦一体化热沉主要性能指标、设备结构和特点。针对热沉使用温度能够保持在低于10 K的使用要求,对热沉总体布置、管板结构形式、壁板结构形式、翅片管间距进行了详细设计,并对热沉材料选择和焊接进行了论述。该热沉能够进行航天发动机羽流效应试验,同时能够兼顾航天器热真空和热平衡试验。
The technical parameters, mechanical structure and characteristics of the large liquid nitrogen and liquid helium inte- grated heat sink were introduced. In order to realize the heat sink surface temperature below 10 K, the overall structure, the tube plate structure, the baffle plate structure and the finned tube space were amply designed. Also, the selection of the material and the welding of the heat sink were discussed. The heat sink is mainly applied to spacecraft-thruster vacuum plume effects＇ experi- mental study, the thermal vacuum test and heat balance test of satellite simuhaneouslv.
出处
《真空》
CAS
2015年第1期75-78,共4页
Vacuum
关键词
真空
液氮热沉
液氦热沉
羽流效应
热真空试验
vacuum
liquid nitrogen heat sink
liquid helium heat sink
plume effects
thermal vacuum test
