超临界氦增压与排放过程的压力温度特性  

Pressure and temperature characteristics of super critical helium pressurization and exhaust stage

作　　者：张亮 姚娜 赵栋梁 张卫东[2] 耑锐 

机构地区：[1]上海宇航系统工程研究所,上海201109 [2]上海航天技术研究院,上海201109

出　　处：《低温工程》2014年第5期10-15,共6页Cryogenics

摘　　要：为了探讨超临界氦增压技术在中国运载火箭和航天器上实现的可行性,进行了超临界氦增压排放实验研究。分析了低温杜瓦内的超临界氦的热分层稳定性;讨论了温度计引线两端大温差引起热声振荡和漏热现象;此外,由于节流微分效应和换热器管壁轴向导热,换热器出口温度在排放过程出现大幅温度波动。实验结果证明超临界氦增压过程中增压压力平稳、可靠,压力容易控制。但后续改进实验中应消除换热器节流微分效应导致的出口温度波动,并且减小杜瓦以及支撑结构的漏热。To investigate feasibility of pressurization and discharge by super critical helium applied to launch vehicle and space shuttle,the experiments about super critical helium pressurization were conducted,where the Dewar was heated and pressurized by gas helium at normal temperature. The stability of thermal layer of super critical helium in the cryogenic Dewar was analyzed. The large temperature fluctuations and heat leak induced by high temperature differences between two ends of the thermometer were discussed.In addition,temperature fluctuated significantly at the outlet of the exchanger during discharge due to the JT effect and axial conduction of exchanger pipes. Experimental results testified steady and credibility of super critical helium pressurization,and better control of system pressure. In future,the experiments to eliminate temperature fluctuations at exchanger outlet caused by J-T effect should improved,and decrease the heat leak induced by Dewar and support.

关 键 词：运载火箭 超临界氦 增压 实验 焦耳-汤姆逊效应 热声振荡 

分 类 号：TB65[一般工业技术—制冷工程] V434[航空宇航科学与技术—航空宇航推进理论与工程]