航天器推进系统气路减压阀温度特性研究  

The throttle valve temperature characteristics in spacecraft propulsive gas path

作　　者：苏生[1] 马巨印[1] 陈阳[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器环境工程》2012年第4期445-449,共5页Spacecraft Environment Engineering

摘　　要：针对航天器推进系统,分析了氦气在气路上的工作过程,研究了氦气节流效应及其对减压阀阀体温度的影响。研究结果表明,在航天器气路正常工作的温度与压力范围内,氦气经过减压阀节流后的温升在65～68 K之间,并随减压阀进、出口压力差的增大而增大。氦气温度变化引起减压阀阀体温度的变化,因此了解阀体温度特性是减压阀热控设计的依据。In the context of the propulsion system in spacecraft,the helium flow mode in the gas loop,the helium Joule-Thomson effect and its influence on the temperature in the throttle valve are discussed.It is shown that the temperature rise of the helium is about 65 K to 68 K after passing through the value under the normal operating temperature and the pressure range of the gas-loop for spacecraft,and the rise enhances with the increase of the pressure difference between inlet and outlet.The variation of the valve temperature caused by the helium temperature change would lead to some special characteristics of the temperature,as the basis of the thermal control design of the valve.

关 键 词：航天器 减压阀 节流效应 温度特性 

分 类 号：TH138.52[机械工程—机械制造及自动化]