摘要
文章介绍了卫星电推进系统工质氙气充装特性试验系统及测试方法,开展了氙气充装饱和蒸气压,气相及超临界状态PVT充装特性试验研究,建立了新的氙气饱和蒸气压方程,拟合得到了氙气的临界压力,并与其他研究机构的试验数据进行了比较分析。氙气饱和蒸气压试验结果与NIST方程计算值的相对偏差小于0.2%,发现并验证了NIST方程计算值在近临界区的偏差最高达到6 k Pa。试验数据为建立氙气充装加注预估模型奠定基础,为卫星电推进系统充装加注及在轨应用提供重要的参考。
The principle and the theory of charge characteristics of xenon working gases for the satellite electric propulsion system are discussed. A technique to study the charge characteristics of xenon working gases is put forward. Physical experiments including the saturated vapor pressure and the xenon in the phase of gas and in super-critical state are carried out. A new saturated vapor pressure formula is obtained. The critical pressure of the xenon is obtained by a linear fitting method, and experimental data are compared with testing data obtained by other research institutes. The relative deviations between the xenon saturated vapor pressure testing value and the NIST equation are less than 0.2%. The maximal deviation of the NIST formula takes place near the critical region, with a value of 6 kPa. The experiment helps to establish a mathematical model of the xenon working gas charge characteristics.
出处
《航天器环境工程》
2014年第6期640-645,共6页
Spacecraft Environment Engineering
基金
卫星型号专项支持
关键词
电推进系统
工质
氙气
充装
检漏试验
electric propulsion system
working gases
xenon
gas charge
leak testing
