航天器推進(jìn)系統(tǒng)氣路減壓閥溫度特性研究

The throttle valve temperature characteristics in spacecraft propulsive gas path

摘要: 針對航天器推進(jìn)系統(tǒng)，分析了氦氣在氣路上的工作過程，研究了氦氣節(jié)流效應(yīng)及其對減壓閥閥體溫度的影響。研究結(jié)果表明，在航天器氣路正常工作的溫度與壓力范圍內(nèi)，氦氣經(jīng)過減壓閥節(jié)流后的溫升在65～68 K之間，并隨減壓閥進(jìn)、出口壓力差的增大而增大。氦氣溫度變化引起減壓閥閥體溫度的變化，因此了解閥體溫度特性是減壓閥熱控設(shè)計(jì)的依據(jù)。

Abstract: 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.

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