衛(wèi)星推進(jìn)系統(tǒng)檢漏多余物控制分析

Control of redundant substance in the leakage test for satellite propulsion system

摘要: 衛(wèi)星推進(jìn)系統(tǒng)每個(gè)檢漏階段均需要充入氣體進(jìn)行檢漏，充氣過(guò)程是推進(jìn)系統(tǒng)內(nèi)部多余物控制的重點(diǎn)。文章梳理了衛(wèi)星推進(jìn)系統(tǒng)檢漏充氣過(guò)程多余物控制的要素，通過(guò)大量基礎(chǔ)試驗(yàn)得到了詳細(xì)的試驗(yàn)數(shù)據(jù)，在此基礎(chǔ)上分析多余物控制的各個(gè)環(huán)節(jié)，總結(jié)出具有針對(duì)性的多余物控制方法。該研究可以廣泛應(yīng)用于各類航天器推進(jìn)系統(tǒng)的多余物控制。

Abstract: In each leak testing stage for a satellite, the propulsion system must be charged with gas. For the satellite propulsion system, the process of gas charging must be paid great attention to for an effective control of redundant substance. This paper analyzes the factors influencing the control of redundant substances in the gas charging process during the leak testing of the propulsion system based on a large number of tests and the data obtained from the tests, and the methods of controlling the redundant substances. The result can be applied in the propulsion system of various kinds of spacecraft to control the redundant substances.

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