航天器密封艙真空熱試驗(yàn)用壓控系統(tǒng)設(shè)計(jì)與實(shí)現(xiàn)
Design and realization of a pressure control system for sealed cabin in vacuum thermal test for spacecraft
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摘要: 帶有密封艙段的航天器在進(jìn)行真空熱試驗(yàn)時(shí)，經(jīng)常需要對(duì)密封艙內(nèi)壓力進(jìn)行調(diào)節(jié)控制。壓控系統(tǒng)具有泄壓、復(fù)壓、穩(wěn)壓功能，可以實(shí)現(xiàn)密封艙內(nèi)壓力調(diào)控的目的。文章詳細(xì)介紹了某型號(hào)真空熱試驗(yàn)用密封艙壓控系統(tǒng)的結(jié)構(gòu)原理及設(shè)計(jì)方法，同時(shí)解決了真空低溫環(huán)境下真空管路的隔熱與密封難題。通過模擬測(cè)試對(duì)系統(tǒng)主要指標(biāo)進(jìn)行了驗(yàn)證，結(jié)果表明系統(tǒng)能夠滿足試驗(yàn)要求。Abstract: In the vacuum thermal test for spacecraft with sealed cabin, the pressure in the cabin should be under control and adjustment. A pressure control system(PCS) is designed for this purpose, with functions such as depressurization, repressurization and keeping the pressure unchanged. The structure, principle and design method of the PCS are discussed. The simulation results indicate that the PCS can satisfy most requirements of the vacuum thermal test.
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