大型航天器漏率检测系统设计与性能分析  

Design and Performance Analysis of Leak Rate Testing System for Large Spacecraft

作　　者：李宏宇 苏东平 代明桥 孙立志[2] 窦威[2] 彭光东 LI Hong-yu;SU Dong-ping;DAI Ming-qiao;SUN Li-zhi;DOU Wei;PENG Guang-dong(Shanghai Institute of Spacecraft Equipment,Shanghai 200240,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]上海卫星装备研究所,上海200240 [2]北京卫星环境工程研究所,北京100094

出　　处：《真空》2022年第6期10-16,共7页Vacuum

摘　　要：为满足在轨航天器推进系统密封性能检测需求,本文基于氦质谱检漏法介绍了大型航天器漏率检测系统的组成和设计方案。系统采用组合设计,嵌入式盖板结构,远程集控等方式,提高了航天器漏率检测效率和自动化水平;通过真空、常压氦质谱检漏试验验证了系统的漏率检测性能,真空检漏法最小可检漏率为7.5×10^(-10)Pa·m^(3)/s,常压累积检漏法最小可检漏率为2.0×10^(-6)Pa·m^(3)/s(周期2天);研究了检漏容器环境参数变化规律和微正压条件下的气密性,发现随着容器内温度增加,相对湿度呈降低趋势,容器充入表压1500Pa以上的压缩空气后24h压降小于80Pa,气密性满足航天器检漏测试要求。This work introduces the system composition and design scheme of a large spacecraft leak rate testing for in-orbit spacecraft sealing performance requirement based on leak detection with helium mass spectrometer.The testing efficiency and automation level during spacecraft leak rate testing are improved because of the integrated optimization design,embedded plate construction and remote centralized control.Experimental verification of system leakage detection performance via atmospheric and vacuum helium mass spectrum leak detection shows that,the minimum detectable leakage rate are 7.5×10^(-10)Pa·m^(3)/s with vacuum leak detection method and 2.0×10^(-6)Pa·m^(3)/s with atmospheric accumulation leak detection method for two days.Variation rule of environmental parameters in collection chamber and air tightness under micro-positive pressure are studied,the results indicate that the relative humidity declines with the increasing temperature influenced by external environmental factors.The pressure drop is less than 80Pa within 24h after filling compressed air in the collection chamber with gauge pressure above 1500Pa,and the air tightness meets the requirements of the spacecraft leak rate detection.

关 键 词：氦质谱检漏 检漏容器 气密性 航天器推进系统 

分 类 号：TB774[一般工业技术—真空技术]