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VACUUM ›› 2022, Vol. 59 ›› Issue (6): 10-16.doi: 10.13385/j.cnki.vacuum.2022.06.02

• Vacuum Acquisition System • Previous Articles     Next Articles

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

LI Hong-yu1, SU Dong-ping1, DAI Ming-qiao1, SUN Li-zhi2, DOU Wei2, PENG Guang-dong1   

  1. 1. Shanghai Institute of Spacecraft Equipment, Shanghai 200240, China;
    2. Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China
  • Received:2022-06-20 Online:2022-11-25 Published:2022-12-05

Abstract: 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 7.5×10-10Pa·m3/s with vacuum leak detection method and 2.0×10-6Pa·m3/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.

Key words: helium mass spectrometer leak detection, leak detection chamber, air tightness, spacecraft propulsion system

CLC Number: 

  • TB774
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