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载人航天器密封系统漏率设计方法
引用本文:李兴乾,张伟,郑昊,张雅彬,李学东.载人航天器密封系统漏率设计方法[J].航天器环境工程,2013,30(6):606-609.
作者姓名:李兴乾  张伟  郑昊  张雅彬  李学东
作者单位:1. 南京航空航天大学 航空宇航学院, 南京 210016;2.中国空间技术研究院 载人航天总体部, 北京 100094
摘    要:载人航天器密封舱为航天员提供在轨生活、工作的环境,对密封舱及其环控生保系统、热控制系统、推进控制系统等中各管路的密封性能有严格要求。文章提出了一种漏率设计方法,建立了相应的漏率检测系统,并依据该方法制定了密封舱体和各管路的漏率设计和指标分配的流程。本流程可用作载人航天器舱体密封系统、管路密封系统的漏率设计,对保证载人航天器在轨安全可靠运行有重要参考价值。

关 键 词:载人航天器  密封系统  漏率设计
收稿时间:2013/7/26 0:00:00
修稿时间:2013/11/5 0:00:00

The design method of leaking ratio in manned spacecraft sealing system
Li Xingqian,Zhang Wei,Zheng Hao,Zhang Yabin,Li Xuedong.The design method of leaking ratio in manned spacecraft sealing system[J].Spacecraft Environment Engineering,2013,30(6):606-609.
Authors:Li Xingqian  Zhang Wei  Zheng Hao  Zhang Yabin  Li Xuedong
Institution:1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. Beijing Institute of Manned Space System Engineering, China Academy of Space Technology, Beijing 100094, China
Abstract:The manned spacecraft cabin provides an in-orbit working and living environment for the astronauts. The environment control system, the thermal control system, the propulsion control system are to guarantee the normal operation of the pipelines; and they all should have a good sealing performance. The paper studies the design method of the sealing system based on the leakage ratio, to be used in the manned spacecraft cabin sealing system and the piping sealing system.
Keywords:manned spacecraft  sealing system  design of leaking ratio
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