北京航空航天大学学报 ›› 2010, Vol. 36 ›› Issue (8): 977-980.

• 论文 • 上一篇    下一篇

低功率N2H4电弧加热发动机高空模拟试验系统

张莘艾, 汤海滨, 施陈波, 刘 宇   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2009-06-22 出版日期:2010-08-30 发布日期:2010-09-07
  • 作者简介:张莘艾(1981-),男,上海人,博士生,zhangxinai@sa.buaa.edu.cn.
  • 基金资助:

    国家自然科学基金资助项目(50826007)

High altitude simulation experiment system for low power hydrazine arcjet

Zhang Xinai, Tang Haibin, Shi Chenbo, Liu Yu   

  1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2009-06-22 Online:2010-08-30 Published:2010-09-07

摘要: 介绍了用于低功率肼(N2H4)电弧加热发动机(Arcjet)的高空模拟试验系统,阐述了该系统中的高空模拟真空系统、推进剂供给系统、电源调理单元(PCU,Power Control Unit)、微推力全弹性测量装置、数据采集系统以及其它配套设施.针对低功率肼电弧加热发动机地面试验的特殊要求,重点介绍了有毒推进剂肼(N2H4)的供给、微小流量测量、微小推力测量的方法与原理,并在该套系统上进行了系统功能验证性试验.试验证明,该套系统满足低功率肼电弧加热发动机高空模拟试验要求,为推进肼电弧加热发动机的研究与工程应用提供了保障.

Abstract: A high altitude simulation experiment system for low power hydrazine arcjet was presented. The elements in this system including vacuum facility, propellant feed system, power control unit, full elastic micro thrust measurement equipment, data acquisition system etc. were depicted in details. To meet the special demands in low power arcjet high altitude simulation experiment, the working process and principle of the propellant feed system, the full elastic steady weighting method micro flow measurement system and the full elastic micro thrust measurement equipment were emphasized. Tests to validate the system were conducted in this system. The results show that the high altitude simulation experiment is steady, reliable and competent for low power hydrazine arcjet high altitude simulation experiment.

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