中国空间科学技术

›› 2019, Vol. 39 ›› Issue (5): 69-.doi: 10.16708/j.cnki.1000-758X.2019.0042

• 技术交流 • 上一篇    下一篇

微型镓场发射电推力器的推力和比冲测量

 徐明明, 刘欣宇, 康小明, 郭登帅, 贺伟国   

  1. 上海交通大学机械与动力工程学院，上海200240
  • 出版日期:2019-10-25 发布日期:2019-10-25

Thrust and specific impulse tests of miniature gallium field emission electric propulsion thruster

 XU  Ming-Ming, LIU  Xin-Yu, KANG  Xiao-Ming, GUO  Deng-Shuai, HE  Wei-Guo   

  1. School of Mechanical Engineering，Shanghai Jiao Tong University，Shanghai200240，China
  • Published:2019-10-25 Online:2019-10-25

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摘要： 电推进技术的发展推动了微推力测量技术和比冲测量技术的研究进程。为了评估已研制出的微型镓场发射电推力器的性能，进行了推力和比冲测量。研制了一种用于场发射电推力器的微推力测量平台；进行了LabVIEW开发；对测量平台进行了标定与分析，并通过试验比较了推力实测值与理论值，实测值范围为3~28μN。另外，利用飞行时间法，测得推力器在不同发射电流下的比冲数据，比冲范围为5917~8875s。

关键词: 场发射电推力器；推力；比冲；测量；发射电流；飞行时间法, 电推进

Abstract: The development of electric propulsion technology has promoted the research process of micro thrust measurement technology and specific impulse measurement technology. In order to evaluate the performance of the developed miniature gallium field emission electric thruster, thrust and specific impulse measurements were made. A thrust measurement platform for field emission electric thrusters was developed, the LabVIEW development was carried out and the measurement platform was calibrated and analyzed. The measured values and theoretical values of the thrust were compared through experiments. The measured values range from 3 to 28μN. In addition, using the time of flight method, the thruster′s specific impulse data under different emission currents were measured, and the specific impulse′s range is 5917-8875s.

Key words: field emission eletric propulsion, thrust, specific impulse, measurement, emission current, time of flight, electric propulsion