中国物理B ›› 2025, Vol. 34 ›› Issue (4): 45203-045203.doi: 10.1088/1674-1056/adb9cb

所属专题： Featured Column — INSTRUMENTATION AND MEASUREMENT

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Precision assessment of micro-thruster performance: A comparative study of indium field emission electric propulsion thrust measurement methods with a force-feedback pendulum

Bo-Song Cai(蔡柏松)1, Yan Shen(沈岩)1,2, Yuan Zhong(钟源)3,4,†, Jian-Ping Liu(刘建平)3,‡, Yu-Qing Wang(王宇清)3, Zhu Li(李祝)3, Liang-Cheng Tu(涂良成)3, and Shan-Qing Yang(杨山清)3   

  1. 1 School of Aeronautics and Astronautics, Sun Yat-Sen University (Shenzhen Campus), Shenzhen 518107, China;
    2 Shenzhen Key Laboratory of Intelligent Microsatellite Constellation, Shenzhen 518107, China;
    3 MOE Key Laboratory of TianQin Mission, TianQin Research Center for Gravitational Physics & School of Physics and Astronomy, Frontiers Science Center for TianQin, Gravitational Wave Research Center of CNSA, Sun Yat-Sen University (Zhuhai Campus), Zhuhai 519082, China
  • 收稿日期:2024-12-25 修回日期:2025-02-24 接受日期:2025-02-25 出版日期:2025-04-15 发布日期:2025-04-15
  • 通讯作者: Yuan Zhong, Jian-Ping Liu E-mail:zhongy257@mail2.sysu.edu.cn;liujp39@mail.sysu.edu.cn
  • 基金资助:
    Project supported by the National Key Research and Development Program of China (Grant No. 2020YFC2201001), the Guangdong Major Project of Basic and Applied Basic Research (Grant No. 2019B030302001), the National Natural Science Foundation of China (Grant Nos. 12105373, 12105374, and 11927812), and the Science and Technology Research Project of Jiangxi Provincial Department of Education (Grant No. GJJ2402105).

Precision assessment of micro-thruster performance: A comparative study of indium field emission electric propulsion thrust measurement methods with a force-feedback pendulum

Bo-Song Cai(蔡柏松)1, Yan Shen(沈岩)1,2, Yuan Zhong(钟源)3,4,†, Jian-Ping Liu(刘建平)3,‡, Yu-Qing Wang(王宇清)3, Zhu Li(李祝)3, Liang-Cheng Tu(涂良成)3, and Shan-Qing Yang(杨山清)3   

  1. 1 School of Aeronautics and Astronautics, Sun Yat-Sen University (Shenzhen Campus), Shenzhen 518107, China;
    2 Shenzhen Key Laboratory of Intelligent Microsatellite Constellation, Shenzhen 518107, China;
    3 MOE Key Laboratory of TianQin Mission, TianQin Research Center for Gravitational Physics & School of Physics and Astronomy, Frontiers Science Center for TianQin, Gravitational Wave Research Center of CNSA, Sun Yat-Sen University (Zhuhai Campus), Zhuhai 519082, China
  • Received:2024-12-25 Revised:2025-02-24 Accepted:2025-02-25 Online:2025-04-15 Published:2025-04-15
  • Contact: Yuan Zhong, Jian-Ping Liu E-mail:zhongy257@mail2.sysu.edu.cn;liujp39@mail.sysu.edu.cn
  • Supported by:
    Project supported by the National Key Research and Development Program of China (Grant No. 2020YFC2201001), the Guangdong Major Project of Basic and Applied Basic Research (Grant No. 2019B030302001), the National Natural Science Foundation of China (Grant Nos. 12105373, 12105374, and 11927812), and the Science and Technology Research Project of Jiangxi Provincial Department of Education (Grant No. GJJ2402105).

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摘要： Accurate thrust assessment is crucial for characterizing the performance of micro-thrusters. This paper presents a comprehensive evaluation of the thrust generated by a needle-type indium field emission electric propulsion (In-FEEP) micro-thruster using three methods based on a pendulum: direct thrust measurement, indirect plume momentum transfer and beam current diagnostics. The experimental setup utilized capacitive displacement sensors for force detection and a voice coil motor as a feedback actuator, achieving a resolution better than 0.1 μN. Key performance factors such as ionization and plume divergence of ejected charged particles were also examined. The study reveals that the high applied voltage induces significant electrostatic interference, becoming the dominant source of error in direct thrust measurements. Beam current diagnostics and indirect plume momentum measurements were conducted simultaneously, showing strong agreement within a deviation of less than 0.2 μN across the operational thrust range. The results from all three methods are consistent within the error margins, verifying the reliability of the indirect measurement approach and the theoretical thrust model based on the electrical parameters of In-FEEP.

关键词: micro-thruster, field emission, thrust stand, micro-thrust measurement, calibration, pendulum

Abstract: Accurate thrust assessment is crucial for characterizing the performance of micro-thrusters. This paper presents a comprehensive evaluation of the thrust generated by a needle-type indium field emission electric propulsion (In-FEEP) micro-thruster using three methods based on a pendulum: direct thrust measurement, indirect plume momentum transfer and beam current diagnostics. The experimental setup utilized capacitive displacement sensors for force detection and a voice coil motor as a feedback actuator, achieving a resolution better than 0.1 μN. Key performance factors such as ionization and plume divergence of ejected charged particles were also examined. The study reveals that the high applied voltage induces significant electrostatic interference, becoming the dominant source of error in direct thrust measurements. Beam current diagnostics and indirect plume momentum measurements were conducted simultaneously, showing strong agreement within a deviation of less than 0.2 μN across the operational thrust range. The results from all three methods are consistent within the error margins, verifying the reliability of the indirect measurement approach and the theoretical thrust model based on the electrical parameters of In-FEEP.

Key words: micro-thruster, field emission, thrust stand, micro-thrust measurement, calibration, pendulum

中图分类号:  (Emission, absorption, and scattering of particles)

  • 52.25.Tx
52.75.Di (Ion and plasma propulsion) 79.70.+q (Field emission, ionization, evaporation, and desorption) 94.05.-a (Space plasma physics)