Advanced Search+
Tao CHEN (陈焘), Juntai YANG (杨俊泰), Xinwei CHEN (陈新伟), Yong ZHAO (赵勇). The plume diagnostics of 30 cm ion thruster with an advanced plasma diagnostics system[J]. Plasma Science and Technology, 2020, 22(9): 94005-094005. DOI: 10.1088/2058-6272/ab854f
Citation: Tao CHEN (陈焘), Juntai YANG (杨俊泰), Xinwei CHEN (陈新伟), Yong ZHAO (赵勇). The plume diagnostics of 30 cm ion thruster with an advanced plasma diagnostics system[J]. Plasma Science and Technology, 2020, 22(9): 94005-094005. DOI: 10.1088/2058-6272/ab854f

The plume diagnostics of 30 cm ion thruster with an advanced plasma diagnostics system

More Information
  • Received Date: December 19, 2019
  • Revised Date: March 29, 2020
  • Accepted Date: March 30, 2020
  • In order to achieve a better understanding of plume characteristics of LIPS-300 ion thruster, the beam current density, ion energy and electron number density of LIPS-300 ion thruster plume are studied with an Advanced Plasma Diagnostics System (APDS) which allows for simultaneous in situ measurements of various properties characterizing ion thruster, such as plasma density, plasma potential, plasma temperature and ion beam current densities, ion energy distribution and so on. The results show that the beam current density distribution has a double 'wing' shape. The high energy ions were found in small scan angle, while low energy ions were found in greater scan angle. Electron number density has a similar shape with the beam current density distribution.
  • [1]
    Zhang T P et al 2013 Initial flight test results of the LIPS-200 electric propulsion system on SJ-9A satellite Proc. 33rd Int. Electric Propulsion Conf. (Washington, The George Washington University, 6–10 October, 2013)
    [2]
    Zhang T P 2015 J. Rocket Propul. 41 7 (in Chinese)
    [3]
    Goebel D M and Katz I 2008 Fundamentals of Electric Propulsion: Ion and Hall Thrusters (Pasadena: California Institute of Technology)
    [4]
    Lobbia R B and Beal B E 2017 J. Propul. Power 33 566
    [5]
    Yu W et al 2013 Experimental investigations of plasma plume potential in a vacuum chamber Proc. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. (AIAA) 2013, 2013–4130
    [6]
    Langendorf S et al 2013 Effect of ion-neutral collisions on sheath potential profile Proc. 33rd Int. Electric Propulsion Conf. (Washington, The George Washington University,6–10 October, 2013)
    [7]
    Brown D L et al 2017 J. Propul. Power 33 582
    [8]
    Liang R 2013 The combination of two concentric discharge channels into a nested hall-effect thruster PhD Thesis University of Michigan
    [9]
    Sekerak M J et al 2015 IEEE Trans. Plasma Sci. 43 72
    [10]
    Szabo J et al 2015 IEEE Trans. Plasma Sci. 43 141
    [11]
    Walker J A, Frieman J D and Walker M L R 2014 Hall effect thruster electrical interaction with a conductive vacuum chamber Proc. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. (Cleveland, OH, USA, 28–30 July 2014) (Reston, VA: AIAA)
    [12]
    Huang W S et al 2013 A new method for analyzing near-field Faraday probe data in hall thrusters Proc. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. (San Jose, CA, USA, 14–17 July, 2013) (Reston, VA: AIAA) (https://doi.org/10.2514/6.2013-4118)
    [13]
    Sekerak M J 2014 Plasma oscillations and operational modes in hall effect thrusters PhD Thesis University of Michigan
    [14]
    Brown D L, Lobbia R B and Blakely J M 2014 Low-voltage hall thruster mode transitions Proc. of the 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. (Cleveland, OH: AIAA)
    [15]
    Huang W S, Kamhawi H and Haag T 2013 Effect of background pressure on the performance and plume of the HiVHAc hall thruster Proc. 33rd Int. Electric Propulsion Conf. (Washington, The George Washington University, 6–10 October, 2013)
    [16]
    Farnell C et al 2013 Electrostatic analyzers with application to electric propulsion testing Proc. 33rd Int. Electric Propulsion Conf. Fairview (The George Washington University, USA, 6–10 October, 2013) (Electric Rocket Propulsion Society)
    [17]
    Farnell C C et al 2017 J. Propul. Power 33 638
    [18]
    Sheehan J P et al 2017 J. Propul. Power 33 614
    [19]
    Yang J et al 2018 Plasma Sci. Technol. 20 085402
    [20]
    Yildim Serhan Z and Murat C 2019 Plasma Sci. Technol. 21 045505
    [21]
    King L B 1998 Transport-property and mass spectral measurements in the plasma exhaust plume of a hall-effect space propulsion system PhD Thesis University of Michigan
    [22]
    Qayyum A et al 2013 Rev. Sci. Instrum. 84 123502
  • Cited by

    Periodical cited type(6)

    1. Moon, G., Choe, W., Jun, E. Plasma plume simulation of an atomic oxygen-fed ion thruster in very-low-earth-orbit. Plasma Sources Science and Technology, 2023, 32(12): 125012. DOI:10.1088/1361-6595/ad15b0
    2. Wang, Y.-F., Zhu, X.-M., Jia, J.-W. et al. Development of a circumferential-scanning tomography system for the measurement of 3-D plume distribution of the spacecraft plasma thrusters. Measurement: Journal of the International Measurement Confederation, 2023. DOI:10.1016/j.measurement.2023.112966
    3. Yang, Y., Zhou, S., Yan, K. et al. Measurement and diagnosis of miniaturized ion thruster plume. AIP Advances, 2023, 13(3): 035036. DOI:10.1063/5.0143330
    4. Chen, X.-W., Gu, Z., Gao, J. et al. Beam Divergence and Thrust Vector Deviation Characteristics of Low-Power Hall Thruster | [低功率霍尔推力器束流发散和推力矢量偏心特性研究]. Tuijin Jishu/Journal of Propulsion Technology, 2022, 43(8): 200948. DOI:10.13675/j.cnki.tjjs.200948
    5. Liu, X., Kang, X., Deng, H. et al. Energy properties and spatial plume profile of ionic liquid ion sources based on an array of porous metal strips. Plasma Science and Technology, 2021, 23(12): 125502. DOI:10.1088/2058-6272/ac23bd
    6. Chen, X., Gu, Z., Gao, J. et al. The far-field plasma characteristics of LHT40 low-power Hall thruster for commercial aerospace applications. Plasma Science and Technology, 2021, 23(10): 104009. DOI:10.1088/2058-6272/ac15eb

    Other cited types(0)

Catalog

    Article views (121) PDF downloads (199) Cited by(6)

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return