Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster

Takahiro Nakamura, Sho Ito, Hiroyuki Nishida, Shunjiro Shinohara, Ikkoh Funaki, Takao Tanikawa, Tohru Hada

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    In order to realize long-lived electric propulsion systems, we have been investigating an electrodeless plasma thruster. In our concept, high-density helicon plasma is accelerated by a magnetic nozzle for thrust production. In order to improve the thrust performance with simple systems, high magnetic flux density magnetic nozzle formed by permanent magnets is employed to our laboratory model plasma thruster. A magnetic circuit, which has high magnetic flux density up to 0.2 T at the magnetic nozzle throat, is constructed by permanent magnets and magnetic yoke. In order to investigate the thrust performance of this thruster, the thrust force is measured by a torsion-pendulum type thrust stand. From the thrust measurement, the thrust force and specific impulse increases with the RF power input. The thrust efficiency is drastically improved by increasing the RF power input, and it is considered to be caused by the discharge mode transition from the CCP to the ICP. The maximum thrust force and thrust efficiency of 2.7 ± 0.4 mN and 0.26 % is measured when the Ar gas mas flow rate is 1.2 mg/s, and plasma production frequency and power is 13.56 MHz and 1000 W.

    Original languageEnglish
    Title of host publication50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
    PublisherAmerican Institute of Aeronautics and Astronautics Inc.
    ISBN (Electronic)9781624103032
    DOIs
    Publication statusPublished - Jan 1 2014
    Event50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States
    Duration: Jul 28 2014Jul 30 2014

    Publication series

    Name50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

    Other

    Other50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
    CountryUnited States
    CityCleveland
    Period7/28/147/30/14

    Fingerprint

    Magnetic nozzles
    Helicons
    Permanent magnets
    Magnetic flux
    Magnetic fields
    Plasmas
    Electric propulsion
    Magnetic circuits
    Plasma sources
    Pendulums
    Torsional stress
    Flow of gases
    Flow rate

    All Science Journal Classification (ASJC) codes

    • Energy Engineering and Power Technology
    • Aerospace Engineering
    • Control and Systems Engineering
    • Electrical and Electronic Engineering
    • Mechanical Engineering

    Cite this

    Nakamura, T., Ito, S., Nishida, H., Shinohara, S., Funaki, I., Tanikawa, T., & Hada, T. (2014). Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-3474

    Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster. / Nakamura, Takahiro; Ito, Sho; Nishida, Hiroyuki; Shinohara, Shunjiro; Funaki, Ikkoh; Tanikawa, Takao; Hada, Tohru.

    50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Nakamura, T, Ito, S, Nishida, H, Shinohara, S, Funaki, I, Tanikawa, T & Hada, T 2014, Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster. in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, American Institute of Aeronautics and Astronautics Inc., 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014, Cleveland, United States, 7/28/14. https://doi.org/10.2514/6.2014-3474
    Nakamura T, Ito S, Nishida H, Shinohara S, Funaki I, Tanikawa T et al. Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc. 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). https://doi.org/10.2514/6.2014-3474
    Nakamura, Takahiro ; Ito, Sho ; Nishida, Hiroyuki ; Shinohara, Shunjiro ; Funaki, Ikkoh ; Tanikawa, Takao ; Hada, Tohru. / Thrust performance of high magnetic field permanent magnet type Helicon Plasma Thruster. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).
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