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Optimization, Test and Diagnostics of Miniaturized Hall Thrusters
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Optimization, Test and Diagnostics of Miniaturized Hall Thrusters.

Jian W M Lim1, Igor Levchenko2, Muhammad W A B Rohaizat1

  • 1Plasma Sources and Applications Centre, National Institute of Education, Nanyang Technological University.

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PubMed
Summary

This study details the development and optimization of a compact Hall thruster for small satellites. The research demonstrates a highly efficient, small-scale electric propulsion system suitable for 50 kg spacecraft.

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Area of Science:

  • Spacecraft propulsion systems
  • Plasma physics
  • Miniaturized electric propulsion

Background:

  • Traditional thermochemical thrusters face physical limitations in exhaust velocity and efficiency, especially at low thrust levels, making them unsuitable for advanced satellite control.
  • Electric propulsion, specifically Hall thrusters, offers superior mass efficiency and specific impulse by accelerating plasma using electromagnetic fields, overcoming thermochemical limitations.
  • There is a growing demand for compact, low-power, high-efficiency thrusters for small satellites (50-200 kg) requiring precise, continuous maneuvering.

Purpose of the Study:

  • To design, construct, and optimize a small (30 mm) Hall thruster for 50 kg satellite applications.
  • To evaluate the thruster's performance in a simulated space environment, including thrust measurement and plasma characteristic analysis.
  • To achieve high efficiency in a miniaturized Hall thruster, addressing material challenges and opportunities.

Main Methods:

  • Development and testing of a 30 mm Hall thruster prototype.
  • Operation and data collection within a large space environment simulator.
  • Measurement of thrust, electrical parameters, and plasma characteristics for performance assessment and optimization.

Main Results:

  • Demonstration of a functional Hall thruster capable of propelling a 50 kg satellite.
  • Optimization process leading to one of the most efficient small Hall thrusters developed.
  • Analysis of plasma characteristics and electrical parameters to validate performance.

Conclusions:

  • The developed 30 mm Hall thruster is a viable, highly efficient propulsion solution for small satellites.
  • Optimization strategies and advanced materials can significantly enhance the performance of miniaturized electric propulsion systems.
  • This work contributes to the advancement of smart, durable, and reliable propulsion for the next generation of small spacecraft.