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<p>Surface Arc Thrusters (SATs) offer a promising CubeSat propulsion option due to their low voltage and current requirements, but their development faces three key challenges: bulky power supply circuits, uneven propellant consumption, and high-voltage ignition producing electromagnetic interference (EMI). To address these issues, this study investigated (1) the use of electric double-layer capacitors (EDLCs, a.k.a. super capacitors) to realize compact circuits with extended discharge durations, (2) a rectangular propellant configuration to improve consumption uniformity, and (3) a vacuum arc thruster (VAT) igniter to reduce ignition voltage. EDLCs enabled millisecond-scale discharges, the rectangular design mitigated uneven propellant use, and the VAT reduced ignition voltage to below 1&#xa0;kV, though with limited reproducibility. These results provide fundamental insights toward the practical implementation of SATs in CubeSats. This study systematically integrates power supply design, propellant geometry, and ignition method in SAT development, clarifying both their interdependence and the key challenges for future applications. </p>

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Investigation of the use of electric double-layer capacitors and rectangular propeller shape to improve the performance of surface arc thrusters and to reduce the voltage of the igniter discharge circuit

  • 期刊论文

  • 出版模式：

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  • 发表日期：

    2026年1月31日

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  • Kazuki Nishioka,
  • Tomohiro Shinnyo,
  • Kazuhiro Toyoda

摘要

Surface Arc Thrusters (SATs) offer a promising CubeSat propulsion option due to their low voltage and current requirements, but their development faces three key challenges: bulky power supply circuits, uneven propellant consumption, and high-voltage ignition producing electromagnetic interference (EMI). To address these issues, this study investigated (1) the use of electric double-layer capacitors (EDLCs, a.k.a. super capacitors) to realize compact circuits with extended discharge durations, (2) a rectangular propellant configuration to improve consumption uniformity, and (3) a vacuum arc thruster (VAT) igniter to reduce ignition voltage. EDLCs enabled millisecond-scale discharges, the rectangular design mitigated uneven propellant use, and the VAT reduced ignition voltage to below 1 kV, though with limited reproducibility. These results provide fundamental insights toward the practical implementation of SATs in CubeSats. This study systematically integrates power supply design, propellant geometry, and ignition method in SAT development, clarifying both their interdependence and the key challenges for future applications.