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<p>High magnetic fields, efficiently generated by superconducting magnets, can enhance and modulate the thrust of applied-field magnetoplasmadynamic thrusters (AF-MPDTs). However, the extent to which high magnetic fields can impact performance is unknown due to the scarcity of tests conducted at Tesla-levels. This paper presents the discharge characteristics of a kW-class thruster (maximum 1.8&#xa0;kW) operating under a high magnetic flux density, reaching 1.25&#xa0;T, with argon propellant flow rates of 2 and 4&#xa0;mg/s. The measured discharge voltage increases with both discharge current and magnetic field. A portion of the voltage, the anode voltage fall, increases with the magnetic fields in the high-field regime and decreases with the mass flow rate. The temperatures monitored at the anode showed a maximum increase of 29.1&#xa0;K at 750&#xa0;mT during 15&#xa0;A discharge. The temperature measurements were used to quantify the anode’s thermal efficiency. The highest thermal efficiency of the anode, 66%, was registered at 750&#xa0;mT and showed minimal variation for both 10&#xa0;A and 15&#xa0;A at higher magnetic fields. For a 5&#xa0;A discharge, the anode’s thermal efficiency increases for all investigated magnetic fields, indicating that the thrusters operating in low-power mode can benefit from high magnetic flux densities (<InlineEquation ID="IEq1"> <EquationSource Format="TEX">\( &gt; \)</EquationSource> </InlineEquation> 256&#xa0;mT).</p>

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Discharge characteristics of a low-power applied-field magnetoplasmadynamic thruster in a Tesla-level magnetic field

  • 期刊论文

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  • 发表日期：

    2026年6月22日

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  • Jakub Głowacki,
  • Sebastian Hellmann,
  • Emile Webster,
  • Zoë Jaeger-Letts,
  • Jamal Olatunji,
  • Steven Smart,
  • Gennady Sidorov

摘要

High magnetic fields, efficiently generated by superconducting magnets, can enhance and modulate the thrust of applied-field magnetoplasmadynamic thrusters (AF-MPDTs). However, the extent to which high magnetic fields can impact performance is unknown due to the scarcity of tests conducted at Tesla-levels. This paper presents the discharge characteristics of a kW-class thruster (maximum 1.8 kW) operating under a high magnetic flux density, reaching 1.25 T, with argon propellant flow rates of 2 and 4 mg/s. The measured discharge voltage increases with both discharge current and magnetic field. A portion of the voltage, the anode voltage fall, increases with the magnetic fields in the high-field regime and decreases with the mass flow rate. The temperatures monitored at the anode showed a maximum increase of 29.1 K at 750 mT during 15 A discharge. The temperature measurements were used to quantify the anode’s thermal efficiency. The highest thermal efficiency of the anode, 66%, was registered at 750 mT and showed minimal variation for both 10 A and 15 A at higher magnetic fields. For a 5 A discharge, the anode’s thermal efficiency increases for all investigated magnetic fields, indicating that the thrusters operating in low-power mode can benefit from high magnetic flux densities ( \( > \) 256 mT).