Impact of the Microwave Coupling Structure on an Electron-Cyclotron Resonance Thruster

Peterschmitt, Simon; Packan, Denis

doi:10.2514/1.b38156

Cited by 12 publications

(24 citation statements)

References 12 publications

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“…The way microwave power is coupled to the plasma appears to be a relevant factor for electron heating and consequently ion acceleration. Lower performance levels have been reported for the waveguide configuration [13] for similar operating conditions (input microwave power of 25 W at 2.45 GHz, 1 sccm of Xenon) and thruster dimensions. A better understanding of the reasons behind the performance discrepancy is of great importance since it could lead to improved design strategies.…”

Section: Introductionmentioning

confidence: 82%

“…Two different microwave injection designs have been reported in the literature for ECRTs, the coaxial [7,[11][12][13] and the truly electrodeless circular waveguide design [14][15][16][17][18]. In the first case, a central conductor is present in the plasma chamber which can be seen as an extension of the coaxial cable delivering the microwaves from the source to the thruster.…”

Section: Introductionmentioning

confidence: 99%

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Ion dynamics in the magnetic nozzle of a waveguide ECR thruster via laser-induced fluorescence spectroscopy

Vinci¹,

Inchingolo²,

Mazouffre³

et al. 2022

J. Phys. D: Appl. Phys.

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Xenon ion velocity is mapped in the magnetic nozzle of a circular waveguide electron cyclotron resonance thruster operating at 5.8 GHz by means of laser-induced fluorescence spectroscopy in the near-infrared spectral range. An array of thruster operational parameters are explored to investigate the influence on the acceleration profile and terminal ion velocity. Owing to several mechanisms which broaden the measured spectra, e.g. Paschen-Back/Zeeman effect, inference of the most probable velocity along with the axial kinetic temperature requires full lineshape modeling, especially in the near-field plume and inside the source. Ions are effectively accelerated along the magnetic nozzle, reaching up to 12000 m/s for the lowest neutral pressure tested. A relatively large axial kinetic temperature is observed, typically in the order of 5000 K, which can be attributed to an extended ionization region that overlaps with the acceleration region.

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Section: Introductionmentioning

confidence: 82%

Section: Introductionmentioning

confidence: 99%

Ion dynamics in the magnetic nozzle of a waveguide ECR thruster via laser-induced fluorescence spectroscopy

Vinci¹,

Inchingolo²,

Mazouffre³

et al. 2022

J. Phys. D: Appl. Phys.

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“…The µW power is produced by a solid state laboratory power supply tunable in frequency and in power. It is measured at the vacuum chamber wall using a setup of two couplers, two diodes and a circulator [19] allowing for the measurement of the forward and reflected powers. The transmission line from the vessel wall to the thruster is calibrated ahead of each campaign using a vector network analyzer and its transmission factor is used to evaluate the power deposited in the thruster.…”

Section: Ecra Thruster Descriptionmentioning

confidence: 99%

“…The research on ECRT at ONERA, in France, started in 2010 with the development of a 30W ECRT named ECRA, leading to a patent [16,17] and several PhD thesis focusing on the subject [18][19][20]. During these studies, a low power prototype using a permanent magnet was designed, accurate thrust measurements were made [21][22][23].…”

Section: Introductionmentioning

confidence: 99%

“…During these studies, a low power prototype using a permanent magnet was designed, accurate thrust measurements were made [21][22][23]. The coaxial coupling structure demonstrated a higher efficiency with respect to the previously used waveguide coupling [24]. The acceleration electric field was measured using LIF and Langmuir probe measurements [25].…”

Section: Introductionmentioning

confidence: 99%

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ECRA thruster advances: 30W and 200W prototypes latest performances

et al. 2023

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The H2020 MINOTOR project focused on the study and the optimization of the ECRA thruster, an electric propulsion system for satellites. First, a 30 W prototype of this Electron Cyclotron Resonance Thruster (ECRT) is optimized. Then, a 200 W prototype is design based on these findings. The performances of both prototypes were assessed at two different facilities: at ONERA in France and at Justus Liebig University in Germany. Significant improvement of performances of both thrusters with the decrease of background pressure is presented. Total thrust efficiencies as high as 50% are measured at JLU, as well as erosion and lifetime assessment. The stability of the thruster for a constant point of operation was measured for one hundred hours of operation.

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Experimental characterization of thrust production mechanisms in a magnetic nozzle ECR thruster

2022

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Direct thrust measurements have been performed on a low-power (30 W) ECR plasma thruster operated with xenon. The total thrust, the force exerted on the walls of the source (thermal thrust), and the force exerted on the permanent magnet (magnetic thrust) have been measured separately for various operating conditions (power and flowrate). The results are compared for two magnetic field topologies (with a different magnetic field gradient and divergence). The magnetic thrust dominates thermal thrust for most operating conditions, and its contribution to total thrust can be as high as 80%. A saturation of magnetic thrust with increasing power has been observed and is correlated with a decrease in thrust efficiency. A high degree of electron anisotropy can be inferred from the thrust measurements.

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Impact of the Microwave Coupling Structure on an Electron-Cyclotron Resonance Thruster

Cited by 12 publications

References 12 publications

Ion dynamics in the magnetic nozzle of a waveguide ECR thruster via laser-induced fluorescence spectroscopy

Ion dynamics in the magnetic nozzle of a waveguide ECR thruster via laser-induced fluorescence spectroscopy

ECRA thruster advances: 30W and 200W prototypes latest performances

Experimental characterization of thrust production mechanisms in a magnetic nozzle ECR thruster

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