Verification of azimuthal current generation employing a rotating magnetic field plasma acceleration method in an open magnetic field configuration

Furukawa, Takeru; Shimura, Kaichi; Kuwahara, D.; Shinohara, Shunjiro

doi:10.1063/1.5064392

Cited by 19 publications

(4 citation statements)

References 30 publications

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“…To this point, Furukawa's group performed azimuthal plasma current measurements directly in an RMF thruster. They showed that azimuthal currents are indeed induced by the RMF but at ∼2.5% of the theoretically expected value [17]. In our recently developed test article, the RMF magnitudes are higher and frequencies are lower, and therefore we expect a more effective RMF current drive owing to increased field penetration into the plasma.…”

Section: Introductionmentioning

confidence: 60%

Inductive probe measurements in a rotating magnetic field thruster

Sercel,

Gill,

Jorns

2023

Plasma Sources Sci. Technol.

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The induced magnetic field during acceleration in a pulsed rotating magnetic field (RMF) thruster is experimentally investigated. A two-axis Bdot probe is employed to characterize the time-resolved evolution of the fields in a 5 kW-class test article. This device is operated at an average power of 4 kW with an RMF frequency of 415 kHz, pulse widths of 125 µs, and a repetition rate of 155 Hz. Plasma currents induced in the thruster are shown to be 2500 A and to have sufficient magnitude to form a Field-Reversed Configuration (FRC) plasmoid. The Lorentz force resulting from the induced magnetic field contributes ∼25% of measured thrust at this operating condition. Of this Lorentz thrust, ∼58% is due to plasma current interaction with the steady applied bias field, while the remainder is caused by interaction with secondary induced currents in nearby structural elements. This structure force is predicted to scale quadratically with plasma current magnitude. These results are discussed in the context of the historically low performance of these devices and strategies for improving their operation are presented.

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Section: Introductionmentioning

confidence: 60%

Inductive probe measurements in a rotating magnetic field thruster

Sercel,

Gill,

Jorns

2023

Plasma Sources Sci. Technol.

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“…Mathematical Sciences Northwest (MSNW) developed multiple test articles demonstrating pulse energies up to 50 J on gases including nitrogen and xenon [5][6][7][8]. Tokyo University of Agriculture and Technology implemented another RMF device intended to run semi-continuously at 1 kW on argon [9,10]. At the University of Michigan, we recently built and characterized a test article that demonstrated steady-state operation at 150 pulses per second and powers up to 4.5 kW operating on xenon.…”

Section: Introductionmentioning

confidence: 99%

“…With that said, there is a lack of direct experimental data to assess what drives the efficiency loss. Moreover, for the data that has been previously generated, either the diagnostics had limited accessibility [9,10] or the test articles in question were operated in facilities that were not representative of the on-orbit environment where these devices are intended to operate [5][6][7][8]. Given the outstanding fundamental questions about the operation of RMF thrusters, there is an apparent need for a detailed experimental characterization of the efficiency modes of the performance of an RMF device operating under more space-like conditions.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation into efficiency loss in rotating magnetic field thrusters

Gill,

Sercel,

Jorns

2024

Plasma Sources Sci. Technol.

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An experimental investigation into the low thrust eﬀiciency of a rotating magnetic field (RMF) thruster is presented. This technology is a low maturity but potentially enabling candidate for high-power in-space propulsion for use with alternative propellants. Direct thrust stand measurements of a 5-kW class RMF thruster were performed and show the thrust eﬀiciency was 0.41 ± 0.04% with a specific impulse of 292 ± 11 s—typical values for RMF thruster operation. A suite of far-field probes were used to inform a phenomenological eﬀiciency model for RMF thruster performance that accounted for divergence, power coupling, mass utilization, and plasma/acceleration eﬀiciency. It was found that the plasma eﬀiciency was the critically low term at 6.4 ± 1.0%. This indicates that the majority of the energy coupled to the plasma from the RMF antennas was lost before being converted to directed kinetic energy in the thruster beam. To determine the source of these losses, time-resolved measurements of the internal plasma properties were performed using a triple Langmuir probe. It was found that collisional excitation radiation and wall losses were the two dominant loss processes. This trend can be explained by the unusually high plasma density (> 1e19 m−3) exhibited by this device compared to other electric propulsion architectures. Limitations in the probing techniques and strategies for improving RMF thruster performance are discussed given the results from the eﬀiciency analysis.

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“…3,4,5 Not surprisingly, exploration of new physical principles for creating thrust in space, 6,7 and advanced implementation of the existing thrust systems attract strong attention of the researchers. 8,9 Among other space propulsion systems, the thrust platforms that utilize plasma 10 , 11, -12, 13 and ionized gas 14,15,16 to create reactive thrust are currently attracting the strongest attention due to many potential advantages of these devices, 17,18,19 mainly owing to very high specific impulse 20,21 and potentially long service life. 22,23 However, further uptake of these systems is challenged by several problems.…”

Section: Introductionmentioning

confidence: 99%

Perspectives, frontiers, and new horizons for plasma-based space electric propulsion

et al. 2020

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There are a number of pressing problems mankind is facing today that could, at least in part, be resolved by space systems. They include capabilities for fast and far-reaching telecommunication, surveying of resources and climate, and sustaining global information networks, to name but a few. Not surprisingly, increasing efforts are now devoted to building a strong near-Earth satellite infrastructure, with plans to extend the sphere of active life to orbital space and later, to the Moon and Mars if not further. This demands novel and more efficient means of propulsion. At present not only heavy launch systems are still based on thermodynamic principles but satellites and spacecraft still rely on gasbased thrusters or chemical engines to move. Similarly to other transportation systems where electrical platforms expand rapidly, space propulsion technologies are also experiencing a shift towards electric thrusters which do not feature limitations intrinsic to thermodynamic systems. Most important, electric and plasma thrusters promise virtually any impulse ultimately limited by the light speed. Not surprisingly, consolidated efforts in this field could be seen, and all-electric space systems are becoming closer to reality. In this paper we briefly outline the most recent successes in the development of plasma-based space propulsion systems, and present our view on future trends, possibilities and challenges.

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Verification of azimuthal current generation employing a rotating magnetic field plasma acceleration method in an open magnetic field configuration

Cited by 19 publications

References 30 publications

Inductive probe measurements in a rotating magnetic field thruster

Inductive probe measurements in a rotating magnetic field thruster

Experimental investigation into efficiency loss in rotating magnetic field thrusters

Perspectives, frontiers, and new horizons for plasma-based space electric propulsion

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