Design analysis of a plasma thruster with superconducting magnets

Glowacki, Jakub; Badcock, Rodney A.; Long, Nicholas J.

doi:10.2514/6.2019-4081

Cited by 9 publications

(4 citation statements)

References 8 publications

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“…The Russian MPDT, built on second generation High Temperature Superconductors (2G HTSs), achieves a maximum magnetic field of 1 T, resulting in a 300% thrust increase and a 700% boost in efficiency when superconducting magnets are applied. 11 China's superconducting MPDT has achieved a maximum efficiency of 76.6% and a specific impulse of 5714 s. 1 Moreover, numerous research institutions in Germany [12][13][14] and New Zealand 15 have also embarked on research into superconducting MPDT.…”

Section: Introductionmentioning

confidence: 99%

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

Tang,

Zheng,

Liu

et al. 2024

AIP Advances

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The high temperature superconductors enhanced magnetoplasmadynamic thruster is a promising device for various space mission scenarios. However, a critical issue hindering the enhancement of the thruster’s performance is the problem of anode power deposition. Previous studies have identified the anode fall voltage as a major contributor to this power deposition. This paper introduces an approximate analytical formula for calculating anode power deposition resulting from anode fall voltage. The paper further analyzes and calculates the variation of anode fall voltage with an applied magnetic field and discharge current. The findings reveal a direct correlation between applied magnetic field and both anode fall voltage and power, indicating an increase with higher magnetic field values. In contrast, while the anode fall voltage experiences a slight decline with increased discharge current, the anode power deposition remains elevated due to the transition from field ionization to thermal ionization. To gain a comprehensive understanding of anode power deposition, an experiment was conducted to obtain measurements under different operating conditions, involving varying levels of applied magnetic field and discharge current. The experimental results align with the theoretical predictions. These insights have the potential to serve as a valuable reference for enhancing the efficiency of magnetoplasmadynamic thrusters, bringing us closer to unlocking the full potential of these remarkable propulsion systems in the realm of space exploration.

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Section: Introductionmentioning

confidence: 99%

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

Tang,

Zheng,

Liu

et al. 2024

AIP Advances

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“…al. presented theoretical design and benefit of using superconductor based AF-MPDT [11]. 25 kW AF-MPDT is developed and tested(thrust, specific impulse and efficiency) experimentally by Voronov et.al.…”

Section: Introductionmentioning

confidence: 99%

Thrust estimation for HTS-magnet based Magneto Plasma Dynamic Thrusters (MPDT)

Meena

Anand

Gour

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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At present time, electric propulsion is being considered for outer deep space missions. Magneto Plasma Dynamic Thrusters are capable of accelerating semi- neutral plasma gas (Xenon, Iodine, Argon, Ammonia, or Lithium) to a high exhaust velocity using combination of RF power & high magnetic fields. High Temperature Superconducting (HTS) coils can generate high magnetic field due to high operating current density at temperatures below its critical temperature(Tc). These superconducting coils can be cooled by using the cold of outer dark space. The use of 2nd Generation (2G) HTS coils can increase thrust, by increasing high magnetic field with very low power consumption. Thus, specific impulse due to the combination of RF plasma and HTS based superconducting high magnetic field is increased drastically. In this paper, the thrust calculation are carried out for MPDT for varying magnetic fields produced by superconducting coils. The estimation of exhaust velocity and thrust generated by plasma for an MPDT is of great challenge and is required to determine for calculating the life of mission as well as the distance of travel. These estimations are required to support the indigenous development of MPDT.

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“…The concept of a superconducting applied field module has also been presented as a space technology business opportunity by a company in Germany [45]. A systemlevel design analysis of an AF-MPDT with a superconducting applied field module has also taken place [89]. This considered a mission profile of a 100 kg m f and a ∆v of 3 kms −1 .…”

Section: Superconductors and Applied-field Modulesmentioning

confidence: 99%

“…Operating conditions for these thrusters are shown in Table 5.1, which are shown alongside previous CC-EST and AF-MPDT study data. In addition to experimental campaigns, there have been theoretical and commercial studies on the topic of HTS magnets for plasma thruster applied field modules [57], [89], [181].…”

Section: Introductionmentioning

confidence: 99%

A Central-Cathode Electrostatic Thruster Featuring a High-Temperature Superconducting Applied Field Module

Acheson

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In recent decades, advances in electric propulsion have enabled the development of novel mission designs for space exploration. However, future deep space mission payloads of unprecedented mass will require advances in high thrust, high specific impulse propulsion. To achieve higher thrust density than traditional ion thrusters or Hall effect thrusters, novel designs for central-cathode electrostatic thrusters (CC-ESTs) and applied field magnetoplasmadynamic thrusters incorporate an applied magnetic field module which is used to accelerate plasma. The high thrust density of such designs makes them suitable candidates for further research and development for space deployment.Crucial performance metrics of such thrusters have been shown to increase as the applied magnetic field increases, and high temperature superconducting (HTS) magnets show promise as low-power, high applied field modules. Both the strength and the profile of the applied magnetic field are closely tied to thruster performance. This raises the question- which magnetic fields improve thruster performance and why?In this thesis, the impact of the magnetic field strength and profile on the performance of a plasma thruster is investigated. Numerical modelling of a central-cathode electrostatic thruster (CC-EST) was performed with particular regard to the detachment of plasma from magnetic field lines. This modelling was conducted alongside an experimental campaign to manufacture and integrate a high temperature superconducting applied field module with a CC-EST to characterise the HTS CC-EST performance. CC-EST performance was measured at central bore fields exceeding 1 T and with two different magnetic field profiles. These efforts have led to a novel understanding of the scaling of performance parameters in CC-EST with magnetic field, and how the performance of the thruster might be tailored to a specific application.

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Design analysis of a plasma thruster with superconducting magnets

Cited by 9 publications

References 8 publications

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

Investigating the impact of applied magnetic field and current on anode power deposition in AF-MPDT

Thrust estimation for HTS-magnet based Magneto Plasma Dynamic Thrusters (MPDT)

A Central-Cathode Electrostatic Thruster Featuring a High-Temperature Superconducting Applied Field Module

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