Particle Simulation Model for Self-Field Magnetoplasmadynamic Thruster

Li, Jian; Wu, Jianjun; Cheng, Yuqiang; Du, Xinru

doi:10.3390/en12081579

Cited by 6 publications

(3 citation statements)

References 24 publications

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“…It's nearly impossible to enhance thruster performance without a thorough understanding of the process. This paper also inferred that the performance improvement of SF-MPDT is greatly restricted by low efficiency about 30% [16].…”

Section: Detailed Study Of Limitationsmentioning

confidence: 67%

MPD Thruster Technology and Its Limitations

Patel¹,

Bondugula²,

Gorakula³

2021

International Journal of Scientific Advances

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It was realized earlier that chemical propulsion systems utilize fuel very inefficiently, which greatly limits their lifespan. Electric propulsion is into existence to overcome this limitation of chemical propulsion. The magnetoplasmadynamic (MPD) thruster is presently the most powerful form of electromagnetic propulsion. It is the thruster’s ability to efficiently convert MW of electric power into thrust which gives this technology a potential to perform several orbital as well as deep space missions. MPD thruster offers distinct advantages over conventional types of propulsion for several mission applications with its high specific impulse and exhaust velocities. However, MPD thruster has limitations which limits its operational efficiency and lifetime. In this paper, the thruster limitations are reviewed with respect to three operational limits i.e., the onset phenomenon, cathode lifetime, and thruster overfed limits. The dependence and effects of the operational limits on each other is compared using different empirical models to derive a scaling factor that has been found for each geometrical arrangement; a limiting value exists beyond which the operation becomes highly unsteady and electrode erosion occurs. Along with reviewing and proposing methods to overcome power limitations for MPD thrusters, the relation between exit velocity and ratio of electrode’s radius is also verified using Maecker’s formula.

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Section: Detailed Study Of Limitationsmentioning

confidence: 67%

MPD Thruster Technology and Its Limitations

Patel¹,

Bondugula²,

Gorakula³

2021

International Journal of Scientific Advances

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“…Each particle's charge is then assigned to the four nearest grid points, weighted linearly based on the particle's proximity to each node. This is called the Cloudin-Cell algorithm [16]. Potential can then be calculated at each grid point, using Poisson's Equation, Eq.…”

Section: Methodsmentioning

confidence: 99%

A Novel Approach for the Particle-in-Cell Modelling of Gridded Ion Engine Plume Neutralisation

Parke Sturrock,

Jelic,

Evans

et al. 2021

J. Technol. Space Plasmas

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The Particle-in-Cell modelling of gridded ion engine plume neutralisation has been simplified when compared to traditional methods. This results in significantly less computational resources being required. The NSTAR engine was modelled as a reference, where simulated specific impulse values were found to be 5% higher than the real engine. This method will be most suited to rapid prototyping and optimisation studies, where speed of simulations is an important factor.

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“…They also found that at an applied field strength of 0.1 T, F AF was approximately ten times larger than F GD or F Hall . Li et al also used a PIC-MCC model to investigate an AF-MPD thruster [98] [99]. They made the electrostatic assumption and derived a self-similar scaling law to reduce computation time.…”

Section: Particle-in-cellmentioning

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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Particle Simulation Model for Self-Field Magnetoplasmadynamic Thruster

Cited by 6 publications

References 24 publications

MPD Thruster Technology and Its Limitations

MPD Thruster Technology and Its Limitations

A Novel Approach for the Particle-in-Cell Modelling of Gridded Ion Engine Plume Neutralisation

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

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