Accuracy Improvements in a Hall Thruster PIC/Fluid Code

Santos, Robert; Ahedo, Eduardo

doi:10.2514/6.2009-4914

Cited by 2 publications

(1 citation statement)

References 7 publications

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“…Second, both direct simulation Monte Carlo (DSMC) and deterministic schemes are implemented, depending on the type of collision to be modeled. Third, population control algorithms are implemented in each cell in order to improve the macro-particles number and weight and thus reduce the statistical noise inherent in PIC formulations [44][45][46]. Fourth, while standard volumetric weighting is used in inner cells, more accurate surface weighting is implemented at the material boundary cells [47,48].…”

Section: Introductionmentioning

confidence: 99%

Hybrid 3D model for the interaction of plasma thruster plumes with nearby objects

Cichocki

Domínguez-Vázquez

Merino

et al. 2017

Plasma Sources Sci. Technol.

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This paper presents a hybrid PIC-fluid approach to model the interaction of a plasma plume with a spacecraft and/or any nearby object. Ions and neutrals are modeled with a particle-in-cell approach, while electrons are treated as a fluid. After a first iteration of the code, the domain is split into quasineutral and non-neutral regions, based on nonneutrality criteria, such as the relative charge density and the Debye length to cell size ratio. At the material boundaries of the former quasineutral region, a dedicated algorithm ensures that the Bohm condition is met. In the latter non-neutral regions, the electron density and the electric potential are obtained by solving the coupled electron momentum balance and Poisson equations. Boundary conditions for both the electric current and potential are finally obtained with a plasma sheath sub-code and an equivalent circuit model. The hybrid code is validated by applying it to a typical plasma plume-spacecraft interaction scenario, and the physics and capabilities of the model are finally discussed.

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Section: Introductionmentioning

confidence: 99%

Hybrid 3D model for the interaction of plasma thruster plumes with nearby objects

Cichocki

Domínguez-Vázquez

Merino

et al. 2017

Plasma Sources Sci. Technol.

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Quasi-steady testing approach for high-power Hall thrusters

Brieda¹,

Raitses

Choueiri

et al. 2021

Journal of Applied Physics

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Hall effect thrusters operating at power levels in excess of several hundreds of kilowatts have been identified as enabling technologies for applications such as lunar tugs, large satellite orbital transfer vehicles, and solar system exploration. These large thrusters introduce significant testing challenges due to the propellant flow rate exceeding the pumping speed available in most laboratories. Even with proposed upgrades in mind, the likelihood that multiple vacuum facilities will exist in the near future to allow long duration testing of high-power Hall thrusters operating at power levels in excess of 100 kW remains extremely low. In this article, we numerically explore the feasibility of testing Hall thrusters in a quasi-steady mode defined by pulsing the mass flow rate between a nominal and a low value. Our simulations indicate that sub-second durations available before the chamber reaches critical pressure are sufficiently long to achieve the steady-state current and flow field distributions, allowing us to characterize thruster performance and the near plume region.

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Accuracy Improvements in a Hall Thruster PIC/Fluid Code

Cited by 2 publications

References 7 publications

Hybrid 3D model for the interaction of plasma thruster plumes with nearby objects

Hybrid 3D model for the interaction of plasma thruster plumes with nearby objects

Quasi-steady testing approach for high-power Hall thrusters

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