Magnetic Nozzle and RPA Simulatons vs. Experiments for a Helicon Plasma Thruster Plume

e-Archivo Repository

Show simple item record Cichoki, Filippo Navarro Cavallé, Jaume Modesti, Alberto Ramírez Vázquez, Gonzalo 2022-04-20T07:49:34Z 2022-04-20T07:49:34Z 2022-04-14
dc.identifier.bibliographicCitation Cichocki, F., Navarro-Cavallé, J., Modesti, A., & Ramírez Vázquez, G. (2022). Magnetic Nozzle and RPA Simulations vs. Experiments for a Helicon Plasma Thruster Plume. Frontiers in Physics, 10.
dc.identifier.issn 2296-424X
dc.description.abstract The experimental characterization of electrodeless plasma thrusters with a magnetic nozzle is fundamental in the process of increasing their maturity to reach the industrialization level. Moreover, it offers the unique opportunity of validating existing numerical models for the expansion of a magnetized plasma plume, and for the synthetic simulation of diagnostics measurements, like those of a retarding potential analyzer, which provides essential information regarding the ion beam energy distribution function. Simulations to experiments comparison ultimately enables a better understanding of the physical processes behind the observed experimental curves. In this work, input experimental data of a Helicon plasma plume is used to simulate both a magnetic nozzle expansion in the divergent field region, and the corresponding measurements of a retarding potential analyzer, through dedicated small-scale simulations of this diagnostics tool. Magnetic nozzle simulation and experimental results agree well in terms of the angular distribution of the ion current at 40 cm distance from the source, and also in the prediction of the energies of the two main peaks of the ion energy distribution function: a first one at 45 eV due to source ions, and a second one, at 15-20 eV, due to ions from charge-exchange and ionization collisions in the plume. Finally, the small-scale simulation of the retarding potential analyzer permits to assess the parasitic effects caused by the ion current collected by the different analyzer grids. The inclusion of the retarding and electron suppression grids currents in the overall I-V characteristic is shown to correct almost entirely these effects on the obtained ion velocity distribution.
dc.description.sponsorship This work has been funded by European Union's Horizon 2020 research and innovation program under grant agreement No 870542 HIPATIA(HelIconPlasmAThruster for In-space Applications), and the Spanish National research plan under the project ESPEOS, PID2019-108034RB-I00/AEI/10.13039/501100011033.
dc.format.extent 15
dc.language.iso eng
dc.publisher MDPI
dc.rights Copyright © 2022 Cichocki, Navarro-Cavallé, Modesti and Ramírez Vázquez.
dc.rights Atribución 3.0 España
dc.subject.other Helicon
dc.subject.other Plasma plumes
dc.subject.other Retarding potential analyzer (RPA)
dc.subject.other Particle in cell (PIC)
dc.subject.other Fluid models
dc.subject.other Hybrid models
dc.subject.other Magnetic nozzle (MN)
dc.title Magnetic Nozzle and RPA Simulatons vs. Experiments for a Helicon Plasma Thruster Plume
dc.type article
dc.subject.eciencia Física
dc.rights.accessRights openAccess
dc.relation.projectID Gobierno de España. PID2019-108034RB-I00
dc.relation.projectID info:eu-repo/grantAgreement/EC/H2020/870542
dc.type.version publishedVersion
dc.identifier.publicationfirstpage 1
dc.identifier.publicationlastpage 15
dc.identifier.publicationtitle Frontiers in Physics
dc.identifier.publicationvolume 10
dc.identifier.uxxi AR/0000030462
dc.contributor.funder European Commission
dc.contributor.funder Agencia Estatal de Investigación (España)
dc.affiliation.dpto UC3M. Departamento de Ingeniería Aeroespacial
dc.affiliation.grupoinv UC3M. Grupo de Investigación: Equipo de Propulsión Espacial y Plasmas (EP2)
 Find Full text

Files in this item

*Click on file's image for preview. (Embargoed files's preview is not supported)

The following license files are associated with this item:

This item appears in the following Collection(s)

Show simple item record