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Title: Chaotic waves in Hall thruster plasma

Abstract

The set of hyperbolic equations of the fluid model describing the acceleration of plasma in a Hall thruster is analyzed. The characteristic feature of the flow is the existence of a trapped characteristic; i.e. there exists a characteristic line, which never intersects the boundary of the flow region in the thruster. To study the propagation of short wave perturbations, the approach of geometrical optics (like WKB) can be applied. This can be done in a linear as well as in a nonlinear version. The nonlinear version describes the waves of small but finite amplitude. As a result of such an approach one obtains so called transport equation, which are governing the wave amplitude. Due to the existence of trapped characteristics this transport equation appears to have chaotic (turbulent) solutions in both, linear and nonlinear versions.

Authors:
 [1];  [2]; ; ;  [3];  [4]
  1. Institute of Applied Mathematics and Mechanics, Warsaw University, Banacha 2, 02-097 Warsaw (Poland)
  2. (Poland)
  3. Institute of Fundamental Technological Research, Polish Academy of Sciences, SwiePtokrzyska 21, 00049 Warsaw (Poland)
  4. Laboratoire d'Aerothermique, Centre National de la Recherche Scientifique 1C Avenue de la Recherche Scientifique, 45071 Orleans Cedex 2 (France)
Publication Date:
OSTI Identifier:
20797890
Resource Type:
Journal Article
Resource Relation:
Journal Name: AIP Conference Proceedings; Journal Volume: 812; Journal Issue: 1; Conference: PLASMA 2005: International conference on research and applications of plasmas; 3. German-Polish conference on plasma diagnostics for fusion and applications; 5. French-Polish seminar on thermal plasma in space and laboratory, Opole-Turawa (Poland), 6-9 Sep 2005; Other Information: DOI: 10.1063/1.2168816; (c) 2006 American Institute of Physics; Country of input: International Atomic Energy Agency (IAEA)
Country of Publication:
United States
Language:
English
Subject:
70 PLASMA PHYSICS AND FUSION TECHNOLOGY; ACCELERATION; AMPLITUDES; CHAOS THEORY; DISTURBANCES; ION THRUSTERS; NONLINEAR PROBLEMS; PLASMA; PLASMA FLUID EQUATIONS; PLASMA SIMULATION; TRANSPORT THEORY; TRAPPING

Citation Formats

Peradzynski, Zbigniew, Institute of Fundamental Technological Research, Polish Academy of Sciences, SwiePtokrzyska 21, 00-049 Warsaw, Barral, S., Kurzyna, J., Makowski, K., and Dudeck, M.. Chaotic waves in Hall thruster plasma. United States: N. p., 2006. Web. doi:10.1063/1.2168816.
Peradzynski, Zbigniew, Institute of Fundamental Technological Research, Polish Academy of Sciences, SwiePtokrzyska 21, 00-049 Warsaw, Barral, S., Kurzyna, J., Makowski, K., & Dudeck, M.. Chaotic waves in Hall thruster plasma. United States. doi:10.1063/1.2168816.
Peradzynski, Zbigniew, Institute of Fundamental Technological Research, Polish Academy of Sciences, SwiePtokrzyska 21, 00-049 Warsaw, Barral, S., Kurzyna, J., Makowski, K., and Dudeck, M.. Sun . "Chaotic waves in Hall thruster plasma". United States. doi:10.1063/1.2168816.
@article{osti_20797890,
title = {Chaotic waves in Hall thruster plasma},
author = {Peradzynski, Zbigniew and Institute of Fundamental Technological Research, Polish Academy of Sciences, SwiePtokrzyska 21, 00-049 Warsaw and Barral, S. and Kurzyna, J. and Makowski, K. and Dudeck, M.},
abstractNote = {The set of hyperbolic equations of the fluid model describing the acceleration of plasma in a Hall thruster is analyzed. The characteristic feature of the flow is the existence of a trapped characteristic; i.e. there exists a characteristic line, which never intersects the boundary of the flow region in the thruster. To study the propagation of short wave perturbations, the approach of geometrical optics (like WKB) can be applied. This can be done in a linear as well as in a nonlinear version. The nonlinear version describes the waves of small but finite amplitude. As a result of such an approach one obtains so called transport equation, which are governing the wave amplitude. Due to the existence of trapped characteristics this transport equation appears to have chaotic (turbulent) solutions in both, linear and nonlinear versions.},
doi = {10.1063/1.2168816},
journal = {AIP Conference Proceedings},
number = 1,
volume = 812,
place = {United States},
year = {Sun Jan 15 00:00:00 EST 2006},
month = {Sun Jan 15 00:00:00 EST 2006}
}
  • This paper presents a linear analysis of gradient plasma instabilities in Hall thrusters. The study obtains and analyzes the dispersion equation of high-frequency electromagnetic waves based on the two-fluid model of a cold plasma. The regions of parameters corresponding to unstable high frequency modes are determined and the dependence of the increments and intrinsic frequencies on plasma parameters is obtained. The obtained results agree with those of previously published studies.
  • Magnetic field topology has been found to be a central design concern for high-efficiency Hall thrusters. For future improvements in Hall thruster design, it is necessary to better understand the effects that magnetic field topology has on the internal plasma structure. The Plasmadynamics and Electric Propulsion Laboratory's High-speed Axial Reciprocating Probe system is used in conjunction with a floating emissive probe to map the internal plasma potential structure of the NASA-173Mv1 Hall thruster [R. R. Hofer, R. S. Jankovsky, and A. D. Gallimore, J. Propul. Power 22, 721 (2006); 22, 732 (2006)]. Measurements are taken at 300 and 500 Vmore » with a xenon propellant. Electron temperature and electric field are also measured and reported. The acceleration zone and equipotential lines are found to be strongly linked to the magnetic field lines. Moreover, in some cases the ions are accelerated strongly toward the center of the discharge channel. The agreement between magnetic field lines and equipotential lines is best for high-voltage operation. These results have strong implications on the performance and lifetime optimization of Hall thrusters.« less
  • A large research programme on Hall thrusters has been initiated in France in 1996. This programme includes modelling, as well as theoretical and experimental approaches. These researches are coordinated in the frame of a national Research Group. Recent results obtained at the laboratoire d'Aerothermique taking part to the activities of this group are presented. A short description of electric propulsion and especially the behaviour of a Hall Effect Thruster are presented in the first part of this paper. In the second part, experimental time resolved measurements performed by means of electrostatic probe are presented to show the dynamical behaviour ofmore » electron characteristics and compared with the recorded discharge current and potential. These results describe to ion and electron properties in the plasma flow in the surroundings of the thruster channel exhaust.« less
  • This work represents a two-dimensional (r,z)-3V axisymmetric fully kinetic particle-in-cell/Monte Carlo collision model of the plasmadynamics in the acceleration channel of a stationary plasma thruster. The model includes the process of secondary electron emission from the dielectric walls. In order to allow for a realistic simulation, differently from the previous fully kinetic model using a dummy mass ratio and vacuum permittivity or neglecting radial effects, a geometrical scaling of the channel is applied keeping the main dimensionless physics parameters constant. By this, the problem of the computational limits due to the very fast electron dynamics can be overcome. This modelmore » is able to give a clear picture of the plasma flow inside the acceleration channel. The results confirm the existence of an anode sheath with reverse ion flow, an ionization and acceleration region separated by a sonic transition point, and the ion flux distribution hitting the walls. Furthermore, the code is able to reproduce the observed two populations of electrons and to calculate the ion distribution on the exit plane used as input data for plume simulations.« less
  • Secondary-electron emission at the ceramic walls of a Hall thruster modifies the potential jump of the wall Debye sheaths and thus the electron energy losses to the wall. Because of the low plasma collisionality the two counterstreaming beams of secondary electrons are not expected to be totally trapped within the bulk of the discharge. In order to analyze the effects of partial trapping of secondary electrons on the presheath/sheath radial structure, a macroscopic model is formulated. The plasma response depends on the secondary electron emission yield and the trapped fraction of secondary electrons. The sheath potential and wall energy lossesmore » are determined mainly by the net current of secondary electrons in the sheaths. For any practical value of the secondary emission yield, the zero-trapping solution is very similar to the zero secondary emission case. Space charge saturation of the sheaths is unattainable for weak trapping. In all cases, secondary electrons have a weak effect on the presheath solution and the ion flux recombined at the walls.« less