Results 261 to 270 of about 1,081 (308)

µ-Hall Effect Thruster Characterization

49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011
Results of two methods to characterize a novel micro-Hall effect thruster are presented. The voltage-current characteristics of the thruster during steady state operation are reported. The exhaust plume is characterized using Faraday probe measurements and the beam efficiency is reported.
John-David de La Harpe, Richard Branam, Richard Huffman, Sujeet Paintal, Rachel Tedrake   +4 more
openaire   +1 more source

Effects of wall electrodes on Hall effect thruster plasma

Physics of Plasmas, 2015
This paper investigates the physical mechanisms that cause beneficial and detrimental performance effect observed to date in Hall effect thrusters with wall electrodes. It is determined that the wall electrode sheath can reduce ion losses to the wall if positioned near the anode (outside the dense region of the plasma) such that an ion-repelling sheath
S. Langendorf, K. Xu, M. Walker
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Magnetic mirror effect in a cylindrical Hall thruster

Journal of Physics D: Applied Physics, 2017
Abstract For cylindrical Hall thrusters, the magnetic field geometry is totally different from that in conventional Hall thrusters. In this study, we investigate the magnetic mirror effect in a fully cylindrical Hall thruster by changing the number of iron rings (0–5), which surround the discharge channel wall.
Yiwei Jiang, Haibin Tang, Junxue Ren, Min Li, Jinbin Cao   +4 more
openaire   +1 more source

Optimized atom injection in a Hall effect thruster

Applied Physics Letters, 2004
An improvement of the neutral gas injection in order to increase the Hall thruster lifetime capabilities is demonstrated using a two-dimensional model. An additional atom injection through the channel ceramics in a region located between the ionization and the acceleration zones leads to an efficient ionization of the neutral flux, with a flattening of
L. Garrigues, G. J. M. Hagelaar, C. Boniface, J. P. Boeuf   +3 more
openaire   +1 more source

Elementary Scaling Relations for Hall Effect Thrusters

Journal of Propulsion and Power, 2011
Various sizing methodologies are currently available to get a first estimate of the required Hall effect thruster dimensions for a given input power and a corresponding thrust and specific impulse level. In this work, a semiempirical approach to compute the three characteristic thruster dimensions, i.e., the channel length, the channel width, and the ...
Käthe Dannenmayer, Stéphane Mazouffre
openaire   +1 more source

Azimuthal Spoke Propagation in Hall Effect Thrusters

IEEE Transactions on Plasma Science, 2015
Spokes are azimuthally propagating perturbations in the plasma discharge of Hall effect thrusters (HETs) that travel in the $E \times B$ direction. The mechanisms for spoke formation are unknown, but their presence has been associated with improved thruster performance in some thrusters motivating a detailed investigation.
Sekerak, Michael J., Longmier, Benjamin W., Gallimore, Alec D., Brown, Daniel L., Hofer, Richard R., Polk, James E.   +5 more
openaire   +2 more sources

Effect of Anode Temperature on Hall Thruster Performance

Journal of Propulsion and Power, 2010
The effects of anode temperature on the performance of a 5-kW Hall-effect thruster are investigated. The performance characteristics of the P5 Hall-effect thruster are measured with and without active cooling of the anode. Thrust, ion current density, anode temperature, and cooling power are measured for discharge voltages between 100 and 500 V at ...
Carl F. Book, Mitchell L. R. Walker
openaire   +1 more source

A study of wall effects on hall thruster operation

The 31st IEEE International Conference on Plasma Science, 2004. ICOPS 2004. IEEE Conference Record - Abstracts., 2004
Summary form only given. An electron emission from the wall facing the plasma can reduce the sheath potential drop increasing the electron energy flux to the wall. As the flux of cold emitted electrons becomes comparable to the flux of incident plasma electrons the sheath saturates due to the space charge of slow emitted electrons.
Y. Raitses, D. Staack, N.J. Fisch
openaire   +1 more source

The Effect of Pressure on the Plume Divergence in the Hall Thruster

IEEE Transactions on Plasma Science, 2008
The plume divergence in the Hall thruster due to the plasma pressure is analyzed by deriving and solving envelope equations. The evolution of the electron temperature and the radial expansion of the plasma beam are calculated self-consistently. The rate of decrease of the electron temperature due to the plasma radial expansion is affected by heat ...
A. Cohen-Zur, A. Fruchtman, A. Gany
openaire   +1 more source

Hall Effect Thruster with an AlN Chamber

AIP Conference Proceedings, 2006
The potential of AlN as a material for Hall thruster channels is assessed on the basis of actual thruster performances, computer simulations of the discharge and microscopy studies of an eroded channel. Comparison of experimental and numerical data provides further evidence that secondary electron emission (SEE) is the main phenomena responsible for ...
openaire   +1 more source