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3 edition of Preliminary far-field plume sputtering characterization of the stationary plasma thruster (SPT--100) found in the catalog.

Preliminary far-field plume sputtering characterization of the stationary plasma thruster (SPT--100)

Preliminary far-field plume sputtering characterization of the stationary plasma thruster (SPT--100)

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Electric propulsion.

  • Edition Notes

    Other titlesPreliminary far field plume sputtering ....
    StatementEric J. Pencil.
    SeriesNASA technical memorandum -- 106464
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17111906M

    The plasma plume expansion could also lead to the generation of shockwaves. In addition, the laser-matter interactions are associated with mechanical stress due to thermal expansion or the propagation of shockwaves, which can cause another kind of ablation by spallation if the amplitude exceeds the binding strength of the lattice within the target. Modeling of the Plasma Jet of a Stationary Plasma Thruster - Free download as PDF File .pdf), Text File .txt) or read online for free. Modeling of the Plasma Jet of a Stationary Plasma Thruster.

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Preliminary far-field plume sputtering characterization of the stationary plasma thruster (SPT--100) Download PDF EPUB FB2

Get this from a library. Preliminary far-field plume sputtering characterization of the stationary plasma thruster (SPT).

[Eric J Pencil; United States. plume is therefore more energetic than a resistojet plume. As a result of the arc, electronic excitation, ionization, and dissociation occur in the nozzle.

Immediately downstream of the nozzle, the plume is a rapidly-expanding, partially-ionized plasma in which recombination and de-excitation take place.

In order. 10 Lau, M. and Herdrich, G., “Plasma diagnostic with inductive probes in the discha rge channel of a pulsed plasma thruster,” Vacuum, pp. The simulation of stationary plasma thruster plume is important for spacecraft design due to possible interaction plume with spacecraft surf ace.

Such simulations are. a follow up to a previous study 5 where only partial far-field planes of a PPT were examined.

The objective of the research presented in this article was to determine the symmetry/asymmetry of a PPT plume by characterizing the films deposited on local witness plates.

The films collected from the thruster discharge were characterizedFile Size: 1MB. from the far field to very near field of a Hall thruster plume.

Recent work in this vein has applied statistical methods to create transfer functions between the thruster discharge current and spatially resolved plume plasma properties, permitting a time-resolved reconstruction of plume properties from temporally disparate probe measurements.

on how the plasma potential in the thruster plume and the ionization and acceleration processes internal to the thruster were affected by changes of the magnetic field and discharge voltage.

EXPERIMENTAL APPARATUS The thruster hardware and configuration were the same as the experiments reported in Ref. This included the thruster, power. Computer models of Hall thruster plumes play an important role in integration of these devices onto spacecraft as the space environment is not easily reproduced in ground testing facilities.

In this article, a hybrid particle-fluid model of a Hall thruster plume is applied to model the SPT thrusters used on the Russian Express by:   This site uses cookies. By continuing to use this site you agree to our use of cookies. To find out more, see our.

Far-field plume contamination and sputtering of the stationary plasma thruster. Randolph, E. Pencil and; Preliminary characterization of a low power end-Hall thruster. Alec Gallimore, Mark Reichenbacher, Stationary plasma thruster ion velocity distribution.

David Manzella. Ion species fractions in the far-field plume of a high-specific impulse Hall thruster Richard R. Hofer* † QSS Group, Inc. NASA Glenn Research Center Cleveland, OH USA @ Alec D. Gallimore Plasmadynamics and Electric Propulsion Laboratory University of Michigan Ann Arbor, MI USA ABSTRACT.

thruster exit) to the near- and far-field region (25 cm to 1 m downstream of the thruster exit). Although there have been many studies of Hall thruster plume characteristics, the combined data of the very-near-field and the near- and far-field plume studies provided the most comprehensive collection of plasma parameters in the Hall thruster by: In operation, gaseous xenon effuses from the thruster acceleration channel.

The plume consists of light electrons with thermal speeds of 1 × 10 6 m / s, and heavier ions or neutrals, such as fast single or double charged ions, Xe +, Xe + +, slow neutral xenon, fast neutral xenon, and slow ions due to of these xenon atoms are ionized, then accelerated by the electric field in Cited by: 9.

Effect of magnetic field configuration on the multiply charged ion and plume characteristics in Hall thruster plasmas Holak Kim,1 Youbong Lim,1 Wonho Choe,1,a) Sanghoo Park,1 and Jongho Seon2 1Department of Physics, Korea Advanced Institute of Science and Technology Daehak-ro, Yuseong-gu, DaejeonRepublic of KoreaCited by: 9.

Electric Propulsion Introduction Specific impulse Types of electric propulsion Electrothermal hydrazine thruster Hydrazine arcjet Ion thruster Stationary plasma thruster Magneto-hydrodynamic Pulsed plasma thruster Performance comparison Solar PV propulsion Solar thermal.

An Electric Propulsion diagnostic package for the characterization of the plasma thruster/spacecraft interactions on STENTOR satellite Modeling of a pulsed plasma thruster from plasma generation to plume far field. Iain Boyd, Michael Signal processing and non-linear behavior of a Stationary Plasma Thruster - First results.

Gascon, C. H. Kamhawi et al., "Performance, Stability, and Plume Characterization of the HERMeS Thruster with Boron Nitride Silica Composite Discharge Channel", IEPC ASTM C, "Standard Test Method for Monotonic Compressive Strength of Advanced Ceramics at Ambient Temperature". В журнале "Вестник Московского авиационного института" публикуются оригинальные научно-технические статьи.

Full text of "NASA Technical Reports Server (NTRS) Research and Technology " See other formats. Stationary force production: experimental and theoretical investigations V.

Apollonov Proc. SPIEHigh-Power Laser Ablation VII, (15 May ); doi: /. Full text of "NASA Technical Reports Server (NTRS) Bibliography of Lewis Research Center Technical Publications announced in " See other formats.Computer Physics Communications Vol NumberNovember / December, I. J. Thompson and A.

R. Barnett Modified Bessel functions $ I_\nu (z) $ and $ K_\nu (z) $ of real order and complex argument, to selected accuracy   Nesting/clustering moderately powered thrusters to reach a desired total throughput: This component development can include: an assessment of system performance and plasma plume interactions, a thermal characterization of the system, and an assessment of the system lifetime during multi-thruster operation.