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3 edition of Applied-field MPD thruster geometry effects found in the catalog.

Applied-field MPD thruster geometry effects

Applied-field MPD thruster geometry effects

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Published by Sverdrup Technology, Inc., National Aeronautics and Space Administration, Lewis Research Center in Brook Park, Ohio, Cleveland, Ohio .
Written in English

    Subjects:
  • Space vehicles -- Electric propulsion systems.,
  • Plasma (Ionized gases)

  • Edition Notes

    Other titlesApplied field MPD thruster geometry.
    Statementby Roger M. Myers.
    SeriesNASA contractor report -- 187163., NASA contractor report -- NASA CR-187163.
    ContributionsLewis Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18063208M

    Critical applied-field MPD thruster technical issues remain to be resolved, including demonstration of reliable steady-state operation at input powers of hundreds to thousands of. Leveraging Technology to Reduce Patient Transaction Costs. PubMed. Edlow, Richard C.   The second with the advancement of steady-state magnetoplasmadynamic (MPD) thruster technology at kW to multimegawatt input power levels. The major technology issues for ion propulsion are demonstration of adequate engine life at the 5 to 10 kW power level and scaling ion engines to power levels of tens to hundreds of kilowatts. final annotated source list - Free download as Word Doc .doc /.docx), PDF File .pdf), Text File .txt) or read online for free. Scribd is the world's largest social reading and publishing site. Search Search.


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Applied-field MPD thruster geometry effects Download PDF EPUB FB2

Geometric Effects in Applied-Field MPD Thrusters R.M. Myers Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio M. Mantenieks and J. Sovey National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Abstract Three applied-field MPD thruster geometries were tested with argon propellant to.

Applied-Field MPD Thruster Geometry Effects Roger M. Myers Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio (NA_A-CR-l_) A°PLIFO-FIELD MPD TNRUSTER GEOMETRY EFFECT_ Fin_1 _eporL (Sver_lrup Techno|o_y) 36 p CSCL 21H G3/20 N Unc1_s _81 August Prepared for Lewis Research Center Under Contract NAS File Size: 1MB.

Get this from a library. Applied-field MPD thruster geometry effects. [Roger M Myers; Lewis Research Center.]. with the thruster geometry and plasma physics included in the relations for V and T. The system model reduces the number of free variables to only 2, from which all other parameters are derived.

An experimental investigation of a pulsed, quasi-steady, kW-class applied-field magnetoplasmadynamic thruster is discussed.

Measurements were. title = "Theoretical model for applied-field MPD thrusters", abstract = "Numerical modeling of the NASA LeRC kW, steady-state, applied-field MPD thruster is performed using the magnetohydrodynamics code, MACH2, for a range of applied magnetic field strengths and discharge by: 7.

Simple Thrust Formula for an MPD Thruster with Applied-Magnetic Field from Magnetic Stress Tensor M The purpose of this work is to develop an easy-to-use theory to predict the thrust generated by an applied-field MPD thruster and compare it with the experimental data. representing the thruster.

Hence, assuming a cylindrical geometry for. the forces acting on plasma can be expressed as the flux of the tensor B through the boundary surface of the volume V representing the thruster.

The control surface of an MPD with cylindrical geometry is reported in Fig. Download: Download full-size image; Fig. Thruster geometry and integration by: Fig. 3 shows the schematic of the experimental setup. We adopted an applied-field 2D-MPD thruster with coils wound on both sides of a rectangular thruster head, and a Th-W rod is used for each anode and cathode.

The power source developed in the previous research is used for discharge between electrodes Applied-field MPD thruster geometry effects book the external coil respectively. A magnetoplasmadynamic (MPD) thruster (MPDT) is a form of electrically powered spacecraft propulsion which uses the Lorentz force (the force on a charged particle by an electromagnetic field) to generate thrust.

It is sometimes referred to as Lorentz Force Accelerator (LFA) or (mostly in Japan) MPD arcjet. Generally, a gaseous material is ionized and fed into an acceleration chamber, where the.

Some ten years ago this was extended to applied-field MPD thrusters as these devices can also cope with moderate to low powers while the former need a certain minimum power in order to produce the self-induced magnetic fields to an adequate extend6,7,8,9.

Break through results for the AF MPD thruster SX3 referring to the. Roger Metcalf Myers has written: 'MPD thruster technology' -- subject(s): Electric propulsion systems, Space vehicles, Nuclear propulsion 'Applied-field MPD thruster geometry effects' -- subject(s. A Critical Review of Thrust Models for Applied-Field Magnetoplasmadynamic Thrusters: 53rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference: Will Coogan, Edgar Choueiri: MPD,jpc,magnetoplasmadynamic,AF-MPD: Applied-Field Topology Effects on the Thrust of an MPDT: 35th International Electric Propulsion Conference: Will Coogan, Edgar.

This work investigated the effects of tailored, externally-applied magnetic fields on current transport and near-anode processes in the plasma discharge of a magnetoplasmadynamic thruster (MPDT).

Electrical and plasma diagnostics were used to determine whether applied magnetic fields could mitigate the effects of the "onset" phenomena, including large-amplitude terminal voltage fluctuations Author: Robert Carlos Moeller.

MPD Operation Image right: Overview of magnetoplasmadynamic (MPD) thruster operation. Credit: NASA In its basic form, the MPD thruster has two metal electrodes: a central rod-shaped cathode, and a cylindrical anode that surrounds the cathode. Just as in an arc welder, a high-current electric arc is struck between the anode and cathode.

Introduction Anode power deposition has long been identi ed as the main power dissipation mechanism in MPD thrusters and was shown to account for most of the thruster input power.5,6,20,24 Since anode power fraction is high at low thruster power, low power MPD.

Numerical Study on Plasma Flowfield and Performance of Magnetoplasmadynamic Thrusters Kenichi KUBOTA Supervisor: Prof. Yoshihiro OKUNO Department of Energy Sciences Tokyo Institute of Technology January, Thus the intensity of magnetization M at every stage lags behind the applied field H Applied-Field MPD Thruster Geometry Effects Roger M.

Myers _ Sverdrup Technology, Inc. NASA Lewis Research Center Group Brook Park, OH Abstract Eight MPD thruster configurations were used to study the effects of applied-field strength, propellant, and. Applied-field magnetoplasmadynamic thrusters, Part 2: analytic expressions for thrust and voltage The new visualization of applied-field magnetoplasmadynamic thruster operation offered by numerical simulations with the MACH2 code is used to develop an analytic model.

Applied-field magnetoplasmadynamic thrusters, Part 2: analytic Cited by: The thrust performance of a steady-state, applied-field magnetoplasmadynamics (MPD) thruster has been improved by increasing a discharge current was increased from 20 A to 60 A using a lanthanum hexaboride (LaB 6) hollow experimentally obtained thrust characteristics were consistent with that of electromagnetic by: 1.

Until now, for relatively low-power classes of MPD thrusters, e.g. applied-field type or repetitive-pulse type, thruster design is established at a very high level. Actually, radiation cooled steady-state devices of applied-field MPD thruster have been operated in laboratories and radiation cooled repetitivepulse devices9,10 have been.

Numerical analysis of real gas MHD flow on two-dimensional self-field MPD thrusters Carlos M. Xiston, José C.

Páscoa, flow in applied-field MPD thrusters have also been pro-posed in the subsequent years [14,22,8]. The earlier Here the effects due to the geometry of the anode and the cathode, and the influence of mass flow rate.

The facility, at which MPD thruster were tested, is a vacuum chamber of 7 m length and 10 m'. The vacuum chamber pressure is sustained to be of torr. During a test the thruster on alkali metals, the vacuum chamber pressure is decreasing. To supply a liquid lithium into the thruster, a.

A time dependent, 2-dimensional axisymmetric MHD simulation code, MACH 2, is adopted to model both self-field and applied-field magneto-plasmadynamic thrusters. One of the NASA Lewis MPD thruster configurations is considered with operation at amp discharge current and g/s mass flow rate.

The paper describes a novel mathematical model to study the physics of fully ionized plasma flow through MPD thrusters otherwise known as magnetoplasmadynamic thrusters.

The developed model consist Author: S Vijai Kumar, S Thanigaiarasu. The thruster can operate in both self-field and applied-field MPD configuration as an external coil can produce an axial quasi-steady magnetic (B ext) up to mT on the thruster axis. Magnetohydrodynamics (MHD) is a branch of physics and engineering that investigates the effects of a magnetic field on the motion of an electrically conducting fluid.

Although the term 'magnetohydrodynamics' and its acronym MHD may be somewhat misleading, it is often used to designate physical phenomena in which the conducting fluid is not a.

I worked on different ESA and EU research projects and designed our first kW-class applied-field MPD thruster for future high-power space missions.

My proudest accomplishment was a collaboration with the Moscow Aviation Institute (RIAME-MAI) to develop a set of high-current multi-channel hollow cathodes that successfully operated for many.

Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of.

The contributions of ideal, resistive, and Hall effects are examined in isolation and in combination against available analytical and computational results. We also simulate the evolution of a laminar MHD jet subject to an externally applied magnetic field.

This configuration is of much importance in the field of plasma by: 3. 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 25 July - 28 July Nashville, TN. eISBN: Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster.

Georg Herdrich, A. Boxberger, D. Petkow, R Injector Geometry Effects on Cryogenic Coaxial. This banner text can have markup.

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The engine proposed here uses a deuterium–helium-3 reaction to produce fusion energy by employing a novel field-reversed configuration (FRC) for Cited by: 5. Full text of "Numerical Modeling of a Vortex Stabilized Arcjet" See other formats. basic text on mpd thrusters.

heat exchange and pressure drop enhanced by violent sloshing author / creator: himeno, t advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster. injector geometry effects on cryogenic coaxial jets at supercritical pressures.

Ion Propulsion and accelerator industrial applications (IPAIA) This workshop will provide a forum for the presentation and discussion on the progress in methods and technologies used for the research, development and industrial applications of ion propulsion (IP) for satellite and spacecraft.

IP is a class of space propulsion which makes use of electrical power to ionize and accelerate a. Performance Measurements of an MPD Thruster with a Diverging Exp Robert Thomas; James H. Gilland View Presentation Experimental Investigation of Applied-Field Magnetoplasmadynamic T Institute of Space Systems Georg H.

Herdrich; Adam Boxberger View Presentation Investigation of Discharge in a Magnetoplasmadynamic Thruster (MP Applied Magnetic. Optimization of Civil Turbofan with Evolutionary Algorithms (English) Effects of Gas Generator Burn Rate Variability on Variable Flow Ducted Rocket Design and Performance.

Effect of Inter-electrode Geometry on the Performance of an Applied-field 2D MPD Thruster. Takubo, M. / Koizumi, H. Book Reviewer for McGraw Hill, Gordon and Breech, Edwards, Cambridge University Press publishers.

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KHAYMS, Lockheed Martin Corporation hrs hrs hrs AIAA AIAA AIAA The Effects of Background Analysis of a plasma test cell A Step Towards Electric Pressure on Hall Thruster including non-neutrality and Propulsion Testing Standards Operation.b), k) AE, AEAE ; AE electives x/x/x d) They will have the ability to analyze and design aerospace structural elements such as trusses, beams and thin walled structures, taking into account structural dynamics and aeroelastic effects.

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