Scaling of 100 kW class applied-field MPD thrusters

Myers, Roger

doi:10.2514/6.1992-3462

Cited by 18 publications

(13 citation statements)

References 6 publications

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“…10 addresses propellant-type effects, comparisons of the argon thrust further support the preceding scaling because it is calculated at yet another mass-ow-rate setting. The discrepancy in the slope may be caused by experimentally observed instabilities, 8 which did not allow data collection beyond 0.07 T.…”

Section: Comparisons With Experimentsmentioning

confidence: 98%

“…The anode fall voltage was calculated from measurements of the heat deposited into the electrodes' cooling water. 8 Ion heat conduction to the walls could not be separately accounted for, which will tend to overestimate the fall voltages and in turn underestimate the plasma voltage. The high ion temperatures present, caused by the viscous heating, may account for the heat conduction discrepancy, which is of the order of 4-5 V.…”

Section: Comparisons With Experimentsmentioning

confidence: 98%

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Applied-Field Magnetoplasmadynamic Thrusters, Part 2: Analytic Expressions for Thrust and Voltage

Mikellides

Turchi

2000

Journal of Propulsion and Power

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The new visualization of applied-eld magnetoplasmadynamic thruster operation offered by numerical simulations with the MACH2 code is used to develop an analytic model. This model provides simple expressions for the thrust and voltage drop across the plasma that capture all of the trends and in most cases the magnitudes of a wide range of experimental data including tests at multiple laboratories on three propellants: argon, hydrogen, and lithium. It establishes that the thrust scales as the square root of the product of the applied-eld strength, discharge current, and mass-ow rate. Voltage scales linearly with applied-eld strength and is independent of discharge current and mass-ow rate. This model also provides additional insights that can be used to improve applied-eld magnetoplasmadynamicthruster performance. NomenclatureA = atomic weight, amu a = cathode radius to electrode length ratio, r c / L B = magnetic induction, T I = discharge current, A j = current density, A/m 2 L = electrode length, m Çm = mass-ow rate, kg/s p = pressure, N/m 2 Q = cross section, m 2 R = electrode radius ratio, r a / r c R = speci c gas constant, m 2 /s 2 -K Rm = magnetic Reynolds number r a = anode radius, m r c = cathode radius, m T H = heavy particle temperature, K U = characteristic speed, IB/ l , m/s V = discharge voltage, V V emf = electromotive voltage, V V f = fall voltage, V V p = plasma voltage, V V RH = resistive + Hall voltage, V v = axial velocity, m/s w = azimuthal velocity, m/s Z = charge number a = degree of ionization g F = ow ef ciency k = mean free path, m l = viscosity coef cient, kg/m-s q = mass density, kg/m 3 ¾ = stress tensor, N/m 2 } = ionization factor, i [a i / j a j Z 2 i Z 2 j ] X = Hall parameter Subscripts r, h , z = physical dimensions: radial, azimuthal, axial

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Section: Comparisons With Experimentsmentioning

confidence: 98%

Section: Comparisons With Experimentsmentioning

confidence: 98%

Applied-Field Magnetoplasmadynamic Thrusters, Part 2: Analytic Expressions for Thrust and Voltage

Mikellides

Turchi

2000

Journal of Propulsion and Power

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“…The term ranges from 50 -150 V and is empirically determined to best fit the data. However, experimental tests have demonstrated (Myers, 1992) that there is a physical basis for this fall voltage term, and that each thruster has its own characteristic fall voltage. …”

Section: Self-field Mpd Thruster Modelmentioning

confidence: 99%

MPD Thruster Performance Analytic Models

Gilland

Johnston

2003

AIP Conference Proceedings

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Abstract. Magnetoplasmadynamic (MPD) thrusters are capable of accelerating quasi-neutral plasmas to high exhaust velocities using Megawatts (MW) of electric power. These characteristics make such devices worthy of consideration for demanding, far-term missions such as the human exploration of Mars or beyond. Assessment of MPD thrusters at the system and mission level is often difficult due to their status as ongoing experimental research topics rather than developed thrusters. However, in order to assess MPD thrusters' utility in later missions, some adequate characterization of performance, or more exactly, projected performance, and system level definition are required for use in analyses. The most recent physical models of self-field MPD thrusters have been examined, assessed, and reconfigured for use by systems and mission analysts. The physical models allow for rational projections of thruster performance based on physical parameters that can be measured in the laboratory. The models and their implications for the design of future MPD thrusters are presented.

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“…[4][5][6][7][8][9] While we overview each of these components, our focus is on analytical models of the applied-field thrust since the mechanisms behind self-field thrust are simpler and far better understood, 10,11 and because gasdynamic thrust is negligible under nominal operating conditions. 9,12,13 There are many applied-field thrust models, 1,5,7,9,[12][13][14][15][16] but what is lacking is a comparison of each of them to measurement across a large parameter space.…”

Section: Introductionmentioning

confidence: 99%

A Critical Review of Thrust Models for Applied-Field Magnetoplasmadynamic Thrusters

Coogan

Choueiri

2017

53rd AIAA/SAE/ASEE Joint Propulsion Conference

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A critical review of published thrust models for applied-field magnetoplasmadynamic thrusters is presented, along with a new model addressing shortcomings related to electrode and magnet geometry. While numerous theoretical thrust models have been presented in the literature, there has not been a comprehensive comparison to determine which best predicts thruster behavior across a large parameter space. In order to make this determination, all thrust data available in the literature were collected into a single database and tested against each model. Unlike previous comparisons between prediction and measurement, only the regime in which the applied-field thrust component dominates is examined, allowing for a direct comparison without invoking models of self-field and gasdynamic components of thrust. The degree to which each model deviates from measurement is determined for each controllable parameter. It is found that the largest deviations are due to incorrect representation of the effects of electrode and solenoid geometries. In light of this comparative study, an improved empirical model is derived as a function of nondimensional parameters representing these geometric variables. The improved agreement is attributed to the effects of magnetic field topology near the anode, which sets the effective anode radius that controls the magnitude of the Lorentz force for certain electrode geometries.

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Scaling of 100 kW class applied-field MPD thrusters

Cited by 18 publications

References 6 publications

Applied-Field Magnetoplasmadynamic Thrusters, Part 2: Analytic Expressions for Thrust and Voltage

Applied-Field Magnetoplasmadynamic Thrusters, Part 2: Analytic Expressions for Thrust and Voltage

MPD Thruster Performance Analytic Models

A Critical Review of Thrust Models for Applied-Field Magnetoplasmadynamic Thrusters

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