Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster

Herdrich, Georg; Boxberger, Adam; Petkow, Dejan; Gabrielli, Roland; Fasoulas, Stefanos; Andrenucci, Mariano; Albertoni, Riccardo; Paganucci, Fabrizio; Rossetti, P.

doi:10.2514/6.2010-6531

Cited by 16 publications

(13 citation statements)

References 3 publications

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“…where c s is the ion sound speed and k GD is a nondimensional coefficient on the order of unity. [4][5][6][7][8][9] The magnitude of k GD has been modeled as being dependent on the angle of the gas flow with respect to the thrust axis 6 or as a function of an additional pressure acting over the area of the injection site. 32 Ref.…”

Section: Gasdynamic Thrust Componentmentioning

confidence: 99%

“…The thrust of an AF-MPDT is typically assumed to be the sum of the applied-field, self-field, and gasdynamic thrust components. [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%

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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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Section: Gasdynamic Thrust Componentmentioning

confidence: 99%

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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“…One thruster that can benefit from isolated-component thrust measurements is the applied-field Lorentz force accelerator (AF-LFA), for which various models of its applied-field thrust component have been proposed [1][2][3][4][5][6][7]. However, applied-field component thrust stands in the literature are limited to low-current (≤ 6 A) solenoids [8], and they are poorly suited to the high currents typical of AF-LFAs, which require cooling and a means of calibrating for electromagnetic tare forces.…”

Section: Introductionmentioning

confidence: 99%

Method for Measuring the Applied-Field Thrust Component of Plasma Thrusters

Coogan

Hepler

Choueiri

2018

Journal of Propulsion and Power

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“…The applied-field magnetoplasmadynamic thruster (AF-MPDT) is a high thrust-density electric propulsion device typically consisting of an annular anode surrounding a central cathode with a solenoid generating a magnetic field along the thrust axis. Many theoretical thrust models have been presented for the AF-MPDT, [1][2][3][4][5][6][7] and while there is a general consensus that the thrust is proportional to both the current through the electrodes and the strength of the applied magnetic field, a complete model in terms of controllable parameters, such as the propellant type, mass flow rate, electrode geometry, applied-field strength, and thruster current, has yet to be agreed upon.…”

Section: Introductionmentioning

confidence: 99%

“…where T AF is the applied-field thrust component, T is the total thrust, T SF is the self-field thrust component, and T GD is the gasdynamic thrust component. 2,[5][6][7] While this theoretically provides the AF thrust component, the magnitude of the error on the final value is undeterminable without individual measurements of T SF and T GD along with the corresponding error on each component. Tahara et al inferred values of each of the three components through the measurement of pressure, current, and magnetic field distributions within the thruster volume, 3 but this is still an indirect measurement of the force from each component with undeterminable error.…”

Section: Introductionmentioning

confidence: 99%

Measurement of the Applied-Field Component of the Thrust of a Lithium Lorentz Force Accelerator

Coogan

Hepler

Choueiri³

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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The operation of an inverted-pendulum thrust stand designed to directly measure the applied-field thrust component of a steady-state applied-field magnetoplasmadynamic thruster is presented. This measurement, which is necessary for improving and validating thrust models, is achieved by mechanically isolating the solenoid from the thruster so that the solenoid can move independently. The deflection of the solenoid is compared to deflection by known forces to determine the applied-field thrust component. The thrust stand is found to be accurate to ±9 mN over a total range of 1200 mN. Two measurement methods are implemented to account for tare forces resulting from azimuthal currents to the thruster electrodes and are shown to agree with one another. As a proof-of-concept, the first direct measurements of the applied-field component of the thrust from a 30 kW lithium Lorentz force accelerator operating at 400 A, 8 mg/s lithium mass flow rate, and 0.056 T applied-field strength give a measured force of 108 ± 14 mN. This measurement agrees with the value predicted by measuring the total thrust and subtracting out all other thrust components. Nomenclature a 0 Ion sound speed, m/s A Area, m 2 B A Applied magnetic field, T J Current, A k Thrust coefficienṫ m Mass flow rate, kg/s p Pressure, N/m 2 r Electrode radius, m T Thrust, N Subscript ae Anode exit plane AF Applied-field c Cathode GD Gasdynamic SF Self-field

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Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster

Cited by 16 publications

References 3 publications

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

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

Method for Measuring the Applied-Field Thrust Component of Plasma Thrusters

Measurement of the Applied-Field Component of the Thrust of a Lithium Lorentz Force Accelerator

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