Experiments using a 25-kw hollow cathode lithium vapor MPD arcjet

Fradkin, D. B.; Blackstock, A. W.; Roehling, D. J.; Stratton, T. F.; Williams, Michael R.; Liewer, K.W.

doi:10.2514/3.5783

Cited by 67 publications

(12 citation statements)

References 11 publications

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“…Fradkin et al derive an expression for the total amount of azimuthal kinetic energy generated by the torque produced as a result of the cross product of the radial current and axial applied magnetic field within a cylindrical anode volume. 1 This energy is presented as an upper limit for the total amount of energy available for conversion into axial kinetic energy. Assuming all of the energy is converted, the corresponding thrust generated is…”

Section: Thrust Model Comparisonmentioning

confidence: 99%

“…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%

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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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Section: Thrust Model Comparisonmentioning

confidence: 99%

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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“…3. The close coupling of the magnetic helicity injection electrodes (which are also the termination points of the connected divertor field lines) with the fusion plasma may impose more severe conditions on these surfaces with regard to erosion and sputtering than for conventional divertor components; however, experiments with magnetoplasmadynamic arcs 21 The program plan for the davelopment of the RFP confinement system has two specific goals: "The advancement of the data base for axisymmetric toroidal, high beta, confinement systems; and the assessment of the physics and technology required foj: compact high-energy-density fusion reactor systems." 26 The critical issues that involve PMI and HHF issues are as follows:…”

Section: Remote Maintenancementioning

confidence: 99%

Technical assessment of critical Plasma-Materials Interaction (PMI) and High Heat Flux (HHF) issues for alternative fusion concepts (AFCs)

Downing¹

1986

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“…98,99 There has been a large number of prototypes developed and tested since the 1960s, varying largely in the power range (from few kW to MW), propellants employed (Argon, Hydrogen, Helium, Ammonia, Alkali vapours like Lithium or Cesium), and thruster configuration. 97,98,[100][101][102][103][104][105][106][107][108][109][110][111][112][113][114][115] Likewise, there has been a research effort in the modeling of the physical processes and the scaling laws of the performance figures. 15,100,106,[116][117][118][119] Good reviews of these developments can be found in the works of Kodys et al, 120 and Krülle et al 98 So far, one of the highest performance figures achieved are those of the Moscow Aviation Institute, who have obtained 50% thrust efficiency at I sp = 42 km/s with a 200 kW lithium thruster.…”

Section: Applied-field Magnetoplasmadynamic Thrustersmentioning

confidence: 99%

“…97,98,[100][101][102][103][104][105][106][107][108][109][110][111][112][113][114][115] Likewise, there has been a research effort in the modeling of the physical processes and the scaling laws of the performance figures. 15,100,106,[116][117][118][119] Good reviews of these developments can be found in the works of Kodys et al, 120 and Krülle et al 98 So far, one of the highest performance figures achieved are those of the Moscow Aviation Institute, who have obtained 50% thrust efficiency at I sp = 42 km/s with a 200 kW lithium thruster. 121 While these data are encouraging, current knowledge of the AF-MPD is limited, and there is still a long way ahead until these thrusters become commercially competitive.…”

Section: Applied-field Magnetoplasmadynamic Thrustersmentioning

confidence: 99%

Analysis of Magnetic Nozzles For Space Plasma Thrusters = Análisis de Toberas Magnéticas para Motores Espaciales de Plasma

Martínez¹

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This Thesis presents a theoretical analysis of the operation of magnetic nozzles for plasma space propulsion. The study is based on a two-dimensional, two-fluid model of the supersonic expansion of a hot plasma in a divergent magnetic field. The basic model is extended progressively to include the dominant electron convective terms, the plasma-induced magnetic field, multi-temperature electron populations, and the capability to integrate the plasma flow in the far expansion region. The hyperbolic plasma response is integrated accurately and efficiently with the method of the characteristic lines.Special acknowledgments go to the rest of members of the EP2 (Equipo de Propulsión Espacial por Plasmas) research group at UPM, in particular to my colleague and collaborator Jaume Navarro, with whom I have shared many moments (and coffees). My thanks to all the members of the department, specially Robert Santos, for their friendly support and reassuring presence all along the way. I shall v vi ACKNOWLEDGMENTS not forget my friends from the Physics department, Hodei, Claudio, Gonzalo, Sandra, Antonio, Bayajid, Arnaud, Xin, Juancho, and the rest of my friends at the ETSI Aeronáuticos and elsewhere: you have always managed to make me smile and blow away some stress, and I have always valued the richness in viewpoints of our 'international' group (there are 5 nationalities alone in the people I have named). Laura, Carol, Manu, Pepe, Vero: I am lucky to have met you all and count you among my friends.Marijke Frank deserves a full paragraph just for herself. You have brought life and light to my world, and I could not have probably made this climb without you. You are all sweetness and energy and music. Thank you for the moments we share, and for your support and understanding during my Thesis-journey. Also, thank you for applying your near-native English to correct the introductory Chapters of this text.I want to thank Prof. Manuel Martínez-Sánchez at MIT for the interest he has shown in this Thesis, and for all his intelligent comments on the role of the plasma-induced magnetic field: I value much our discussions, which I hope we will continue to share after this Thesis.I am indebted to Prof. Georg Herdrich, Adam Boxberger and Tomeu Massuti at IRS Stuttgart, Germany, for inviting me to visit their institute for three months and participate in their work. It has been a great learning experience for me. Also, I would like to thank Käthe Dannenmayer and Stéphane Mazouffre at ICARE-CNRS, Orléans, France, for accepting to initiate a comparison of self-similar plasma plume models with their experimental data on two Hall-effect thrusters. Likewise, I deeply appreciate the work done with Claudio Bombardelli, Hodei Urrutxua, and Jesús Peláez, at UPM, and Dejan Petkow and Leopold Summerer, at ESTEC, ESA, regarding the study of the Ion Beam Satellite.Lastly, my thanks go to the members of the Committee for agreeing to review and evaluate my work, and to María García at ETSI Aeronáuticos, who has muddled through the cumbersome bureaucra...

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Experiments using a 25-kw hollow cathode lithium vapor MPD arcjet

Cited by 67 publications

References 11 publications

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

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

Technical assessment of critical Plasma-Materials Interaction (PMI) and High Heat Flux (HHF) issues for alternative fusion concepts (AFCs)

Analysis of Magnetic Nozzles For Space Plasma Thrusters = Análisis de Toberas Magnéticas para Motores Espaciales de Plasma

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