Very-Near-Field Plume Investigation of the Anode Layer Thruster

Domonkos, Matthew T.; Gallimore, Alec D.; Marrese, Colleen M.; Haas, James M.

doi:10.2514/2.5536

Cited by 17 publications

(19 citation statements)

References 8 publications

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“…75 ) reaches 10...15 eV at the distance of 10...15 mm from the thruster exit. The obtained change of temperature along the radius of a plume is similar to data of work 87 .…”

Section: Results Of the Probe Measurementsmentioning

confidence: 99%

“…For instance, at typical for the D-55 TAL plume electron temperature T e ≤ 5 eV and number density N e ≤ 10 11 cm -3 (see Ref. 75,76 ) requirement (3.29) turns into: In the very near field of the plume and in the discharge region electron number density grows up to N e ≥ 10 12 eV and bulk of electrons have energies E e ≥ 10 eV there. In these conditions requirement (3.29) becomes much stricter: Transition probabilities and excited state lifetimes in xenon were reported in quite a few of publications (see for example Ref.…”

Section: Applicability Of the Developed Crm In The Het Plasmamentioning

confidence: 99%

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Studying of Atomic and Molecular Interaction Processes in Rarified Hypervelocity Expanding Flows by Methods of Emissive Spectroscopy

Karabadzhak¹

2004

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“…75 ) reaches 10...15 eV at the distance of 10...15 mm from the thruster exit. The obtained change of temperature along the radius of a plume is similar to data of work 87 .…”

Section: Results Of the Probe Measurementsmentioning

confidence: 99%

Section: Applicability Of the Developed Crm In The Het Plasmamentioning

confidence: 99%

Studying of Atomic and Molecular Interaction Processes in Rarified Hypervelocity Expanding Flows by Methods of Emissive Spectroscopy

Karabadzhak¹

2004

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“…1 for a typical stationary plasma thruster configuration. The guidelines and recommendations in this paper are based primarily on numerous past experiments with stationary plasma thrusters; however, the paper is applicable to alternative HET configurations, including nested channel HETs and the thruster with anode layer variants [7][8][9]. In HETs, a constant potential difference is applied between the anode and cathode, where the cathode may be located external to the thruster body (as in Fig.…”

Section: A Electric Propulsion Technologiesmentioning

confidence: 99%

Recommended Practice for Use of Faraday Probes in Electric Propulsion Testing

Brown

Walker

Szabo

et al. 2017

Journal of Propulsion and Power

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Faraday probes are a common plasma diagnostic used to determine the local ion charge flux of electric propulsion plumes. Standard practices, guidelines, and recommendations are provided for experimental methods and analysis techniques that aim to standardize community practices, to mitigate test environment effects, and to reduce systematic measurement error in order to improve plume predictions in the space environment. The approaches are applicable to time-averaged plasma properties in the near-field and far-field of electric propulsion plumes, with emphasis on Hall effect thrusters and gridded ion thrusters. Considerations for other electric propulsion technologies are provided, including electrosprays, arcjets, and electromagnetic thruster concepts. These test strategies are expected to increase the quality of comparisons between different thrusters and vacuum environments, thereby broadening the applicability of ground-based measurements and enhancing the fidelity for on-orbit predictions and modeling validation.

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“…M. T. Domonkos at PEPL used a Hall probe to map the magnetic topography near the exit of D55. 6 Due to large perturbations in the discharge, the measurement was carried out 15 mm down the exit plane. Peter Y. Peterson 4 used a B-dot probe with a High-speed Axial Reciprocating Probe (HARP) system to measure the internal magnetic topography.…”

Section: Introductionmentioning

confidence: 99%

Magnetic field deformation due to electron drift in a Hall thruster

Han

Ding

et al. 2017

AIP Advances

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The strength and shape of the magnetic field are the core factors in the design of the Hall thruster. However, Hall current can affect the distribution of static magnetic field. In this paper, the Particle-In-Cell (PIC) method is used to obtain the distribution of Hall current in the discharge channel. The Hall current is separated into a direct and an alternating part to calculate the induced magnetic field using Finite Element Method Magnetics (FEMM). The results show that the direct Hall current decreases the magnetic field strength in the acceleration region and also changes the shape of the magnetic field. The maximum reduction in radial magnetic field strength in the exit plane is 10.8 G for an anode flow rate of 15 mg/s and the maximum angle change of the magnetic field line is close to 3° in the acceleration region. The alternating Hall current induces an oscillating magnetic field in the whole discharge channel. The actual magnetic deformation is shown to contain these two parts.

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Very-Near-Field Plume Investigation of the Anode Layer Thruster

Cited by 17 publications

References 8 publications

Studying of Atomic and Molecular Interaction Processes in Rarified Hypervelocity Expanding Flows by Methods of Emissive Spectroscopy

Studying of Atomic and Molecular Interaction Processes in Rarified Hypervelocity Expanding Flows by Methods of Emissive Spectroscopy

Recommended Practice for Use of Faraday Probes in Electric Propulsion Testing

Magnetic field deformation due to electron drift in a Hall thruster

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