State of the Art of Physical Models of Vacuum Arc Cathode Spots

Rakhovsky, V. I.

doi:10.1109/tps.1987.4316741

Cited by 45 publications

(20 citation statements)

References 13 publications

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“…In several arc run experiments, the electron temperature was measured. The average T e was found to be about 2 eV, which agrees well with existing data for copper vacuum arcs [25][26][27].…”

Section: A Experimentssupporting

confidence: 88%

“…The adjusted inlet conditions corresponding to the best fit with experiment were as follows: temperature 2 eV, n e 5.6 × 10 13 cm −3 , inlet velocity is 1.3 × 10 6 cm∕s, ion charge Z i 1.8. Note that these plasma parameters are typical for vicinity of cathodic spot [17,26,32]. A constant electrical conductivity of 120 S∕m is assumed to describe diffusion of the magnetic field.…”

Section: B Numerical Simulation 1 Free Plasma Flow In Absence Of Blmentioning

confidence: 99%

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Laboratory Modeling of the Plasma Layer at Hypersonic Flight

Shashurin¹,

Zhuang²,

Teel³

et al. 2014

Journal of Spacecraft and Rockets

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A simple approach to modeling the plasma layer similar to that appearing in the vicinity of a hypersonic vehicle is demonstrated in a laboratory experiment. This approach is based on the use of a hypersonic jet from a cathodic arc plasma. Another critical element of this laboratory experiment is a blunt body made from a fairly thin foil of refractory material. In experiments, this blunt body is heated by the plasma jet to a temperature sufficiently high to ensure evaporation of surface deposits produced by the metallic plasma jet. This process mimics reflection of gas flow from the hypersonic vehicle in a real flight. Two-dimensional distributions of the hypersonic plasma flow around the blunt body were measured using electrostatic Langmuir probes. Measured plasma density was typically 10 12 cm −3 , which is close to the values measured for real hypersonic flight. The demonstrated laboratory experiment can be used to validate numerical codes for simulating hypersonic flight and to conduct ground-based tests for efficiency validation of various radio communication blackout mitigation techniques.

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Section: A Experimentssupporting

confidence: 88%

Section: B Numerical Simulation 1 Free Plasma Flow In Absence Of Blmentioning

confidence: 99%

Laboratory Modeling of the Plasma Layer at Hypersonic Flight

Shashurin¹,

Zhuang²,

Teel³

et al. 2014

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…Moreover, the cathode material of lower atomic weight yields a higher current density. For small size of cathode spot (10–100 μm), the total current can be approximated as

I = [π R_{c}^{2} - π {((), R_{c} - h)}^{2}] j (x) \approx (2 π R_{c} h) j (x)

, implying that the thrust can be further enhanced by increasing the inner radius of the vacuum arc thruster and expanding the annular spot radially more inward.…”

Section: Ring‐type Vacuum Arc Thrustermentioning

confidence: 99%

“…Moreover, the cathode material of lower atomic weight yields a higher current density. For small size of cathode spot (10-100 μm), [16][17][18] the total current can be approximated as…”

Section: Ring-type Vacuum Arc Thrustermentioning

confidence: 99%

Space‐charge‐limited current of vacuum arc thruster

Zhang¹,

Chang

et al. 2020

Contributions to Plasma Physics

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To optimize thrust performance, the expression of space‐charge‐limited current for vacuum arc thruster is derived from Poisson's equation. The commonly used ring‐type and coaxial‐type vacuum arc thrusters are simplified to the equivalent current sheet in planar geometry and cylindrical capacitor, respectively, for this calculation. Both the spatial distribution and peak magnitude of space‐charge‐limited current are given explicitly, together with their dependences on gap distance, applied voltage, charge number, and ion mass. For typical experimental parameters of the vacuum arc thruster, it is shown that the maximum current density drops significantly when the gap distance becomes large and grows when the applied voltage increases; moreover, a cathode material of lower atomic weight yields a higher current density. The expressions of total current for these two types of vacuum arc thruster are also presented. This work, to our best knowledge, is the first application of space‐charge‐limited current to the vacuum arc thruster and practically very interesting for engineering design.

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“…Such an approach has been widely employed and has given interesting and useful results (see, e.g., reviews [1,2] and references therein; we mention also recent studies [8,9]). Unfortunately, this approach is still incomplete.…”

Section: Introductionmentioning

confidence: 99%

Maxwell's construction for non-linear heat structures and modelling of electrode spots in arc discharges

Benilov

1998

Czech J Phys

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State of the Art of Physical Models of Vacuum Arc Cathode Spots

Cited by 45 publications

References 13 publications

Laboratory Modeling of the Plasma Layer at Hypersonic Flight

Laboratory Modeling of the Plasma Layer at Hypersonic Flight

Space‐charge‐limited current of vacuum arc thruster

Maxwell's construction for non-linear heat structures and modelling of electrode spots in arc discharges

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