On the model of Teflon ablation in an ablation-controlled discharge

Keidar, Michael; Boyd, Iain D.; Beilis, I. I.

doi:10.1088/0022-3727/34/11/318

Cited by 94 publications

(105 citation statements)

References 11 publications

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“…With an increase in E ext the ablation rate increases and, if E ext becomes much larger than conduction heat flux, we may drop the conduction heat term from the velocity distribution function (Eq. (3)), recovering the previous models [9][10][11][12][13][14]. and with an increase in α, the effect of thermal conduction decrease, E x increases and changes sign (becomes positive meaning that the total energy flux is directed upward, Fig.…”

Section: Let Us Introduce a Thermal Conduction Parametersupporting

confidence: 77%

“…(10) Equations (5), (6), (8) and (9) are identical to the corresponding mass and momentum conservation equations obtained in [10][11][12][13][14][15][16][17] while Eqs. (7) and (10) differ from the corresponding energy conservation equations [10][11][12][13][14][15][16][17] by the temperature gradient term, which is responsible for conduction heat flux to the ablative surface.…”

mentioning

confidence: 87%

“…Later these models were applied for the case of dielectric ablation into the discharge plasma in the capillary discharge conditions [12,13] and for the case of strong plasma acceleration [14]. All those analytical models neglected the conductive heat flux to the ablative surface.…”

mentioning

confidence: 99%

“…Assuming the conservation laws of mass, momentum and energy hold at all times within the discontinuity region, through the Knudsen layer, as it has been assumed in all previous models [9][10][11][12][13][14] (quasi steady state approximation within the Knudsen layer), the following integrals are defined:…”

mentioning

confidence: 99%

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Effect of thermal conductivity on the Knudsen layer at ablative surfaces

Pekker¹,

Keidar²,

Cambier³

2008

Journal of Applied Physics

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) 23-03-2007 REPORT TYPE Journal Article DATES COVERED (From -To) TITLE AND SUBTITLE 5a. CONTRACT NUMBER Effect of Thermal Conductivity on the Knudsen Layer at Ablative Surfaces (Preprint)5b DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited (PA #07151A). SUPPLEMENTARY NOTESSubmitted for publication in Physical Review E.. ABSTRACTIn this paper we develop an analytical model of Knudsen layer at the ablative wall taking into account the temperature gradient in the bulk gas. The region of validity of the existing models and effect of the temperature gradient on the Knudsen layer properties are calculated. AbstractIn this paper we develop an analytical model of Knudsen layer at the ablative wall taking into account the temperature gradient in the bulk gas. The region of validity of the existing models and effect of the temperature gradient on the Knudsen layer properties are calculated.

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Section: Let Us Introduce a Thermal Conduction Parametersupporting

confidence: 77%

mentioning

confidence: 87%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Effect of thermal conductivity on the Knudsen layer at ablative surfaces

Pekker¹,

Keidar²,

Cambier³

2008

Journal of Applied Physics

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“…This approach is widely used for plasma plume modeling in Hall thrusters. [33][34][35] From Eq. (8) and (9) we find that the electron temperature is proportional to the plasma potential:…”

Section: B Temperature Saturation Regimementioning

confidence: 99%

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

et al. 2005

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Secondary electron emission in Hall thrusters is predicted to lead to space charge saturated wall sheaths resulting in enhanced power losses in the thruster channel.Analysis of experimentally obtained electron-wall collision frequency suggests that the electron temperature saturation, which occurs at high discharge voltages, appears to be caused by a decrease of the Joule heating rather than by the enhancement of the electron energy loss at the walls due to a strong secondary electron emission.2

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On the Mechanism of Energy Transfer in the Plasma‐Propellant Interaction

Porwitzky

Keidar

Boyd

2007

Propellants Explo Pyrotec

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A coupled plasma sheath/ablation model is developed for electrothermal chemical gun applications. By combining a commonly employed collisional sheath model with a previous ablation model, the convective heat flux as a function of time to the propellant bed is determined for two potential electrothermal chemical gun propellants, XM39 and JA2. It is found that the convective heat flux varies smoothly from a nearly collisionless to a fully collisional regime over the short duration of the plasma pulse. The possibility of determining an accurate estimate of the amount of heat flux to the propellant bed due to radiation from the bulk plasma presents itself.

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On the model of Teflon ablation in an ablation-controlled discharge

Cited by 94 publications

References 11 publications

Effect of thermal conductivity on the Knudsen layer at ablative surfaces

Effect of thermal conductivity on the Knudsen layer at ablative surfaces

Space charge saturated sheath regime and electron temperature saturation in Hall thrusters

On the Mechanism of Energy Transfer in the Plasma‐Propellant Interaction

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