Evolution of the Ion Velocity Distribtuion in the Near Field of the BHT-200-X3 Hall Thruster

Hargus, William A.; Nakles, Michael R.

doi:10.2514/6.2006-4991

Cited by 22 publications

(19 citation statements)

References 7 publications

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“…The 30th International Electric Propulsion Conference, Florence, Italy, September [17][18][19][20]2007 Distribution A: Approved for public release; distribution unlimited.…”

Section: Of 19mentioning

confidence: 99%

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Nakles¹,

Brieda²,

Reed³

et al. 2007

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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) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory (AFMC) AFRL/PRS SPONSOR/MONITOR'S Pollux Drive NUMBER(S)Edwards AFB CA 93524-7048 AFRL-PR-ED-TP-2007-380 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution unlimited (PA #07313A). 14. ABSTRACT The plume of a Busek BHT-200 xenon Hall thruster has been characterized through measurements from various plasma electrostatic probes. Ion current flux, plasma potential, plasma density, and electron temperatures were measured from the near-field plume to 60 cm downstream of the exit plane. These experimentally derived measurements were compared to numerical simulations run with the plasma plume code DRACO. A major goal of this study was to determine the fidelity of the DRACO numerical simulation. The effect of background pressure on the thruster plume was also examined using ion current flux measurements at higher than nominal pressure. The plume of a Busek BHT-200 xenon Hall thruster has been characterized through measurements from various plasma electrostatic probes. Ion current flux, plasma potential, plasma density, and electron temperatures were measured from the near-field plume to 60 cm downstream of the exit plane. These experimentally derived measurements were compared to numerical simulations run with the plasma plume code DRACO. A major goal of this study was to determine the fidelity of the DRACO numerical simulation. The effect of background pressure on the thruster plume was also examined using ion current flux measurements at higher than nominal pressure.

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“…The 30th International Electric Propulsion Conference, Florence, Italy, September [17][18][19][20]2007 Distribution A: Approved for public release; distribution unlimited.…”

Section: Of 19mentioning

confidence: 99%

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Nakles¹,

Brieda²,

Reed³

et al. 2007

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“…Due to the relatively narrow line shape of the 834.68 nm xenon ion transition (∼600 Mhz) relative to the broad distributions of the near-plume LIF profiles, deconvolution is not strictly required to closely approximate xenon ion velocity distributions from the raw LIF data in the near-plume region of the BHT-200-X3. 8 Not performing the deconvolution introduces an uncertainty estimated to be less than 10%. This allows the presentation of less strenuously conditioned LIF data to provide a qualitative xenon velocity distribution, avoiding the noise inevitably amplified by the deconvolution process.…”

Section: Lif Measurementsmentioning

confidence: 99%

Comparison of Numerical and Experimental Near-Field Ion Velocity Distributions of the BHT-200-X3 Hall Thruster

Nakles¹,

Hargus²,

VanGilder³

2006

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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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) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)Air Force Research Laboratory (AFMC) AFRL/PRS SPONSOR/MONITOR'S Pollux Drive NUMBER(S)Edwards AFB ABSTRACTNear-field ion velocity distributions of a BusekBHT-200-X3 xenon Hall thruster obtained through numerical simulation are compared with laser-induced fluorescence measurements taken for one nominal operating condition. The numerical code Hybrid-PIC Hall, a 2D hybrid particle-in-cell model, is used to simulate an axisymmetric cross section of the plasma acceleration zone. A set of nine HP Hall simulations are run using three different cathode positions and Bohm electron mobility coefficients to study the effects of these parameters on ion acceleration. Six additional cases were run in an attempt to better match the simulation results to the experimental data. For model validation, agreement between the numerical and experimental results is examined. The results show that it is difficult to match both the global operational parameters (i.e, thrust, discharge current, and beam current) and the ion velocity distributions. The shape of the axial velocity distributions can be closely matched by using high Bohm electron mobility values. However, this correlation comes at the expense of peak ion velocity and discharge current agreement. Radial velocity distributions are more closely matched by the simulations, but the simulations uniformly predict lower than measured inward and higher than measured outward radial velocity components (relative to the centerline) from the annular acceleration channel. Near-field ion velocity distributions of a Busek BHT-200-X3 xenon Hall thruster obtained through numerical simulation are compared with laser-induced fluorescence measurements taken for one nominal operating condition. The numerical code Hybrid-PIC Hall, a 2D hybrid particle-in-cell model, is used to simulate an axisymmetric cross section of the plasma acceleration zone. A set of nine HPHall simulations are run using three different cathode positions and three different Bohm electron mobility coefficients to stud...

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“…The thrusters examined in those efforts were the BHT-200 [2,3] and the BHT-HD-600 [4,5]. Both of those thrusters are manufactured by the Busek Co., Inc..…”

Section: Comparison To Previous Studiesmentioning

confidence: 99%

“…For example, several studies using laser-induced fluorescence (LIF) techniques have characterized velocity distributions in the near-field region of 200 and 600 W Hall thrusters. The thrusters examined in those studies were the commercially available BHT-200 and BHT-HD-600 [2,3,4,5].…”

Section: Introductionmentioning

confidence: 99%

Near-field angular distributions of high velocity ions for low-power hall thrusters

Sullivan

Yost

Johnson

2009

2009 IEEE Aerospace Conference

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Abstract-Experimental angular distributions of highenergy primary ions in the near-field region of a small Hall thruster between 50-200 mm downstream of the thruster exit plane at a range of centerline angles have been determined using a highly-collimated, energy-selective diagnostic probe. The measurements reveal a wide angular distribution of ions exiting the thruster channel and the formation of a strong, axially-directed jet of ions along the thruster centerline. Comparisons are made to other experimental determinations as applicable.

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Evolution of the Ion Velocity Distribtuion in the Near Field of the BHT-200-X3 Hall Thruster

Cited by 22 publications

References 7 publications

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Experimental and Numerical Examination of a Hall Thruster Plume (Preprint)

Comparison of Numerical and Experimental Near-Field Ion Velocity Distributions of the BHT-200-X3 Hall Thruster

Near-field angular distributions of high velocity ions for low-power hall thrusters

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