Effect of Background Pressure on the Plasma Oscillation Characteristics of the HiVHAc Hall Thruster

Huang, Wensheng; Kamhawi, Hani; Lobbia, Robert B.; Brown, Daniel L.

doi:10.21236/ada611716

Cited by 12 publications

(30 citation statements)

References 16 publications

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“…A detailed analysis of the far-field probe data was performed by Huang. et al 16 , and the plume study revealed that increasing the facility background pressure resulted in changes to how the HiVHAc EDU thruster was operating. The study found that increased background pressure resulted in the average charge state rising rapidly and then leveling off with rising background pressure.…”

Section: Discussionmentioning

confidence: 99%

“…A study by Huang et al 16 used Faraday, E×B, and retarding potential analyzer probes to gain insights to help us understand how increasing the facility background pressure affects thruster operation and performance. The various probe data is used to estimate thruster discharge efficiency by use of a phenomenological efficiency model.…”

Section: Discussionmentioning

confidence: 99%

“…Results from the Faraday, RPA, E×B, and Langmuir probes were reported by Huang et al 16 In addition to the above diagnostics, an Air Force Research Laboratory (AFRL) high speed Langmuir probe (HSLP) rake was implemented in this test. 17 Analysis of the HSLP data is reported in a companion paper by Huang et al; 18  Fast camera imaging of the HiVHAc thruster discharge was performed using a FAST camera.…”

Section: F Diagnosticsmentioning

confidence: 97%

“…This is similar to what was observed in Figs. [16][17][18]. Figure 20 presents the V-I profiles for 5 mg/s after allowing the thruster to reach steady state thermal conditions, referred to as hot.…”

Section: B3 Voltage-current Characterizationmentioning

confidence: 99%

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Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Kamhawi¹,

Huang²,

Haag³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The National Aeronautics and Space Administration (NASA) Science Mission Directorate In-Space Propulsion Technology office is sponsoring NASA Glenn ResearchCenter to develop a 4 kW-class Hall thruster propulsion system for implementation in NASA science missions. A study was conducted to assess the impact of varying the facility background pressure on the High Voltage Hall Accelerator (HiVHAc) thruster performance and voltage-current characteristics. This present study evaluated the HiVHAc thruster performance in the lowest attainable background pressure condition at NASA GRC Vacuum Facility 5 to best simulate space-like conditions. Additional tests were performed at selected thruster operating conditions to investigate and elucidate the underlying physics that change during thruster operation at elevated facility background pressure. Tests were performed at background pressure conditions that are three and ten times higher than the lowest realized background pressure. Results indicated that the thruster discharge specific impulse and efficiency increased with elevated facility background pressure. The voltage-current profiles indicated a narrower stable operating region with increased background pressure. Experimental observations of the thruster operation indicated that increasing the facility background pressure shifted the ionization and acceleration zones upstream towards the thruster's anode. Future tests of the HiVHAc thruster are planned at background pressure conditions that are expected to be two to three times lower than what was achieved during this test campaign. These tests will not only assess the impact of reduced facility background pressure on thruster performance, voltage-current characteristics, and plume properties; but will also attempt to quantify the magnitude of the ionization and acceleration zones upstream shifting as a function of increased background pressure.

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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: F Diagnosticsmentioning

confidence: 97%

Section: B3 Voltage-current Characterizationmentioning

confidence: 99%

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Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Kamhawi¹,

Huang²,

Haag³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…16 These diagnostics include thrust stand, Faraday probe, ExB probe, and retarding potential analyzer. 17 The test results indicated a rise in thrust and discharge current with background pressure. The I-V characteristics also varied with background pressure.…”

Section: High Voltage Hall Acceleratormentioning

confidence: 97%

Status of propulsion technology development under the NASA In-Space Propulsion Technology program

Anderson

Kamhawi²,

Patterson³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Since 2001, the In-Space Propulsion Technology (ISPT) program has been developing and delivering in-space propulsion technologies for NASA's Science Mission Directorate (SMD). These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, Flagship and sample return missions currently under consideration. The ISPT program is currently developing technology in three areas that include Propulsion System Technologies, Entry Vehicle Technologies, and Systems/Mission Analysis. ISPT's propulsion technologies include: 1) the 0.6-7 kW NASA's Evolutionary Xenon Thruster (NEXT) gridded ion propulsion system; 2) a 0.3-3.9kW Halleffect electric propulsion (HEP) system for low cost and sample return missions; 3) the Xenon Flow Control Module (XFCM); 4) ultra-lightweight propellant tank technologies (ULTT); and 5) propulsion technologies for a Mars Ascent Vehicle (MAV). The NEXT Long Duration Test (LDT) recently exceeded 50,000 hours of operation and 900 kg throughput, corresponding to 34.8 MN-s of total impulse delivered. The HEP system is composed of the High Voltage Hall Accelerator (HIVHAC) thruster, a power processing unit (PPU), and the XFCM. NEXT and the HIVHAC are throttle-able electric propulsion systems for planetary science missions. The XFCM and ULTT are two component technologies which being developed with nearer-term flight infusion in mind. Several of the ISPT technologies are related to sample return missions needs: MAV propulsion and electric propulsion. And finally, one focus of the Systems/Mission Analysis area is developing tools that aid the application or operation of these technologies on wide variety of mission concepts. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness.

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Ion plume investigation of a Hall effect thruster operating with Xe/N₂ and Xe/air mixtures

Gurciullo¹,

Fabris²,

Cappelli³

2019

J. Phys. D: Appl. Phys.

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The ion plume of a 72 mm diameter Hall Effect Thruster operated on mixtures of xenon/nitrogen and xenon/air is investigated by means of a Wien filter (or E × B probe). The dependence of the velocities of the plume ions (Xe + , Xe 2+ , Xe 3+ , O + 2 , O + , N + 2 and N +) on the operating parameters of the thruster (anode voltage, anode power, mass flow rate and magnetic field) is explored. The most probable ion acceleration voltages, the ion current and density fractions of the multi-propellant, multi-species ion beam, are computed from the Wien filter spectra through a dedicated post-processing analysis. The knowledge of these properties is fundamental for understanding the contribution of each ion species to the propulsive performance metrics of the thruster when operated on these molecular gas mixtures.

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Effect of Background Pressure on the Plasma Oscillation Characteristics of the HiVHAc Hall Thruster

Cited by 12 publications

References 16 publications

Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Status of propulsion technology development under the NASA In-Space Propulsion Technology program

Ion plume investigation of a Hall effect thruster operating with Xe/N₂ and Xe/air mixtures

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Effect of Background Pressure on the Plasma Oscillation Characteristics of the HiVHAc Hall Thruster

Cited by 12 publications

References 16 publications

Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Investigation of the Effects of Facility Background Pressure on the Performance and Operation of the High Voltage Hall Accelerator

Status of propulsion technology development under the NASA In-Space Propulsion Technology program

Ion plume investigation of a Hall effect thruster operating with Xe/N2 and Xe/air mixtures

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Ion plume investigation of a Hall effect thruster operating with Xe/N₂ and Xe/air mixtures