High Voltage TAL Erosion Characterization

Jacobson, David T.

doi:10.2514/6.2002-4257

Cited by 14 publications

(10 citation statements)

References 2 publications

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“…VF12 has been used in the past for Hall thruster performance and erosion characterizations. 45,46 When considering possible facility effects on performance, measurements from a 10-kW Hall thruster are a convenient reference because this thruster was tested in VF12 and in the main volume of Vacuum Facility 5 (VF5) at NASA GRC. 45,47 When operating the 10-kW thruster at xenon flow rates of 22 mg/s, the pressure in VF12 was 1 × 10 −5 torr, whereas in VF5, the pressure was 2 × 10 −6 torr.…”

Section: Vacuum Facilitymentioning

confidence: 99%

High-Specific Impulse Hall Thrusters, Part 1: Influence of Current Density and Magnetic Field

Hofer¹,

Jankovsky

Gallimore

2006

Journal of Propulsion and Power

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A laboratory-model Hall thruster with a magnetic circuit designed for high-specific impulse (2000-3000 s) was evaluated to determine how current density and magnetic field affect thruster operation. Results have shown for the first time that a minimum current density and optimum magnetic field shape exist at which efficiency will monotonically increase with specific impulse. At the nominal mass flow rate of 10 mg/s and between discharge voltages of 300 and 1000 V, total specific impulse and total efficiency ranged from 1600 to 3400 s and 51 to 61%, respectively. Comparison with a similar thruster showed how efficiency can be optimized for specific impulse by varying the shape of the magnetic field. Plume divergence decreased from a maximum of 48 deg at 400 V to a minimum of 35 deg at 1000 V, but increased between 300 and 400 V as the likely result of a large increase in discharge current oscillations. The breathing-mode frequency continuously increased with voltage, from 14.5 kHz at 300 V to 22 kHz at 1000 V, in contrast to other Hall thrusters where a sharp decrease of the breathing-mode frequency was found to coincide with increasing electron current and decreasing efficiency. These findings suggest that efficient, high-specific impulse operation was enabled through the regulation of the electron current with the applied magnetic field. . Associate Fellow AIAA. η t = total efficiency θ = azimuthal coordinate direction ∇ z B r = axial gradient of the centerline radial magnetic field

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Section: Vacuum Facilitymentioning

confidence: 99%

High-Specific Impulse Hall Thrusters, Part 1: Influence of Current Density and Magnetic Field

Hofer¹,

Jankovsky

Gallimore

2006

Journal of Propulsion and Power

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“…This is caused by ion sputtering in which accelerated propellant ions impinge on the insulator channel wall and remove its molecules [4]. Thus, long-duration tests [5][6][7][8] as well as numerical erosion simulations [9][10][11][12] have been conducted to evaluate and improve the lifetime performance of Hall thrusters.…”

Section: Introductionmentioning

confidence: 99%

Multilayer Coating Method for Investigating Channel-Wall Erosion in a Hall Thruster

Cho

Yokota

Komurasaki

et al. 2013

Journal of Propulsion and Power

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“…Even as the magnetic poles were exposed the robustness of the thruster was demonstrated by the continued nominal operation of the thruster. Jacobson [45] has a complete description of the thruster and test results. …”

Section: High Voltage Thruster Lifementioning

confidence: 99%

Ion Engine and Hall Thruster Development at the NASA Glenn Research Center

2002

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NASA’s Glenn Research Center has been selected to lead development of NASA’s Evolutionary Xenon Thruster (NEXT) system. The central feature of the NEXT system is an electric propulsion thruster (EPT) that inherits the knowledge gained through the NSTAR thruster that successfully propelled Deep Space 1 to asteroid Braille and comet Borrelly, while significantly increasing the thruster power level and making improvements in performance parameters associated with NSTAR. The EPT concept under development has a 40 cm beam diameter, twice the effective area of the Deep-Space 1 thruster, while maintaining a relatively-small volume. It incorporates mechanical features and operating conditions to maximize the design heritage established by the flight NSTAR 30 cm engine, while incorporating new technology where warranted to extend the power and throughput capability. The NASA Hall thruster program currently supports a number of tasks related to high power thruster development for a number of customers including the Energetics Program (formerly called the Space-based Program), the Space Solar Power Program, and the In-space Propulsion Program. In program year 2002, two tasks were central to the NASA Hall thruster program: 1.) the development of a laboratory Hall thruster capable of providing high thrust at high power; 2.) investigations into operation of Hall thrusters at high specific impulse. In addition to these two primary thruster development activities, there are a number of other on-going activities supported by the NASA Hall thruster program. These additional activities are related to issues such as thruster lifetime and spacecraft integration.

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High Voltage TAL Erosion Characterization

Cited by 14 publications

References 2 publications

High-Specific Impulse Hall Thrusters, Part 1: Influence of Current Density and Magnetic Field

High-Specific Impulse Hall Thrusters, Part 1: Influence of Current Density and Magnetic Field

Multilayer Coating Method for Investigating Channel-Wall Erosion in a Hall Thruster

Ion Engine and Hall Thruster Development at the NASA Glenn Research Center

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