Magneto-electrostatically contained plasma ion thruster

Moore, R.

doi:10.2514/6.1969-260

Cited by 32 publications

(10 citation statements)

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“…The uncertainties in mg and nu0 without any correction for charge state effects will certainly be less than 5 percent. The thrust correction due to doubly charged ions can be expressed as: a -0.5868 + 0.414 (4) where neglecting triply ionized species is a reasonable assumption for most practical operating conditions. With the discharge voltage constraints imposed, the thrust correction factor for doubly charged ions will be greater than 0.96.…”

Section: A Value Of 8 Greater Than U95 Results If Component Lifetimementioning

confidence: 99%

Improved ion containment using a ring-cusp ion thruster

Sovey

1982

16th International Electric Propulsion Conference

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Section: A Value Of 8 Greater Than U95 Results If Component Lifetimementioning

confidence: 99%

Improved ion containment using a ring-cusp ion thruster

Sovey

1982

16th International Electric Propulsion Conference

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“…5c and d were also tested and yielded thruster performance essentially equivalent to that of the divergent configuration. Confinement similar to that in the cusped geometry also has been demonstrated recently by Moore et al 9 in a configuration labeled magnetoelectrostatic thruster. The radial configuration displays some …”

Section: Magnetic Field Configurationmentioning

confidence: 61%

Study and optimization of 15-cm Kaufman thruster discharges

Knauer

Poeschel

Ward

1970

Journal of Spacecraft and Rockets

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Parametric and diagnostic studies of the Kaufman thruster discharge have shown that the transmission of the ion extraction optics and the magnetic field shape are the parameters that most significantly affect thruster performance. A high transmission ion optical system produces unexpected beneficial changes in the discharge plasma; over-all plasma density and electron temperature are lowered and the plasma potential distribution inhibits much of the ion loss to discharge chamber electrodes. A magnetic field configuration that distributes energetic electrons across the entire extraction screen produces a uniform plasma density distribution and thereby significantly improves thruster performance. Several different magnetic configurations have been found to provide such uniformity. In all cases the discharge losses are similar, typically 190 ev/ion at 85% propellant utilization in mercury discharges with hollow cathodes and with ion optics of about 70% transmission.

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“…This problem was examined from a number of different viewpoints using Eqs. (14)(15)(16)(17) and similar approaches, but no minimum thickness of the potential gradient region was evident from these equations. But these equations all implicitly assumed continuum processes, and hence did not include the effect of finite orbit size.…”

Section: Kt E Dn E -En E D V= 16jbdxmentioning

confidence: 74%

Plasma Processes in Inert-Gas Thrusters

Kaufman

Robinson

1981

Journal of Spacecraft and Rockets

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A model has been developed to describe electron diffusion across a magnetic field that is driven by both density and potential gradients, with Bohm diffusion used to predict the diffusion rate. This model has applications to conduction across magnetic fields inside a discharge chamber, as well as through a magnetic baffle region used to isolate a hollow cathode from the main chamber. Doubly charged ions constitute a significant lifetime limiter for inert-gas ion thrusters. From an existing model for double ion production, correlations have been developed that may be used without experimental data to predict double ion densities for the design of new, and especially larger ion thrusters.

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Magneto-electrostatically contained plasma ion thruster

Cited by 32 publications

References 0 publications

Improved ion containment using a ring-cusp ion thruster

Improved ion containment using a ring-cusp ion thruster

Study and optimization of 15-cm Kaufman thruster discharges

Plasma Processes in Inert-Gas Thrusters

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