Operation of the J-series thruster using inert gas

Rawlin, Vincent K.

doi:10.2514/6.1982-1929

Cited by 19 publications

(6 citation statements)

References 13 publications

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“…The equation used to calculate ingestion, for an inert gas thruster was A = 2.0 _PÂ _ MW (1) All symbols are defined in the symbol list. This calculation assumes molecular flow through the downstream grid orifices into a discharge chamber with zero pressure.…”

Section: Apparatus and Proceduresmentioning

confidence: 99%

Improved ion containment using a ring-cusp ion thruster

Sovey

1984

Journal of Spacecraft and Rockets

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Section: Apparatus and Proceduresmentioning

confidence: 99%

Improved ion containment using a ring-cusp ion thruster

Sovey

1984

Journal of Spacecraft and Rockets

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“…Recent development work on ion engine technology (Sovey 1982a, Rawlin 1982, and Sovey 1982b has focused on the use of noble gas propellants to circumvent the toxicity and spacecraft contamination issues presented by the use of mercury propellant. Our model, based partially upon a model created by Brophy et al (1989), is designed to reflect both theoretical performance predictions and laboratory data collected from ion engine tests.…”

Section: Electron Bombardment Ion Thrustermentioning

confidence: 99%

Electric thruster models for multimegawatt nuclear electric propulsion mission design

Leifer

Blandino

Sercel

1991

AIP Conference Proceedings

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Three types of electric thrusters currently under development at JPL have potential to support future missions which utilize multimegawatt nuclear elecUic propulsion. These electric thrusters are the electron bombardment ion thruster, the magnetoplasmadynamic (MID) thruster, and the electron-cyclotron-resonance (ECR) thruster. The electron bombardment ion thruster is a relatively mature technology which has been developed for operation at kilowatt power levels but will require new development for application in the multimegawatt regime. The MPD engine represents a technology which may be very well suited to steady-state multimegawatt applications but which has been limited to sub-scale (100's ofkW) and pulsed (MW) testing thus far. The ECR plasma engine represents a class of very promising new concepts which are still in the basic research phase of development, but which may possess important fundamental advantages over other electric thruster technologies. In this paper, models of these thrusters are described and used to make projections of thruster specific mass, efficiency, and power handling capacity for operation in the multimegawatt regime.

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“…(1 4 ) 3 The minimum required vaporization chamber volume was given by the maximum selected test duration (1 hour) at rn = 5 mg/sec (typical fullerene powder density is 1.5 g/cm 3 ). Based on that we selected the vaporization chamber volume to be about 100 cm 3 . Approximately 15% of its volume will be occupied at maximum charge by 3 the fullerene powder.…”

Section: Altsmentioning

confidence: 99%

A High Thrust Density, C60 Cluster, Ion Thruster.

Hruby¹

1996

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Operation of the J-series thruster using inert gas

Cited by 19 publications

References 13 publications

Improved ion containment using a ring-cusp ion thruster

Improved ion containment using a ring-cusp ion thruster

Electric thruster models for multimegawatt nuclear electric propulsion mission design

A High Thrust Density, C60 Cluster, Ion Thruster.

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