Results 261 to 270 of about 2,580 (293)
Magnetic arch plasma expansion\in a cluster of two ECR plasma sources
Boyé C, Navarro-Cavallé J, Merino M.
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One-Millipound Mercury Ion Thruster
Journal of Spacecraft and Rockets, 1975A mercury ion thruster has been developed for efficient operation at the nominal 1-mlb thrust level with a specific impulse of about 3,000 sec and a total power consumption of about 120 W. At a beam voltage of 1,200 V and beam current of 72 mA, the discharge chamber operates with a propellant efficiency of 93.8% at an ion-generation energy of 276 eV ...
J. HYMAN, JR. +3 more
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2005 European Conference on Power Electronics and Applications, 2005
A high voltage drive for radiofrequency ion thrusters is proposed. The load, consisting of a heavy ion plasma, imposes severe dynamic requirements to the power converters. State space models in the discrete time are derived for the power cells of both the high voltage generators constituting the driving system. The frequency responses of the control-to-
F. Belloni +3 more
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A high voltage drive for radiofrequency ion thrusters is proposed. The load, consisting of a heavy ion plasma, imposes severe dynamic requirements to the power converters. State space models in the discrete time are derived for the power cells of both the high voltage generators constituting the driving system. The frequency responses of the control-to-
F. Belloni +3 more
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41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
Many of the missions considered under the Space Vision demand electric propulsion lifetimes that far exceed what has been demonstrated. Some missions for example, such as the recently studied Prometheus 1, require thruster operation life, including margin, in excess of a decade.
Ira Katz +4 more
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Many of the missions considered under the Space Vision demand electric propulsion lifetimes that far exceed what has been demonstrated. Some missions for example, such as the recently studied Prometheus 1, require thruster operation life, including margin, in excess of a decade.
Ira Katz +4 more
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Ion Thruster Performance Calibration
Journal of Spacecraft and Rockets, 1973The calibration of a typical 20-cm diameter ion thrustor was examined to determine performance penalties that must be assessed in projecting measured performance into a space environment. Four specific areas were investigated. These include (1) double ion content of the beam, (2) back ingestion from the vacuum facility, (3) beam spreading, and (4 ...
EUGENE V. PAWLIK +3 more
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Modularized ion thruster development
12th International Electric Propulsion Conference, 1976A family of mercury ion thruster modules has been developed which extends the basic design of the Hughes-developed 1-mlb Engineering Model Thruster to accommodate the extended thrust range from 0.5 mlb to 4 mlb. In the subject program, separate Discharge Chamber Modules (DCM's) have been optimized for operation at nominal thrust levels T = 0.5 mlb and ...
J. HYMAN, JR., C. DULGEROFF
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A doubly charged ion model for ion thrusters
12th International Electric Propulsion Conference, 1976A theoretical equilibrium model of doubly charged ion production and loss processes in electron bombardment ion thrusters is presented. The model is shown to predict double ion density levels accurately for 15and 30-cm diam thrusters operating with several different grid sets and at several different power levels.
R.R. Peters +2 more
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A Facility and Ion Thruster Backsputter Survey for Higher Power Ion Thrusters
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005One of the significant difficulties in ground testing ion thrusters is the back sputtering of material from the vacuum facility walls resulting from beam impingement. This effect becomes even more pronounced with the development of higher power thrusters. Two major effects result from the backsputtered material.
Jonathan Van Noord, George Soulas
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Ion thruster thermal characteristics and performance
9th Electric Propulsion Conference, 1972Experimental and analytical results for a typical 20-cm-diam, hollow-cathode ion thrustor are reported. The foundation of the investigation was the application of thermal model correction techniques. Pertinent thermal properties and plasma heating characteristics of the thrustor were determined through correlation and integration of temperature ...
L. WEN, J. D. CROTTY, E. V. PAWLIK
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