Results 211 to 220 of about 63,437 (256)
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Rayleigh Instability in Hall Thrusters
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002Gradient-driven Rayleigh-type instabilities in Hall plasma thrusters are analyzed using linearized two-fluid hydrodynamic equations. Necessary instability conditions and a general criterion for stability of azimuthally propagating perturbations are derived.
Andrei A. Litvak, Nathaniel J. Fisch
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Performance enhancement of an argon-based propellant in a Hall thruster
Vacuum, 2019Finding alternatives to xenon as a propellant is essential for reducing the launching cost of all-electric satellites and for achieving low-cost electric propulsion, especially using Hall thrusters. Argon is a candidate as such a low-cost propellant, but
J. Yamasaki, S. Yokota, K. Shimamura
semanticscholar +1 more source
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
openaire +2 more sources
Propellant utilization in Hall thrusters
32nd Joint Propulsion Conference and Exhibit, 1996Fuel optimal trajectories for electrically propelled spacecraft require a varying thrust acceleration. To achieve this requirement the electric thruster has to be operated with a variable thrust to power ratio at the maximum available input power. In order to implement this operating mode with a Hall thruster it is necessary to modify both the mass ...
Y. Raitses, J. Ashkenazy, M. Guelman
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Optimization of discharge triggering in micro-cathode vacuum arc thruster for CubeSats
Plasma Sources Science & Technology, 2018The ignition and optimization of the pulsed micro-cathode triggerless vacuum arc thruster model are analyzed. To this end a simplified model of the thruster consisting of two rectangular electrodes on an alumina ceramic plate with a variable inter ...
D. Zolotukhin, M. Keidar
semanticscholar +1 more source
Channel length and thruster performance of Hall thrusters
32nd Joint Propulsion Conference and Exhibit, 1996Kimiya Komurasaki +2 more
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Electrohydrodynamic thruster for near-space applications
Acta Astronautica, 2021Viktor Evgenyevich Malanichev +1 more
exaly
Magnetoplasmadynamic Thrusters
2010The paper starts with a brief account of the origins of MPD concept followed by an explanation of Lorentz force. The nature of an ideal Self-field MPD thruster is then discussed in terms of basic thrust law, cubic dependance and ideal scaling trends. The situation as to real Self-field MPD thrusters follows including their electrical characteristics ...
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Design and demonstration of a micro air-fed magnetoplasmadynamic thruster for small satellites
Acta Astronautica, 2021Zihao Wang, Youngho Eun, Xiaofeng Wu
exaly