The research objective for this project was to investigate and resolve technical issues associated with electric propulsion thrusters, specifically performance and spacecraft integration issues. The thrusters examined include magneto-plasma-dynamic (MPD) thrusters, arcjets, Hall thrusters, and pulsed plasma thrusters. The specific tasks were to identify methods to significantly increase MPD efficiencies, characterize and test laboratory arcjets in support of flight experiments, demonstrate significant gains in impulse to wet mass ratios for Hall thrusters, and develop and test advanced PPT design concepts. Results are summarized and more detail is provided in 34 referenced papers and journal articles.
Plasma Thruster Development
2003
13 pages
Report
Keine Angabe
Englisch
Plasma Physics , Electric & Ion Propulsion , Rocket Engines & Motors , Optimization , Performance(Engineering) , Arc jet engines , Thrusters , Ion engines , Electric propulsion , Plasma diagnostics , Plasma engines , Flight testing , Laboratory tests , Spacecraft , Efficiency , Emission spectra , Electrical conductivity , Electron microscopy , Particulates , Perturbations , Emission spectroscopy , Exhaust plumes , Exhaust nozzles , Solid rocket propellants , Electromagnetic environments , Rocket exhaust , Plasma instabilities , Magneto plasma dynamic thrusters , Hall thrusters , Pulsed plasma thrusters , Plume diagnostics , Mpd thrusters , Esex(Electric space experiment) , Ppt designs , Spacecraft integration , Plasma microturbulence , Arcjet ignition model , Propellant breakdown , Current modulation velocimetry , Pulse electron beam fluorescence , Nozzle geometry , Msti(Miniaturized space technology integration) , Electric orbit transfer vehicles , Propellant inefficiencies , Particulate emission
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