Zobrazeno 1 - 10
of 25
pro vyhledávání: '"Kevin D. Diamant"'
Publikováno v:
52nd AIAA/SAE/ASEE Joint Propulsion Conference.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f8687b2b9bc70e8fc011a88ef9443708
https://doi.org/10.2514/6.2016-4543
https://doi.org/10.2514/6.2016-4543
Publikováno v:
Journal of Propulsion and Power. 27:777-785
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d725d6fa3ed5a46a14d2aa1428302c84
https://doi.org/10.2514/1.b34095
https://doi.org/10.2514/1.b34095
Publikováno v:
IEEE Transactions on Plasma Science. 38:1052-1057
It is shown experimentally that the cylindrical Hall thruster (CHT) produces a highly ionized plasma flow with mass utilization efficiencies greater than 100% due to generation of multicharged ions. For the CHT employing geometries with and without a
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::732ce824c57a597b8397ee6789e06c51
https://doi.org/10.1109/tps.2010.2042623
https://doi.org/10.1109/tps.2010.2042623
Publikováno v:
Journal of Propulsion and Power. 23:27-34
Thrust, specific impulse, thrust efficiency, and coupling efficiency were measured for a nominally 1 kW microwave electrothermal thruster operating on He, N 2 , and N 2 O, and for a 5 kW model operating on water. For He, N 2 , and N 2 O, thrust varie
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::039e7271cb968068c218684e3384b1b3
https://doi.org/10.2514/1.19571
https://doi.org/10.2514/1.19571
Publikováno v:
Journal of Propulsion and Power. 22:1396-1401
Thrust, thrust efficiency, and plume divergence were measured for a 9 cm diam laboratory model Hall thruster with segmented electrodes in the discharge channel. Several geometries with graphite nonemissive electrodes, and one with a tungsten emissive
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e0bf1a18265a08e0159c11b4a37e50ab
https://doi.org/10.2514/1.19417
https://doi.org/10.2514/1.19417
Publikováno v:
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
A flight-model SPT-100 Hall thruster from the Fakel Experimental and Design Bureau was characterized with respect to performance and plume properties at The Aerospace Corporation and at L-3 Electron Technologies, Inc. over vacuum facility background
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0245fb052d026eb3c1611cc668de819c
https://doi.org/10.2514/6.2014-3710
https://doi.org/10.2514/6.2014-3710
Autor:
Jason A. Young, William A. Cox, Mark W. Crofton, Edward J. Beiting, Michael J. Patterson, Kevin D. Diamant, George C. Soulas, John C. Nocerino
Publikováno v:
52nd Aerospace Sciences Meeting.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::af27c7130e538fcd66aa93af6dfc4fb6
https://doi.org/10.2514/6.2014-0140
https://doi.org/10.2514/6.2014-0140
Publikováno v:
Journal of Propulsion and Power. 14:1036-1042
An experimentally based description of the major mechanism regulating the anode fall of a high-power, pulsed, self-field magnetoplasmadynamic thruster is presented. Plasma property data recorded to within one electron Larmor radius of the anode indic
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::43001387f7337a24c23e7f432da5b372
https://doi.org/10.2514/2.5371
https://doi.org/10.2514/2.5371
Publikováno v:
48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
Performance, plume properties, and discharge stability of a 9 cm diameter laboratory model Hall thruster were measured at vacuum chamber background pressures ranging from 1e-6 to 6e-5 Torr. The thruster was operated at constant discharge powers of 30
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::292496b1d05006994e882ab73954081a
https://doi.org/10.2514/6.2012-3735
https://doi.org/10.2514/6.2012-3735
Publikováno v:
47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
The design of and preliminary performance results from a miniature cyclotron resonance thruster are presented. Thrust with xenon and argon propellant was determined by measuring the deflection of a momentum trap suspended by a thin aluminum strip. Xe
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::023ee2bd0815e357cc15aa0676079767
https://doi.org/10.2514/6.2011-5882
https://doi.org/10.2514/6.2011-5882