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Performance Of A Multi Kilowatt Non Circular Discharge Hall Thruster
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Book Synopsis Performance of a Multi-kilowatt Non-circular Discharge Hall Thruster by : B. Pote
Download or read book Performance of a Multi-kilowatt Non-circular Discharge Hall Thruster written by B. Pote and published by . This book was released on 2000 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Hall Thruster Performance Model Incorporating the Effects of a Multiply-Charged Plasma by : Richard R. Hofer
Download or read book A Hall Thruster Performance Model Incorporating the Effects of a Multiply-Charged Plasma written by Richard R. Hofer and published by . This book was released on 2002 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book חומת מגן written by and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Development and Characterization of a Two-stage Hybrid Hall/ion Thruster by : Peter Young Peterson
Download or read book The Development and Characterization of a Two-stage Hybrid Hall/ion Thruster written by Peter Young Peterson and published by . This book was released on 2004 with total page 600 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781726692649 Total Pages :34 pages Book Rating :4.6/5 (926 download)
Book Synopsis A Hall Thruster Performance Model Incorporating the Effects of a Multiply-Charged Plasma by : National Aeronautics and Space Adm Nasa
Download or read book A Hall Thruster Performance Model Incorporating the Effects of a Multiply-Charged Plasma written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-03 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Hall thruster performance model that predicts anode specific impulse, anode efficiency, and thrust is discussed. The model is derived as a function of a voltage loss parameter, an electron loss parameter, and the charge state of the plasma. Experimental data from SPT and TAL type thrusters up to discharge powers of 21.6 kW are used to determine the best fit for model parameters. General values for the model parameters are found, applicable to high power thrusters and irrespective of thruster type. Performance of a 50 kW thruster is calculated for an anode specific impulse of 2500 seconds or a discharge current of 100 A. Hofer, Richard R. and Jankovsky, Robert S. Glenn Research Center NASA/TM-2002-211214, E-13066, NAS 1.15:211214, AIAA Paper 2001-3322
Book Synopsis The Use of Electrostatic Probes to Characterize the Discharge Plasma Structure and Identify Discharge Cathode Erosion Mechanisms in Ring-cusp Ion Thrusters by : Daniel A. Herman
Download or read book The Use of Electrostatic Probes to Characterize the Discharge Plasma Structure and Identify Discharge Cathode Erosion Mechanisms in Ring-cusp Ion Thrusters written by Daniel A. Herman and published by . This book was released on 2005 with total page 910 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721181049 Total Pages :32 pages Book Rating :4.1/5 (81 download)
Book Synopsis Preliminary Evaluation of a 10 KW Hall Thruster by : National Aeronautics and Space Administration (NASA)
Download or read book Preliminary Evaluation of a 10 KW Hall Thruster written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and a range of discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW. Over this range of discharge powers, thrust varied from 278 mN to 524 mN, specific impulse ranged from 1644 to 2392 seconds, and efficiency peaked at approximately 59%. A continuous 40 hour test was also undertaken in an attempt to gain insight with regard to long term operation of the engine. For this portion of the testing the thruster was operated at a discharge voltage of 500 V and a discharge current of 20 A. Steady-state temperatures were achieved after 3-5 hrs and very little variation in performance was detected. Jankovsky, Robert S. and McLean, Chris and McVey, John Glenn Research Center NASA/TM-1999-209075, NAS 1.15:209075, AIAA Paper 99-0456, E-11636
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721783267 Total Pages :30 pages Book Rating :4.7/5 (832 download)
Book Synopsis Multi-Kilowatt Power Module for High-Power Hall Thrusters by : National Aeronautics and Space Administration (NASA)
Download or read book Multi-Kilowatt Power Module for High-Power Hall Thrusters written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-24 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Future NASA missions will require high-performance electric propulsion systems. Hall thrusters are being developed at NASA Glenn for high-power, high-specific impulse operation. These thrusters operate at power levels up to 50 kW of power and discharge voltages in excess of 600 V. A parallel effort is being conducted to develop power electronics for these thrusters that push the technology beyond the 5kW state-of-the-art power level. A 10 kW power module was designed to produce an output of 500 V and 20 A from a nominal 100 V input. Resistive load tests revealed efficiencies in excess of 96 percent. Load current share and phase synchronization circuits were designed and tested that will allow connecting multiple modules in parallel to process higher power. Pinero, Luis R. and Bowers, Glen E. Glenn Research Center NASA/TM-2005-213348, AIAA Paper 2004-3973, E-14816
Book Synopsis Performance Test Results of the Nasa-457m V2 Hall Thruster by : George C. Soulas
Download or read book Performance Test Results of the Nasa-457m V2 Hall Thruster written by George C. Soulas and published by BiblioGov. This book was released on 2013-07 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Performance testing of a second generation, 50 kW-class Hall thruster labeled NASA-457M v2 was conducted at the NASA Glenn Research Center. This NASA-designed thruster is an excellent candidate for a solar electric propulsion system that supports human exploration missions. Thruster discharge power was varied from 5 to 50 kW over discharge voltage and current ranges of 200 to 500 V and 15 to 100 A, respectively. Anode efficiencies varied from 0.56 to 0.71. The peak efficiency was similar to that of other state-of-the-art high power Hall thrusters, but outperformed these thrusters at lower discharge voltages. The 0.05 to 0.18 higher anode efficiencies of this thruster compared to its predecessor were primarily due to which of two stable discharge modes the thruster was operated. One stable mode was at low magnetic field strengths, which produced high anode efficiencies, and the other at high magnetic fields where its predecessor was operated. Cathode keeper voltages were always within 2.1 to 6.2 V and cathode voltages were within 13 V of tank ground during high anode efficiency operation. However, during operation at high magnetic fields, cathode-to-ground voltage magnitudes increased dramatically, exceeding 30 V, due to the high axial magnetic field strengths in the immediate vicinity of the centrally-mounted cathode. The peak thrust was 2.3 N and this occurred at a total thruster input power of 50.0 kW at a 500 V discharge voltage. The thruster demonstrated a thrust-to-power range of 76.4 mN/kW at low power to 46.1 mN/kW at full power, and a specific impulse range of 1420 to 2740 s. For a discharge voltage of 300 V, where specific impulses would be about 2000 s, thrust efficiencies varied from 0.57 to 0.63.
Book Synopsis Preliminary Evaluation of a 10 KW Hall Thruster by : Robert S. Jankovsky
Download or read book Preliminary Evaluation of a 10 KW Hall Thruster written by Robert S. Jankovsky and published by . This book was released on 1999 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit by :
Download or read book 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit written by and published by . This book was released on 2001 with total page 522 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721602209 Total Pages :30 pages Book Rating :4.6/5 (22 download)
Book Synopsis 50 KW Class Krypton Hall Thruster Performance by : National Aeronautics and Space Administration (NASA)
Download or read book 50 KW Class Krypton Hall Thruster Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance of a 50-kilowatt-class Hall thruster designed for operation on xenon propellant was measured using kryton propellant. The thruster was operated at discharge power levels ranging from 6.4 to 72.5 kilowatts. The device produced thrust ranging from 0.3 to 2.5 newtons. The thruster was operated at discharge voltages between 250 and 1000 volts. At the highest anode mass flow rate and discharge voltage and assuming a 100 percent singly charged condition, the discharge specific impulse approached the theoretical value. Discharge specific impulse of 4500 seconds was demonstrated at a discharge voltage of 1000 volts. The peak discharge efficiency was 64 percent at 650 volts. Jacobson, David T. and Manzella, David H. Glenn Research Center NASA/TM-2003-212700, AIAA Paper 2003-4550, E-14203
Book Synopsis Performance Evaluation of a 50kW Hall Thruster by : David T. Jacobson
Download or read book Performance Evaluation of a 50kW Hall Thruster written by David T. Jacobson and published by . This book was released on 1999 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721530649 Total Pages :30 pages Book Rating :4.5/5 (36 download)
Book Synopsis Laboratory Model 50 KW Hall Thruster by : National Aeronautics and Space Administration (NASA)
Download or read book Laboratory Model 50 KW Hall Thruster written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-20 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.46 meter diameter Hall thruster was fabricated and performance tested at powers up to 72 kilowatts. Thrusts up to 2.9 Newtons were measured. Discharge specific impulses ranged from 1750 to 3250 seconds with discharge efficiencies between 46 and 65 percent. Overall specific impulses ranged from 1550 to 3050 seconds with overall efficiencies between 40 and 57 percent. Performance data indicated significant fraction of multiple-charged ions during operation at elevated power levels. Cathode mass flow rate was shown to be a significant parameter with regard to thruster efficiency. Manzella, David and Jankovsky, Robert and Hofer, Richard Glenn Research Center NASA/TM-2002-211887, NAS 1.15:211887, E-13569, AIAA Paper 2002-3676
Book Synopsis Laboratory Model 50 KW Hall Thruster by : David H. Manzella
Download or read book Laboratory Model 50 KW Hall Thruster written by David H. Manzella and published by . This book was released on 2002 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-Power Magnetically Shielded Hall Thrusters by : Ryan Conversano
Download or read book Low-Power Magnetically Shielded Hall Thrusters written by Ryan Conversano and published by . This book was released on 2015 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt: This dissertation presents an investigation of the applicability of magnetic shielding to low-power Hall thrusters as a means to significantly improve operational lifetime. The key life-limiting factors of conventional Hall thrusters, including ion-bombardment sputter erosion of the discharge channel and high-energy electron power deposition to the channel walls, have been investigated extensively for a wide range of thruster scales. As thruster power is reduced to the "miniature" (i.e. sub-500 W) power regime, the increased surface-to-volume ratio of the discharge channel and decreased thruster component sizes promotes increased plasma-wall interactions and susceptibility to overheating, thereby reducing thruster operational lifetime and performance. Although methods for compensating for these issues have been investigated, unshielded miniature Hall thrusters are generally limited to sub-45% anode efficiencies and maximum lifetimes on the order of 1,000 h. A magnetically shielded magnetic field topology aims to maintain a low electron temperature along the channel surfaces and a plasma potential near that of the discharge voltage along the entire surface of the discharge channel along its axial length. These features result in a reduction of the kinetic energy of ions that impact the channel surfaces to near to or below the sputtering threshold, thus preventing significant ion-bombardment erosion of the discharge channel. Improved confinement of high-energy electrons is another byproduct of the field structure, aiding in the reduction of electron power deposition to the channel. Magnetic shielding has been shown to dramatically reduce plasma-wall interactions on 4 - 6 kW Hall thrusters, resulting in significant increases in projected operational lifetimes with minimal effects to thruster performance. In an effort to explore the scalability of magnetic shielding to low-power devices, two magnetically shielded miniature Hall thrusters were designed, fabricated and tested. The performance of the first thruster, called the MaSMi 40, was characterized at an operating condition of 275 V and 325 W. A peak thrust of approximately 13 mN with a specific impulse of approximately 1,100 s at an anode efficiency of approximately 22% were measured at the nominal operating point. Observations of the near exit plasma discharge during operation, and the discharge channel after operation, suggested that the outer channel wall of the thruster was well shielded from ion bombardment while the inner channel wall appeared to be weakly shielded. Further analysis concluded that the MaSMi-40 generated a partially-magnetically shielded field topology. However, the shortcomings of the MaSMi-40's magnetic circuit design were investigated in detail and are now well understood. The second design iteration in the development of a low-power magnetically shielded Hall thruster was the MaSMi-60. Magnetic field measurements confirmed that a symmetric and fully shielded magnetic field topology was generated by this device across a wide range of possible operating conditions. At operating powers of 160 W to nearly 750 W, the key performance metrics of the MaSMi-60 included a measured thrust ranging from approximately 8 mN to over 33 mN with anode specific impulses of up to approximately 1370 s at anode efficiencies of over 28%. Downstream plume measurements identified the primary factors contributing to the low anode efficiency. Visual observations of the discharge plasma and channel walls during and after thruster operation offered strong evidence of magnetic shielding. Erosion rates of the channel were approximated using carbon backsputter measurements; the results suggested a 10x - 100x decrease in wall erosion compared to unshielded Hall thrusters, corresponding to an equal increase in discharge channel lifetime compared to conventional miniature unshielded Hall thrusters. The physics and behaviors of the MaSMi-60's plasma discharge upstream of and in the near-field of the thruster exit plane were investigated using Hall2De, the 2-D axisymmetric code developed at the Jet Propulsion Laboratory for the simulation of the partially ionized plasma in Hall thrusters. Simulations of the MaSMi-60 suggested that the thruster achieved the plasma properties required for effective magnetic shielding, including low electron temperatures and a near-constant plasma potential along the channel walls. This was the final piece of evidence suggesting that magnetic shielding was attained at the miniature scale. The experimentally measured performance of the MaSMi-60 was captured by the Hall2De model, offering physical explanations for the low measured anode efficiency and leading to suggestions for improving the performance in future design iterations.
Book Synopsis Evaluation of Low Power Hall Thruster Propulsion by : David Manzella
Download or read book Evaluation of Low Power Hall Thruster Propulsion written by David Manzella and published by . This book was released on 1996 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: