Author: Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
INTER-CUSP ION AND ELECTRON TRANSPORT IN A NSTAR-DERIVATIVE ION THRUSTER... NASA/TM-2001-210669... AUG. 16, 2001
Author: Inter-Cusp Ion and Electron Transport in a Nstar-Derivative Ion Thruster
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721261611
Category :
Languages : en
Pages : 32
Book Description
Diffusion of electrons and ions to anode surfaces between the magnetic cusps of a NASA Solar Electric Propulsion Technology Application Readiness ion thruster has been characterized. Ion flux measurements were made at the anode and at the screen grid electrode. The measurements indicated that the average ion current density at the anode and at the screen grid were approximately equal. Additionally, it was found that the electron flux to the anode between cusps is best described by the classical cross-field diffusion coefficient. Foster, John E. Glenn Research Center NASA/TM-2001-210669, NAS 1.15:210669, E-12535
Ion and Electron Transport in an Nstar-derivative Ion Thruster ... Nasa
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Ion and Electron Transport in an NSTAR-Derivative Ion Thruster
Author: Ion and electron transport in an NSTAR-derivative ion thruster
Author: John E. FosterPublisher:
ISBN:
Category : Electrons
Languages : en
Pages : 13
Book Description
Improving the Total Impulse Capability of the Nstar Ion Thruster with Thick-Accelerator-Grid Ion Optics
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721284504
Category :
Languages : en
Pages : 36
Book Description
The results of performance tests with thick-accelerator-grid (TAG) ion optics are presented. TAG ion optics utilize a 50 percent thicker accelerator grid to double ion optics' service life. NSTAR ion optics were also tested to provide a baseline performance for comparison. Impingement-limited total voltages for the TAG ion optics were only 0 to 15 V higher than those of the NSTAR ion optics. Electron backstreaming limits for the TAG ion optics were 3 to 9 V higher than those for the NSTAR optics due to the increased accelerator grid thickness for the TAG ion optics. Screen grid ion transparencies for the TAG ion optics were only about 2 percent lower than those for the NSTAR optics, reflecting the lower physical screen grid open area fraction of the TAG ion optics. Accelerator currents for the TAG ion optics were 19 to 43 percent greater than those for the NSTAR ion optics due, in part, to a sudden increase in accelerator current during TAG ion optics' performance tests for unknown reasons and to the lower-than-nominal accelerator aperture diameters. Beam divergence half-angles that enclosed 95 percent of the total beam current and beam divergence thrust correction factors for the TAG ion optics were within 2 degrees and 1 percent, respectively, of those for the NSTAR ion optics. Soulas, George C. Glenn Research Center; Jet Propulsion Laboratory; Marshall Space Flight Center NASA/TM-2001-211276, NAS 1.15:211276, E-13075
THERMAL CHARACTERIZATION OF A NASA 30-CM ION THRUSTER OPERATED UP TO 5 KW... NASA/TM-2001-210696... JUN. 20, 2001
Author: Internal Plasma Properties and Enhanced Performance of an 8 Cm Ion Thruster Discharge
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721192823
Category :
Languages : en
Pages : 30
Book Description
There is a need for a lightweight, low power ion thruster for space science missions. Such an ion thruster is under development at NASA Glenn Research Center. In an effort to better understand the discharge performance of this thruster. a version of this thruster with an anode containing electrically isolated electrodes at the cusps was fabricated and tested. Discharge characteristics of this ring cusp ion thruster were measured without ion beam extraction. Discharge current was measured at collection electrodes located at the cusps and at the anode body itself. Discharge performance and plasma properties were measured as a function of discharge power, which was varied between 20 and 50 W. It was found that ion production costs decreased by as much as 20 percent when the two most downstream cusp electrodes were allowed to float. Floating the electrodes did not give rise to a significant increase in discharge power even though the plasma density increased markedly. The improved performance is attributed to enhanced electron containment. Foster, John E. and Patterson, Michael J. Glenn Research Center NASA/TM-1999-209386, E-11813, NAS 1.15:209386
Plume and Discharge Plasma Measurements of an Nstar-Type Ion Thruster
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721235506
Category :
Languages : en
Pages : 38
Book Description
The success of the NASA Deep Space I spacecraft has demonstrated that ion propulsion is a viable option for deep space science missions. More aggressive missions such as Comet Nuclear Sample Return and Europa lander will require higher power, higher propellant throughput and longer thruster lifetime than the NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) engine. Presented here are thruster plume and discharge plasma measurements of an NSTAR-type thruster operated from 0.5 kW to 5 kW. From Faraday plume sweeps, beam divergence was determined. From Langmuir probe plume measurements on centerline, low energy ion production on axis due to charge-exchange and direct ionization was assessed. Additionally, plume plasma potential measurements made on axis were used to determine the upper energy limits at which ions created on centerline could be radially accelerated. Wall probes flush-mounted to the thruster discharge chamber anode were used to assess plasma conditions. Langmuir probe measurements at the wall indicated significant differences in the electron temperature in the cylindrical and conical sections of the discharge chamber. Foster, John E and Soulas, George C. and Patterson, Michael J. Glenn Research Center NASA/TM-2000-210382, E-12438, AIAA Paper 2000-3812, NAS 1.15:210382
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