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  • 1
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    Diagnostics and performance of a 1/4-scale MPD thruster (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The primary purpose of this study is to evaluate the performance and scaling characteristics of a 1/4-scale magnetoplasmadynamic (MPD) thruster operating with and without applied magnetic nozzle fields. The experiment was carried out with separate pulse forming networks for the thruster and the applied field solenoidal coil. A strong correlation of impact pressure signal with thruster current was noted. Also striking was the larger impact signal when the magnetic nozzle field was applied. Measurements of N(e) and T(e) from Langmuir probes have been made. Compatible interpretation of pressure with N(e), T(e), allow local velocity to be mapped, thus enhancing understanding of the acceleration process.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2665
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Integration issues of a plasma contactor Power Electronics Unit (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A hollow cathode-based plasma contactor is baselined on International Space Station Alpha (ISSA) for spacecraft charge control. The plasma contactor system consists of a hollow cathode assembly (HCA), a power electronics unit (PEU), and an expellant management unit (EMU). The plasma contactor has recently been required to operate in a cyclic mode to conserve xenon expellant and extend system life. Originally, a DC cathode heater converter was baselined for a continuous operation mode because only a few ignitions of the hollow cathode were expected. However, for cyclic operation, a DC heater supply can potentially result in hollow cathode heater component failure due to the DC electrostatic field. This can prevent the heater from attaining the proper cathode tip temperature for reliable ignition of the hollow cathode. To mitigate this problem, an AC cathode heater supply was therefore designed, fabricated, and installed into a modified PEU. The PEU was tested using resistive loads and then integrated with an engineering model hollow cathode to demonstrate stable steady-state operation. Integration issues such as the effect of line and load impedance on the output of the AC cathode heater supply and the characterization of the temperature profile of the heater under AC excitation were investigated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-106977 , E-9739 , NAS 1.15:106977 , AIAA PAPER 95-362 , Intersociety Energy Conversion Engineering Conference; Jul 31, 1995 - Aug 04, 1995; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Plasma flow processes within magnetic nozzle configurations (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An attempt is made to separate the interactive processes occurring in electromagnetic devices and to examine the acceleration of ionized gas within magnetic fields which can guide it through an expansion process. The plasma was generated in a single turn coil 50 cm long with a radius of 5.25 cm which surrounded a quartz tube with an internal radius of 3.81 cm and a length of 100 cm. Choking was found to occur at both sonic and cusp velocities which were coincident in the present experiment.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-2711
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Plasma flow processes within magnetic nozzle configurations (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 5 Se; 1023-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The effects of magnetic nozzle configurations on plasma thrusters (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Plasma thrusters have been operated at power levels from 10kW to 0.1MW. When these devices have had magnetic fields applied to them which form a nozzle configuration for the expanding plasma, they have shown marked increases in exhaust velocity which is in direct proportion to the magnitude of the applied field. Further, recent results have shown that electrode erosion may be influenced by applied magnetic fields. This research is directed to the experimental and computational study of the effects of applied magnetic field nozzles in the acceleration of plasma flows. Plasma source devices which eliminate the plasma interaction in normal thrusters are studied as most basic. Normal thruster configurations will be studied without applied fields and with applied magnetic nozzle fields. Unique computational studies will utilize existing codes which accurately include transport processes. Unique diagnostic studies will support the experimental studies to generate new data. Both computation and diagnostics will be combined to indicate the physical mechanisms and transport properties that are operative in order to allow scaling and accurate prediction of thruster performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-184678 , NAS 1.26:184678 , AAE-AARL-P-89-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    The effects of magnetic nozzle configurations on plasma thrusters (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Plasma thrusters have been operated at power levels from 10 kw to 0.1 MW. When these devices have had magnetic fields applied to them which form a nozzle configuration for the expanding plasma, they have shown marked increases in exhaust velocity which is in direct proportion to the magnitude of the applied field. Further, recent results have shown that electrode erosion may be influenced by applied magnetic fields. This research effort is directed to the experimental and computational study of the effects of applied magnetic field nozzles in the acceleration of plasma flows. Plasma source devices which eliminate the plasma interaction in normal thrusters are studied as most basic. Normal thruster configurations were studied without applied fields and with applied magnetic nozzle fields. Unique computational studies utilize existing codes which accurately include transport processes. Unique diagnostic studies supported the experimental studies to generate new data. Both computation and diagnostics were combined to indicate the physical mechanisms and transport properties that are operative in order to allow scaling and accurate prediction of thruster performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-186465 , NAS 1.26:186465 , AARL-P-90-1
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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