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  • 1
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    The technological and commercial expansion of electric propulsion (2019)
    Elsevier
    Details
    Publication Date: 2019-06-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Electric propulsion: An evolutionary technology (1993)
    Elsevier
    Details
    Publication Date: 1993-09-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Electric propulsion - An evolutionary technology (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 29; 9; p. 651-665.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Electric propulsion: An evolutionary technology (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The NASA Lewis Research Center (LeRC) conducts and directs an electric propulsion research and technology program aimed at providing high-performance electric propulsion system options for a broad range of near and far-term missions. This evolutionary program emphasizes the development of propulsion systems for three classes of missions: (1) near term auxiliary propulsion applications such as North-South Stationkeeping for next generation communications satellites and orbit maintainence for orbiting platforms such as Space Station Freedom; (2) advanced solar electric propulsion and SP-100-class nuclear electric propulsion for Earth-space orbit transfer and robotic planetary missions; and (3) very high power systems to support major space missions including the Space Exploration Initiative. To cover widely disparate mission requirements, the LeRC program includes research on electrothermal, electrostatic, and electromagnetic systems. This paper provides an overview of the LeRC program with a focus on recent progress.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 29; 9; p. 651-665
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    MPD thruster technology (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The topics are presented in viewgraph form and include the following: in house program elements; performance measurements; applied-field magnetoplasmadynamic (MPD) thruster performance scaling; MPD thruster technology; thermal efficiency scaling; anode fall voltage measurements; anode power deposition studies; MPD thruster plasma modeling; MPD thruster lifetime studies; and MPD thruster performance studies.
    Keywords: PLASMA PHYSICS
    Type: NASA, Lewis Research Center, Second Magnetoplasmadynamic Thruster Workshop; p 71-90
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    MPD thruster technology (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Inhouse magnetoplasmadynamic (MPD) thruster technology is discussed. The study focussed on steady state thrusters at powers of less than 1 MW. Performance measurement and diagnostics technologies were developed for high power thrusters. Also developed was a MPD computer code. The stated goals of the program are to establish: performance and life limitation; influence of applied fields; propellant effects; and scaling laws. The presentation is mostly through graphs and charts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Magnetoplasmadynamic Thruster Workshop; 13 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Pulsed Plasma Thrusters for Small Spacecraft Attitude Control (1996)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Pulsed plasma thrusters (PPT's) are a new option for attitude control of a small spacecraft and may result in reduced attitude control system (ACS) mass and cost. The primary purpose of an ACS is to orient the spacecraft configuration to the desired accuracy in inertial space. The ACS functions for which the PPT system will be analyzed include disturbance torque compensation and slewing maneuvers such as sun acquisition for which the small impulse bit and high specific impulse of the PPT offers unique advantages. The NASA Lewis Reserach Center (LeRC) currently has a contracted flight PPT system development program in place with Olin Aerospace and a delivery date of October 1997. The PPT system in this study are based upon the work being done under the NASA LeRC program. Analysis of the use of PPT's for ACS showed that the replacement of the standard momentum wheels and torque rods systems with a PTT system to perform the altitude control maneuvers on a small low Earth orbiting spacecraft reduced the ACS mass by 50 to 75 percent with no increase in required power level over comparable wheel-based systems.
    Keywords: Spacecraft Propulsion and Power
    Type: Flight Mechanics/Estimation Theory Symposium 1996; 295-305; NASA-CP-3333
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Pulsed plasma thrusters for small spacecraft attitude control (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pulsed Plasma Thrusters (PPTS) are a new option for attitude control of a small spacecraft and may result in reduced attitude control system (ACS) mass and cost. The primary purpose of an ACS is to orient the spacecraft to the desired accuracy in inertial space. The ACS functions for which the PPT system will be analyzed include disturbance torque compensation, and slewing maneuvers such as sun acquisition for which the small impulse bit and high specific impulse of the PPT offers unique advantages. The NASA Lewis Research Center (LERC) currently has a contracted flight PPT system development program in place with Olin Aerospace with a delivery date of October 1997. The PPT systems in this study are based upon the work being done under the NASA LERC program. Analysis of the use of PPTs for ACS showed that the replacement of the standard momentum wheels and torque rods with a PPT system to perform the attitude control maneuvers on a small low Earth orbiting spacecraft reduced the ACS mass by 50 to 75% with no increase in required power level over comparable wheel-based systems, though rapid slewing power requirements may present an issue.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-CR-198517 , NAS 1.26:198517 , E-10395
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Photovoltaic Plasma Interaction Test 2 (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The International Space Station (ISS) program is developing a plasma contactor to mitigate the harmful effects of charge collection on the station's large photovoltaic arrays. The purpose of the present test was to examine the effects of charge collection on the solar array electrical circuit and to verify the effectiveness of the plasma contactor. The results showed that the plasma contactor was able to eliminate structure arcing for any array output voltage. However, the current requirements of the plasma contactor were higher than those for prior testing and predicted by analysis. Three possible causes for this excess current demand are discussed. The most likely appeared to be a high local pressure on or very near the surface of the array as a result of vacuum tank conditions. Therefore, in actual space conditions, the plasma contactor should work as predicted.
    Keywords: Geophysics
    Type: NASA-TP-3635 , E-10332 , NAS 1.60:3636
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Applied-field MPD thruster geometry effects (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Eight MPD thruster configurations were used to study the effects of applied-field strength, propellant, and facility pressure on thruster performance. Vacuum facility background pressures higher than about 0.12 Pa were found to significantly influence thruster performance and electrode power deposition. Thrust efficiency and specific impulse increased monotonically with increasing applied field strength. Both cathode and anode radii fundamentally influenced the efficiency-specific impulse relationship, while their lengths influenced only the magnitude of the applied magnetic field required to reach a given performance level. At a given specific impulse, large electrode radii result in lower efficiencies for the operating conditions studied. For all test conditions, anode power deposition was the largest efficiency loss, and represented between 50 percent and 80 percent of the input power. The fraction of the input power deposited into the anode decreased with increasing applied field and anode radius. The highest performance measured, 20 percent efficiency at 3700 seconds specific impulse, was obtained using hydrogen propellant.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2342
    Format: text
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    NASA TECHNICAL REPORTS
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