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  • 1
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    Power system technologies for the manned Mars mission (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The high impulse of electric propulsion makes it an attractive option for manned interplanetary missions such as a manned mission to Mars. This option is, however, dependent on the availability of high energy sources for propulsive power in addition to that required for the manned interplanetary transit vehicle. Two power system technologies are presented: nuclear and solar. The ion thruster technology for the interplanetary transit vehicle is described for a typical mission. The power management and distribution system components required for such a mission must be further developed beyond today's technology status. High voltage-high current technology advancements must be achieved. These advancements are described. In addition, large amounts of waste heat must be rejected to the space environment by the thermal management system. Advanced concepts such as the liquid droplet radiator are discussed as possible candidates for the manned Mars mission. These thermal management technologies have great potential for significant weight reductions over the more conventional systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Manned Mars Mission. Working Group Papers, V. 2, Sect. 5, App.; p 797-814
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Microanalyses of extended-test xenon hollow cathodes (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Four hollow cathodes have been examined using boroscopy, scanning electron microscopy, energy dispersive X-ray analysis, and X-ray diffraction analysis to characterize the life-limiting phenomena that resulted from their extended operation. The first pair of cathodes was operated for approximately 500 h in an ion thruster simulator at a 5.0 kW-equivalent power level using different cathode activation and propellant feed-system procedures. The second pair of cathodes was the main discharge cathode and neutralizer cathode from an ion thruster which have completed an 89-hour life-test at a 5.5 kW power level. The greatest change to the cathode condition was found to be removal of refractory metals, primarily tungsten, and their subsequent deposition on other cathode surfaces. Barium tungstate and barium molybdate were also found in all four cathodes. Criteria for improved cathode longevity and discharge operation are proposed for use in hollow cathode and full thruster testing facilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2123
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Ion beam sputtering in electric propulsion facilities (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Experiments were undertaken to determine sputter yields of potential ion beam target materials, to assess the impact of charge exchange on beam diagnostics in large facilities, and to examine material erosion and deposition after a 957-hour test of a 5 kW-class ion thruster. The xenon ion sputter yield of flexible graphite was lower than other graphite forms especialy at high angles of incidence. Ion beam charge exchange effects were found to hamper beam probe current collection diagnostics even at pressures from 0.7 to 1.7 mPa. Estimates of the xenon ion beam envelope were made and predictions of the thickness of sputter deposited coatings in the facility were compared with measurements.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2117
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    5kW xenon ion thruster lifetest (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the results of the first lifetest of a high power ring-cusp ion thruster. A 30-cm laboratory model thruster was operated steady-state at a nominal beam power of 5kW on xenon propellant for approximately 900 hours. This test was conducted to identify life-limiting erosion mechanisms and thruster design modifications, and to demonstrate operation using simplified power processing. The results from this test are described including the conclusions derived from extensive post-test analyses of the thruster. Modifications to the thruster and ground support equipment, which have been incorporated to solve problems identified by the lifetest, are also described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2543
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    NASA TECHNICAL REPORTS
  • 5
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    Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Nuclear-powered ion propulsion technology was combined with detailed trajectory analysis to determine propulsion system and trajectory options for an unmanned cargo mission to Mars in support of manned Mars missions. A total of 96 mission scenarios were identified by combining two power levels, two propellants, four values of specific impulse per propellant, three starting altitudes, and two starting velocities. Sixty of these scenarios were selected for a detailed trajectory analysis; a complete propulsion system study was then conducted for 20 of these trajectories. Trip times ranged from 344 days for a xenon propulsion system operating at 300 kW total power and starting from lunar orbit with escape velocity, to 770 days for an argon propulsion system operating at 300 kW total power and starting from nuclear start orbit with circular velocity. Trip times for the 3 MW cases studied ranged from 356 to 413 days. Payload masses ranged from 5700 to 12,300 kg for the 300 kW power level, and from 72,200 to 81,500 kg for the 3 MW power level.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100109 , E-3641 , NAS 1.15:100109 , AIAA PAPER 87-1903
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    NASA TECHNICAL REPORTS
  • 6
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    Development of arcjet and ion propulsion for spacecraft stationkeeping (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Near term flight applications of arcjet and ion thruster satellite station-keeping systems as well as development activities in Europe, Japan, and the United States are reviewed. At least two arcjet and three ion propulsion flights are scheduled during the 1992 - 1995 period. Ground demonstration technology programs are focusing on the development of kW-class hydrazine and ammonia arcjets and xenon ion thrusters. Recent work at NASA Lewis Research Center on electric thruster and system integration technologies relating to satellite stationkeeping and repositioning will also be summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 92-0607
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Krypton ion thruster performance (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Preliminary data were obtained from a 30 cm ion thruster operating on krypton propellant over the input power range of 0.4-5.5 kW. The data are presented, and compared and contrasted to those obtained with xenon propellant over the same input power envelope. Typical krypton thruster efficiency was 70 percent at a specific impulse of approximately 5000 s, with a maximum demonstrated thrust-to-power ratio of approximately 42 mN/kW at 2090 s specific impulse and 1580 watts input power. Critical thruster performance and component lifetime issues were evaluated. Order-of-magnitude power throttling was demonstrated using a simplified power-throttling strategy.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3144
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    The evolutionary development of high specific impulse electric thruster technology (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Electric propulsion flight and technology demonstrations conducted in the USA, Europe, Japan, China, and USSR are reviewed with reference to the major flight qualified electric propulsion systems. These include resistojets, ion thrusters, ablative pulsed plasma thrusters, stationary plasma thrusters, pulsed magnetoplasmic thrusters, and arcjets. Evolutionary mission applications are presented for high specific impulse electric thruster systems. The current status of arcjet, ion, and magnetoplasmadynamic thrusters and their associated power processor technologies are summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-1556
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Performance of 10-kW class xenon ion thrusters (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Presented are performance data for laboratory and engineering model 30 cm-diameter ion thrusters operated with xenon propellant over a range of input power levels from approximately 2 to 20 kW. Also presented are preliminary performance results obtained from laboratory model 50 cm-diameter cusp- and divergent-field ion thrusters operating with both 30 cm- amd 50 cm-diameter ion optics up to a 20 kW input power. These data include values of discharge chamber propellant and power efficiencies, as well as values of specific impulse, thruster efficiency, thrust and power. The operation of the 30 cm- and 50 cm-diameter ion optics are also discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-101292 , E-4272 , NAS 1.15:101292 , AIAA PAPER 88-2914
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Performance of 10-kW class xenon ion thrusters (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Presented are performance data for laboratory and engineering model 30 cm-diameter ion thrusters operated with xenon propellant over a range of input power levels from approximately 2 to 20 kW. Also presented are preliminary performance results obtained from laboratory model 50 cm-diameter cusp- and divergent-field ion thrusters operating with both 30 cm- and 50 cm-diameter ion optics up to a 20 kW input power. These data include values of discharge chamber propellant and power efficiencies, as well as values of specific impulse, thruster efficiency, thrust and power. The operation of the 30 cm- and 50 cm-diameter ion optics are also discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-2914
    Format: text
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