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  • 1
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    Energy deposition via magnetoplasmadynamic acceleration: II. modeling and performance predictions (2008)
    Institute of Physics
    Details
    Publication Date: 2008-11-24
    Print ISSN: 0963-0252
    Electronic ISSN: 1361-6595
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Multimegawatt electric propulsion system design considerations (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Piloted Mars mission requirements of relatively short trip times and low initial mass in earth orbit as identified by the NASA Space Exploration Initiative, indicate the need for multimegawatt electric propulsion systems. The design considerations and results for two thruster types, the argon ion and hydrogen magnetoplasmadynamic thrusters, are addressed in terms of configuration, performance, and mass projections. Preliminary estimates of Power Management and Distribution for these systems are given. Some assessment of these systems' performance in a reference Space Exploration Initiative piloted mission are discussed. Research and development requirements of these systems are also described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2552
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Early Track NEP system options for SEI missions (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A development option for nuclear electric propulsion, the 'Early Track' option, is considered from system and mission application viewpoints. The intent of this development option is to address demanding missions of the future, such as robotic outer planet exploration or the Space Exploration Initiative. The 'Early Track' scheme utilizes existing technologies, such as the SP-100 space reactor and radiator components, as well as subsystems scalable from existing programs, such as 50 to 100 kWe ion thrusters. Up to 1.5 MWe of powder can be generated by the existing 2.4 MWt SP-100 reactor through the use of dynamic Rankine or Brayton power conversion. The performance characteristics of these systems are projected, and assessed for SEI missions currently under consideration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3200
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Evolutionary use of nuclear electric propulsion (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Evolving new propulsion technologies through a rational and conscious effort to minimize development costs and program risks while maximizing the performance benefits is intuitively practical. A phased approach to the evolution of nuclear electric propulsion from use on planetary probes, to lunar cargo vehicles, and finally to manned Mars missions with a concomitant growth in technology is considered. Technology levels and system component makeup are discussed for nuclear power systems and both ion and magnetoplasmadynamic thrusters. Mission scenarios are described, which include analysis of a probe to Pluto, a lunar cargo mission, Martian split, all-up, and quick-trip mission options. Evolutionary progression of the use of NEP in such missions is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-3821
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Solar electric propulsion for Mars transport vehicles (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Solar electric propulsion (SEP) is an alternative to chemical and nuclear powered propulsion systems for both piloted and unpiloted Mars transport vehicles. Photovoltaic solar cell and array technologies were evaluated as components of SEP power systems. Of the systems considered, the SEP power system composed of multijunction solar cells in an ENTECH domed fresnel concentrator array had the least array mass and area. Trip times to Mars optimized for minimum propellant mass were calculated. Additionally, a preliminary vehicle concept was designed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-103234 , E-5654 , NAS 1.15:103234
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    MPD thruster scaling (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Full scale and half scale versions of the Princeton Benchmark and Flared Anode self-field MPD thrusters have been investigated to determine the influence of scale and design upon MPD behavior. Thruster performance determined by impulsive thrust and terminal voltage measurements is found to depend primarily on propellant flow rate and the ratio of electrode radii, but not on thruster size. Current distributions obtained from magnetic field probes are independent of scale for both thruster designs. Voltage depends upon current, electrode geometry, and propellant flow rate. This behavior agrees qualitatively with calculations based on a fundamental MHD formulation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-0997
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Multimegawatt electric propulsion system design considerations (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Piloted Mars Mission Requirements of relatively short trip times and low initial mass in Earth orbit as identified by the NASA Space Exploration Initiative, indicate the need for multimegawatt electric propulsion systems. The design considerations and results for two thruster types, the argon ion, and hydrogen magnetoplasmadynamic thrusters, are addressed in terms of configuration, performance, and mass projections. Preliminary estimates of power management and distribution for these systems are given. Some assessment of these systems' performance in a reference Space Exploration Initiative piloted mission are discussed. Research and development requirements of these systems are also described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-105152 , E-6437 , NAS 1.15:105152 , AIAA PAPER 90-2552 , International Electric Propulsion Conference; Jul 18, 1990 - Jul 20, 1990; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Gradient Field Imploding Liner Fusion Propulsion System: NASA Innovative Advanced Concepts Phase I Final Report (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The advancement of human deep space exploration requires the continued development of energetic in-space propulsion systems, from current chemical engines to nuclear thermal rockets to future high energy concepts such as nuclear fusion. As NASA embarks on a program to develop near-term nuclear thermal propulsion, this NASA Innovative Advanced Concepts (NIAC) Phase I activity was funded to investigate the feasibility of an innovative approach toward highly energetic pulsed fusion propulsion. Previous concept studies have proposed the conversion of fusion energy for in-space propulsion, ranging from laser-ignited fusion systems such as Gevaltig and VISTA, to the British Interplanetary Society's Daedalus concept and its more recent incarnation under Project Icarus, to steady-state spherical torus fusion systems. Recent NIAC studies have also evaluated several innovative fusion concepts, including the acceleration and compression of field reversed configuration plasmas in time-changing magnetic fields, magnetically driven liners imploding onto plasma targets, and high current z-pinch compression of material liners onto fission-fusion fuel targets. While each of these studies firmly established the potential benefits of fusion systems for interplanetary travel, they also identified significant challenges in successfully engineering such systems for spacecraft propulsion. The concept outlined in this Technical Publication (TP) builds on the lessons learned from these prior activities, approaching the quest for fusion-powered propulsion through an innovative variation of magneto-inertial fusion concepts developed for terrestrial power applications.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-2018-219996 , M-1471 , MSFC-E-DAA-TN53878
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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